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
2008032500257	20080325	00257	CE  	2008	3	25	0000H2484        	1	20080318	G	2820		LINE            			BEECH 	35    	V35         	1151538	CE  	CONT  	O550  	IO550B      	 	SO  					FUEL SYSTEM	CHAFED          	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	363BC		3    			D9763	297203R			FUEL LINE MOUNTED ON FIREWALL FABRICATED PER STC SA8676SW WAS CHAFING THE ENGINE TAILPIPE.						1	L	7	1 	3O	3	O		3A15    	E3SO				 
2008040300090	20080403	00090	CE  	2008	4	3	01030413         	1	20080103	G	3242	314901	BRAKE ASSY      	BFGOODRICH  		CESSNA	500   	560CESSNA   	2076750	CE  										MLG	LOCKED          	B			PAZR	O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CE	03	561JS				2290	5600413				UPON LANDING THE AIRCRAFT YAWED TO THE RIGHT AND IN OVERCOMPENSATING THE AIRCRAFT THEN STARTED A SIDEWAYS DRIFT ENOUGH T	HAT THE LEFT MAIN TIRE FAILED. IT WAS FOUND THAT ONE RIGHT HAND BRAKE STATOR WAS LOCKED AND HAD GROUND THE WHEEL FLAT AN	D THE LEFT MAIN FAILED AS A RESULT OF TIRE SIDEWALL FAILURE. DAMAGE INCLUDES BOTH TIRES AND WHEELS. LEFT LANDING LIGHT. 	LEFT HAND INBOARD FLAP AND RIGHT HAND BRAKE AND BRAKE LINES.			2	L	7	2 	4F			RT	A22CE   					 
2008041000260	20080410	00260	EU  	2008	4	10	03252008         	1	20080325	G	3233	D52177	HOLDER          	MESSIER     		AMD   	FALC20	FALCON200   	2730150	EU  										ACTUATOR	BROKEN          	B				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			SW	05					DRI76878					THE PACKING HOLDER P/N D52177 BROKE IN (2) PIECES CAUSING HYDRAULIC FLUID LOSS.  THIS PART HAD BEEN MODIFIED IAW SB F200	-110 TO PREVENT FUTURE FAILURES.  THIS IS THE SECOND PACKING HOLDER FOUND TO BE BROKEN AFTER MODIFICATION. BOTH PARTS WE	RE MODIFIED AND IDENTIFIED SRD IAW THE S/B.				2	L	7	2 	4F			RT	A7EU    					 
2008031300042	20080313	00042	SO  	2008	3	13	115301           	1	20080218	G	4910	1159AC30551103	DUCT            			GULSTM	G1159 	GIV         	3980115	SO  										APU INLET	CRACKED         	E			CLWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	589HM	6464 				1153				A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).						2	L	7	2 	4F			RT	A12EA   					 
2008031300044	20080313	00044	SO  	2008	3	13	115302           	1	20080218	G	4910	1159AC30551103	DUCT            			GULSTM	G1159 	GIV         	3980115	SO  										APU INLET	CRACKED         	E			CLWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	589HM	6464 				1153				A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).						2	L	7	2 	4F			RT	A12EA   					 
2008021900067	20080219	00067	CE  	2008	2	19	20080101         	1	20080118	G	2752	505212234	ACTUATOR        			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					T/E FLAP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99						LJ833				RT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE.  CRACK RUNS PARAL	LEL TO TUBE .					1	L	7	2 	3T	4	T		3A20    	E4EA				 
2008050800116	20080508	00116	SO  	2008	5	8	20080420001      	1	20080420	G	7810		BRACKET         			MAULE 	MX7   	MX7180A     	5460186	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE EXHAUST	CRACKED         	C				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SO	16										ON TAKE-OFF, 50 FEET, PARTIAL POWER LOSS (2,500+ RPM TO 1,100 RPM) AND ENGINE ROUGHNESS.  ABORTED TAKE-OFF.  WHEN CARBUR	ATOR TAKEN OFF PLANE, FOUND 1 INCH X .5 INCH PIECE OF METAL LOOSE IN AIR/FUEL MIXING CHAMBER UPSTREAM OF VENTURI. PIECE 	WAS TOO BIG TO GO THROUGH VENTURI, BUT BIG ENOUGH TO DISRUPT FLOW THROUGH VENTURI.  FOUND SOURCE OF METAL TO BE A PIECE 	OF THE BRACKET FROM LEFT MUFFLER. BRACKET USED TO CONNECT SHROUD TO MUFFLER TO CAPTURE HEAT FOR USE IN DIRECTING CARB HE	AT. ENTIRE BRACKET WAS ABOUT 12 INCHES LONG. THE 1 INCH LONG PIECE OF THE BRACKET BROKE OFF AND MADE ITS WAY DOWN CARB H	EAT DUCTING INTO MIXING CHAMBER OF MUFFLER, UPSTREAM OF VENTURI.  BASED ON ENGINE OPERATIONS, BELIEVE PIECE HAD BROKEN F	1	H	7	1 	3O	3	O	NC	3A23    	E286				 
	20080519		CE  	2008	5	19	20080506FA001    	1	20080506	G	3246	10320400AN53	BOLT            	PARKERHANFIN		RAYTHN	36    	G36         	7150061	CE  										RT MLG WHEEL	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	222GL	479  	479  			E3763				THE PILOT REPORTED A "POP" AS HE WAS GROUND HANDLING THE AIRCRAFT ON THE RAMP (IN A STRAIGHT DIRECTION USING AN AIRTUG).	  FURTHER INVESTIGATION REVEALED 1 NUT/BOLT COMBINATION HAD SHEARED ON THE INBOARD WHEEL HALF OF THE RIGHT HAND MAIN LAN	DING GEAR ASSEMBLY.  THE BOLT HAD SUBSEQUENTLY BACK OUT APPROXIMATELY 1/4INCH.  THIS AIRCRAFT HAS BEEN THROUGH 1 ANNUAL 	INSPECTION AND HAS NEVER HAD THE WHEEL HALVES DISASSEMBLED.  UPON DISCOVERY OF THE SHEARED BOLT, THE LEFT AND RIGHT WHEE	LS WERE DISASSEMBLED, CLEANED, INSPECTED AND REASSEMBLED WITH NEW BOLTS AND NUTS.  DURING DISASSEMBLY OF THE WHEEL HALF 	RETAINING BOLTS IT WAS NOTED THAT VERY LITTLE FORCE WAS REQUIRED TO BREAK THE NUTS LOOSE. THE NOSE WHEEL WAS THEN CHECKE	1	L	7	1 	3O			RT	3A15    					 
	20080701		EA  	2008	7	1	2008F00016       	2	20080415	G	8500		ENGINE          			GIPPLD	GA8   	GA8         	3900102	EU  	LYC   	O540  	IO540K1A5   	41532	EA  						FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	23	7508M					GA805094	L3095348A			AIRCRAFT EXPERIENCED AN ENGINE FAILURE. ATTEMPTS TO RESTART ENGINE FAILED AND A SAFE LANDING WAS ACCOMPLISHED. CAUSE OF 	FAILURE REMAINS UNKNOWN AT THIS TIME. (K)					1	H	7	1 	3O	3	O	NT	        	1E4				 
	20080811		CE  	2008	8	11	2008F00019       	1	20080715	G	3260	A46270	SWITCH          			CESSNA	500   	550         	2076604	CE  										MLG	OUT OF ADJUST   	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	68	187JN					5500335				ON DEPARTING AIRPORT, UPON GEAR RETRACTION, THE DOOR UNLOCK LIGHT ACTIVATED.  THE PILOT OPTED TO BURN FUEL AND LAND WHEN	 LANDING WEIGHT WAS ACHIEVED.  THE LANDING WAS WITHOUT INCIDENT.  MAINT WAS THEN CALLED.  THE SWITCH WAS DETERMINED TO B	E OUT OF ADJUSTMENT.  THE SWITCH WAS THEN ADJUSTED IAW MM AND RETURNED TO SERVICE.  (K)				1	L	7	2 	4F				A22CE   					 
	20080811		GL  	2008	8	11	2008F00020       	1	20080711	G	6100		ROD             			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					PITCH CHANGE	MISINSTALLED    	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	99	554PG					2009	360674			ON INSTALLATION OF PROP TO ENG MOUNTING FLANGE IAW MM 61-00-45, THE PLASTIC PROTECTIVE CAP FITTED TO THE END OF THE PITC	H CHANGE ROD WAS NOT REMOVED.  ON FLIGHT TEST OF THE AC, ENGINE OVERSPEED WAS NOTED AT TAKEOFF TO 2850 RPM, NO SIGNIFICA	NT LOSS OF OIL PRESSURE WAS NOTED.  THE PILOT THROTTLED BACK TO REDUCE PROPELLER SPEED TO LESS THAN 2700 RPM ( WITHIN PE	RMITTED LIMITATIONS) ENGINE POWER WAS REDUCED TO 48 PERCENT AT THIS POINT AND THE ENGINE SUBSEQUENTLY STOPPED.  THE PILO	T RESTARTED THE ENGINE, SLIGHTLY EXCEEDING 2700 RPM FOR A SHORT PERIOD.  THE PILOT RETURNED THE AIRCRAFT TO BASE, LANDIN	G SAFELY AND REPORTED THE INCIDENT TO THE MAINT MGR.  ON INVESTIGATION THE PROP WAS REMOVED AND THE PROTECTIVE CAP WAS I	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
	20081110		EA  	2008	11	10	2008F00024       	2	20081001	G	7414	4371	MAGNETO         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	227BH					172S10662	L33887L2A			EXCESSIVE MAGNETO DROP DURING RUNUP AND MAGNETO CHECK. 100 RPM DIFFERENTIAL BETWEEN LT AND RT MAGNETO, ALSO RT MAGNETO R	UNNING ROUGH. CHECKED FOUND RT MAGNETO TIMING OFF. FOUND RT MAGNETO AT 20 DEGREES BEFORE TOP DEAD CENTER, SUPPOSE TO BE 	25 DEGREES BTDC.  DRIVE GEAR FOR THE DISTRIBUTOR WAS FOUND UNEVEN, CAUSING IT TO WOBBLE WHEN ROTATING. THIS CAUSED UNUSU	AL WEAR ON BOTH DRIVE GEAR AND DISTRIBUTOR GEAR. DRIVE GEAR MATERIAL NOT REMOVED DURING CLEANUP PROCESS FROM INJECTION M	OLDING. PIECES WERE COMING OFF INSIDE MAGNETO. EXCESSIVE CAM WEAR FOR 379.9 HRS. CONTACT POINTS FOUND MISALIGNED,  BREAK	ER POINT ARM HAS FALLEN DOWN & IS RIDING ON THE RIDGE ON CAM. RIDGE CREATED BY EXCESSIVE CAM WEAR. CONDITION MAY CAUSE R	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081210		NE  	2008	12	10	2008F00025       	1	20081113	G	2612		PROBE           			SKRSKY	S76   	S76C        	8143008	NE  										FIRE WARNING	MALFUNCTIONED   	G				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			EA	63	85PS					760489				NUMBER 2 ENGINE HAD A FIRE CAUTION WARNING LIGHT ILLUMINATE WITH HORN FOR TWO SECONDS. THIS OCCURRED TWICE DURING THE FL	IGHT.  WHEN THE MECHANICS TRIED TO TROUBLESHOOT THE PROBLEM, COULD NOT DUPLICATE IT.  TO FURTHER TROUBLESHOOT, THE AFT N	R 1 & 2 FIRE PROBES P/N 76306-07902-104 WERE SWAPPED TO SEE IF THE PROBLEM RE-OCCURRED AND FOLLOWED THE PROBE.				1	G	7	2 	3U			NC	H1NE    					 
	20090105		EU  	2009	1	5	2008F00026       	1	20081216	G	5311	117223121151	FRAME           			BOLKMS	117   	BK117B1     	5626012	EU  										ZONE 200	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	330SL					7216				DURING INSP FOUND SPIDER CRACKS AROUND 1 RIVET ON THE DECK UNDER THE TANDEM HYD PACK. FURTHER INSP FOUND 2 FRAMES CRACKE	D UNDER THE HYD DECK.					1	G	7	2 	3U				H13EU   					 
	20090106		EU  	2009	1	6	2008F00027       	1	20081215	G	7797	MS3126F1415S	CONNECTOR       			BRAERO	DH125 	HS125700A   	4230170	EU  										N1 INDICATOR	DEFECTIVE       	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	411P	11744	1070 		549E					ON NOVEMBER 23, 2008, THE NR 2 ENGINE N1 GAUGE DIGITAL PORTION FAILED. THE MALFUNCTION WAS TRACED TO A DEFECTIVE CONNECT	OR AT THE GAUGE.					2	L	7	2 	4F				A3EU    					 
2008011100261	20080111	00261	SO  	2008	1	11	2008FA0000003    	1	20080102	G	3213	39489003	STRUT           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C512   	GL  	RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	69BP	2091 	2091 			3449085	321475	981180		DURING ANNUAL INSPECTION IT WAS NOTED THAT A CRACK WAS FOUND ON THE RT MAIN GEAR LOWER FORK ASSY PN 39489-003.  THE CRAC	K IS LOCATED IN THE MILLED SECTION OF THE CASTING AT THE 11 O'CLOCK AND 1 O'CLOCK POSITIONS. THIS MILLED SECTION IS USED	 TO BOLT THE TORQUE PLATE PN 451-786 TO THE MLG ASSY. CONTACTED MFG THRU THERE DAS SYSTEM AND WAS TOLD THEY NEVER HEARD 	OF ANY PROBLEMS. REQUESTED FROM MFG TO BLEND CRACK AREA OUT AND REQUEST WAS DENIED. PROCEEDED TO CONTACT A DER FOR APPRO	VAL ON BLENDING CRACKED AREA OUT AND AGAIN REQUEST DENIED. FOUND ANOTHER LOWER STRUT IN A SALVAGE YARD WHICH WE PURCHASE	D ONLY TO FIND THIS STRUT ALSO WAS CRACKED IN THE EXACT SAME SPOT. ALSO I NOTED THAT THE CASTING VARY IN THICKNESS UPTO 	1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2008011000012	20080110	00012	SO  	2008	1	10	2008FA0000004    	1	20080102	G	3213	39489003	STRUT           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C512   	GL  	RT MAIN GEAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	69BP	2091 	2091 			3449085	321475	981180		DURING ANNUAL INSPECTION, IT WAS NOTED THAT A CRACK WAS FOUND ON THE RT MAIN GEAR LOWER FORK ASSEMBLY PN 39489-003.  THE	 CRACK IS LOCATED IN THE MILLED SECTION OF THE CASTING AT THE 11 O'CLOCK AND 1 O'CLOCK POSITIONS. THIS MILLED SECTION IS	 USED TO BOLT THE TORQUE PLATE PN 451-786 TO THE MAIN LANDING GEAR ASSY. CONTACTED MFG THRU THERE DAS SYSTEM AND WAS TOL	D THEY NEVER HEARD OF ANY PROBLEMS. REQUESTED FROM MFG TO BLEND CRACK AREA OUT AND REQUEST WAS DENIED. PROCEEDED TO CONT	ACT A DER FOR APPROVAL ON BLENDING CRACKED AREA OUT AND AGAIN REQUEST DENIED. FOUND ANOTHER LOWER STRUT IN A SALVAGE YAR	D WHICH WE PURCHASED ONLY TO FIND THIS STRUT ALSO WAS CRACKED IN THE EXACT SAME SPOT. THIS STRUT CAME OFF A MODEL PA34-2	1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
2008011400075	20080114	00075	CE  	2008	1	14	2008FA0000010    	1	20080104	G	3213	390810001	STRUT           			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					LT MLG	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	09	701KB	30   				RB211				PILOT REPORTED LT AND RT MAIN LANDING GEAR STRUTS LEAKING HYDRAULIC FLUID. DISASSEMBLY LOWER LT MAIN LANDING GEAR STRUT,	 FOUND PAINT CHIPS CONTAMINATING SEALS. DISASSEMBLED RT LOWER MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING S	EALS AND METAL FILLINGS IN INNER BARREL OF STRUT.				1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
2008011400074	20080114	00074	CE  	2008	1	14	2008FA0000011    	1	20080104	G	3213	390810001	STRUT           			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					RT MLG	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	09	701KB	30   				RB211				PILOT REPORTED LT AND RT MAIN LANDING GEAR STRUTS LEAKING HYDRAULIC FLUID. DISASSEMBLY LOWER LT MAIN LANDING GEAR STRUT,	 FOUND PAINT CHIPS CONTAMINATING SEALS. DISASSEMBLED RT LOWER MAIN LANDING GEAR STRUT, FOUND PAINT CHIPS CONTAMINATING S	EALS AND METAL FILLINGS IN INNER BARREL OF STRUT.				1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
2008011100297	20080111	00297	EA  	2008	1	11	2008FA0000013    	2	20080102	G	7414	6393	MAGNETO         			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE	WORN            	C				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			SO	14	51RF	50   	50   							CAM LOBE INSIDE MAG THAT OPENS AND CLOSES POINTS WORN OUT.						1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P25EA	 
2008011400030	20080114	00030	CE  	2008	1	14	2008FA0000018    	1	20080108	G	2701		YOKE            			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360*       	41514	EA  						MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	30673					17701397				WHILE DOING AN ANNUAL, FOUND LOOSENESS IN THE YOKE FOR AND AFT MOVEMENT.  AFTER MUCH CHECKING, FOUND THE LOOSENESS TO BE	 BETWEEN THE YOKE LEVER ASSY 1767033-7 AND 1767037-2 WHICH IS THE SHAFT. ALSO THERE WAS LOOSENESS BETWEEN THE SHAFT 1767	037-2 AND THE QUADRANT 1767024-1.  FURTHER INVESTIGATION FOUND STANDARD AN4 BOLTS INSTEAD OF THE NAS464P4-17 CALLED FOR 	IN THE PARTS MANUAL CONNECTING THESE PARTS.  THE DIFFERENCE IN DIAMETER OF THE BOLTS CAUSED THE LOOSENESS. PARTS MANUAL,	 FIGURE 63.		1	H	7	1 	3O	3	O		A13CE   	E286				 
2008012200046	20080122	00046	EU  	2008	1	22	2008FA0000036    	1	20080114	G	3210	DIN47108VERZ	RETAINING CLIP  			DIAMON	DA42  	DA42        	2990004	EU  										DOWNLOCK PIN	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	966WW	13   	13   			42AC106				DURING PREFLIGHT THE PILOT NOTICED THAT THE MLG DOWNLOCK PIN (PN-D60-3237-11-34) HAD NO RETAINING CLIPS(PN-DIN471-08-VER	Z). THE GROOVES IN THE PIN ARE VERY SHALLOW AND ALLOW THE CLIPS TO MIGRATE OFF.					1	L	7	2 	3I			RT	A57CE   					 
2008012200194	20080122	00194	SO  	2008	1	22	2008FA0000041    	1	20080109	G	7120		MOUNT           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					LT ENGINE	CRACKED         	B			B2ER	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			EA	23	25EL					28R7837087				ENGINE MOUNT FOUND CRACKED AT BOTTOM LT WHERE SHOCK MOUNT ATTACHES.  (K)						1	L	7	1 	3O	3	O		2A13    	1E10				 
2008021200236	20080212	00236	EA  	2008	2	12	2008FA0000043    	2	20080111	G	8520	600050507	PUSHROD         			PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	700LG					608265043				THE AREA IN WHICH THE CORRODED SECTION OF THE PUSHROD ASSY IS LOCATED IS PRONE TO EXHAUST CONTAMINATION SINCE IT IS DIRE	CTLY BEHIND THE ENGINE EXHAUST PIPE OUTLETS.  AREA NEEDS TO BE KEPT CLEAN OF EXHAUST RESIDUE AND CORROSION PREVENTATIVE 	APPLIED.  OLDER TUBES WERE ALODINED ALUMINUM.  NEWER TUBES ARE ZINC CHROMATED ALUMINUM BUT ARE STILL SUSCEPTIBLE TO CORR	OSION.  INSPECTION OF THIS  AREA IS ACCESSIBLE THROUGH THE WING FLAP ACTUATOR ACCESS PANEL.  SB 600-122 ADDRESSES THIS S	UBJECT.  (K)		1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2008021200237	20080212	00237	EA  	2008	2	12	2008FA0000044    	2	20080111	G	8520	600050507	PUSHROD         			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	25RH	2446 				61P066979633				THE AREA IN WHICH THE CORRODED SECTION OF THE PUSHROD ASSY IS LOCATED IS PRONE TO EXHAUST CONTAMINATION SINCE IT IS DIRE	CTLY BEHIND THE ENGINE EXHAUST PIPE OUTLETS.  THIS AREA NEEDS TO BE KEPT CLEAN OF EXHAUST RESIDUE AND CORROSION PREVENTA	TIVE APPLIED.  OLDER TUBES WERE ALODINED ALUMINUM.  NEWER TUBES ARE ZINC CHROMATED ALUMINUM BUT ARE STILL SUSCEPTIBLE TO	 CORROSION.  SB 600-122 ADDRESS THIS SUBJECT.  INSPECTION IS DONE THROUGH FLAP ACTUATOR ACCESS PANEL.  (K)			1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2008021200239	20080212	00239	SO  	2008	2	12	2008FA0000046    	1	20080104	G	3297	153615	WIRE            			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	FAILED          	D			SNSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	878BT	446  				3257402				MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILIC	ONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETTER WIRE AND ROUTING.  (K)					1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2008021200240	20080212	00240	SO  	2008	2	12	2008FA0000047    	1	20080109	G	3297	153615	WIRE            			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	FAILED          	D			SNSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	5354V	528  				3257298				MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILIC	ONE TYPE WIRE COATING TENDS TO HOLE WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETTER WIRE AND ROUTING.  (K)					1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2008013100288	20080131	00288	SO  	2008	1	31	2008FA0000048    	1	20080104	G	3297	153615	WIRE            			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					DOWNLOCK SWITCH	FAILED          	D			SNSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	5354V					3257298				MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILIC	ONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETTER WIRE AND ROUTING.  (K)					1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2008021200241	20080212	00241	SO  	2008	2	12	2008FA0000049    	1	20080111	G	3297	153615	WIRE            			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	FAILED          	D			SNSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	999TC					3257356				MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILIC	ONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETTER WIRE AND ROUTING.  (K)					1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2008021200242	20080212	00242	SO  	2008	2	12	2008FA0000050    	1	20080104	G	3297	153615	WIRE            			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	FAILED          	D			SNSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	999TC	249  				3257356				MAIN GEAR DOWN LOCK SWITCH WIRES PULL TIGHT ON STRUT ON RETRACTION AND PULL WIRE STRANDS APART TO BREAKING POINT.  SILIC	ONE TYPE WIRE COATING TENDS TO HOLD WIRE ENDS TOGETHER FOR INTERMITTENT CONTACT.  NEEDS BETER WIRE AND ROUTING.  (K)					1	L	7	1 	3O	3	O		A3SO    	E14EA				 
2008021200245	20080212	00245	CE  	2008	2	12	2008FA0000051    	1	20080107	G	2752	991434446	FLEX DRIVE      			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					T/E FLAP	WORN            	B			CNQR	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CE	07	953QS					7500153				AIRCRAFT EXPERIENCED A FLAP FAIL MESSAGE AFTER TAKEOFF, DIVERTED FOR REPAIR AND THE PILOT ELECTED TO DECLARE AN EMERGENC	Y BEFORE LANDING.  THE AIRCRAFT LANDED WITHOUT INCIDENT.  AFTER TROUBLESHOOTING, THE FLAP SYSTEM THE RT AND LT NR 5 FLAP	 FLEX DRIVES WERE FOUND TO BE WORN CAUSING A FLAP FAULT.  DRIVES HAVE BEEN REPLACED AND SYSTEM MECHANICAL AND ELECTRICAL	 OPERATIONAL CHECK ACCOMPLISHED.  NO FURTHER DEFECTS WERE FOUND.  (K)			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2008013100296	20080131	00296	CE  	2008	1	31	2008FA0000052    	1	20080116	G	3060		BOOT            			BEECH 	60    	A60         	1153604	CE  	LYC   	O541  	TIO541*     	41536	EA  					PROPELLER	SEPARATED       	B			PZ4R	K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			GL	11	4445W					P245				A PROPELLER CAME IN FOR REPAIRS WHICH NECESSITATED THE INSTALLATION OF NEW DEICE BOOTS ON ALL 3 BLADES.  THE PROP WAS LA	TER INSTALLED BY THE OWNERS MECHANIC.  1 OF THE 3 BOOTS CAME OFF RESULTING IN A DENT ON THE AIRCRAFT FUSELAGE, REPORTED	 AFTER ABOUT 7 HOURS OF FLYING.  QUESTIONING OF OUR TECH THAT INSTALLED THE BOOTS REVEALED NO DEVIATIONS IN PROCEDURES O	CCURRED DURING THE INSTALLATION. IT WAS DETERMINED THAT THE GLUE USED FOR THE INSTALLATION WAS RECEIVED BY OUR FACILITY 	ON 8/23/07 WITH AN EXPIRATION  DATE OF 9/30/08.  MM 202A LISTS THE SHELF LIFE OF 1300L ADHESIVE AS 15 MONTHS.  AS A PREC	AUTION, THE ADHESIVE WAS REMOVED FROM USE EVEN THOUGH NO DISCREPANT CONDITION COULD BE FOUND.  FACILITY VISITED LOCATION	1	L	7	2 	3O	3	O		A12CE   	E10EA				 
2008013100292	20080131	00292	CE  	2008	1	31	2008FA0000053    	1	20080117	G	2134	1303687	PRESSURE SENSOR 			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					AFT BAGGAGE	MALFUNCTIONED   	E				B				EMER. DESCENT           				J			WARNING INDICATION        			CL	CLIMB          	1			SO	11	55FN	11587				202				LOSS OF CABIN PRESSURE AT 25K FT. PRESSURE SENSOR MALFUNCTIONED						2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2008013100294	20080131	00294	CE  	2008	1	31	2008FA0000056    	1	20080123	G	5514		ATTACH BOLT     			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15*       	52060	NE  					HORIZONTAL STAB	UNDERTORQUED    	B			HSRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	570EJ					5600164				DURING A ROUTINE PHASE INSPECTION WE FOUND 50 PERCENT OF THE HORIZONTAL STABILIZER AFT ATTACH BOLTS TO BE UNDERTORQUED, 	AND CAUSING SOME MOVEMENT AND A POPPING NOISE WHEN THE STABILIZER WAS PUSHED UP AND DOWN AT THE OB TIP.  WE RE-TORQUED A	LL BOLTS AND THE NOISE AND MOVEMENT WENT AWAY. SOME OF THE BOLTS REQUIRED 180 DEGREE ROTATION TO OBTAIN PROPER TORQUE.  	PERFORMED HIDDEN DAMAGE INSPECTION, NO DEFECTS WERE NOTED.			2	L	7	2 	4F	4	T	RT	A22CE   	E1NE				 
2008012900004	20080129	00004	SO  	2008	1	29	2008FA0000057    	1	20080118	G	7603	455322	THROTTLE CABLE  			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  						INFLT SEPARATION	B				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SO	15	701ER	4192 	82   			2844053				DURING FLIGHT, THE CREW EXPERIENCED A SEPARATION OF THE THROTTLE CABLE. THE POWER SETTING ALLOWED THEM TO MAINTAIN ALTIT	UDE PLUS A SLIGHT CLIMB. THE CREW POSITIONED THE AIRCRAFT FOR A LANDING ON A RUNWAY THAT HAD AMPLE LENGTH. AN UNEVENTFUL	 LANDING WAS MADE. THE THROTTLE CABLE WAS REMOVED AND INSPECTED AND FOUND TO BE BROKEN A FEW INCHES INSIDE THE OUTER HOU	SING JUST AFT OF THE FUEL SERVO. THERE IS NO TIME/LIFE LIMIT ON THESE CABLES, HOWEVER THE OPERATOR WILL NOW CHANGE THE C	ABLES DURING EACH ENGINE CHANGE.		1	L	7	1 	3O	3	O		2A13    	1E10				 
2008013100295	20080131	00295	NE  	2008	1	31	2008FA0000058    	2	20080123	G	7200	0319008000	ENGINE          			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIUS2F    	60010	NE  						MAKING METAL    	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	01	146CB	173  	169  			1407	34481			ON 10, OCT. 2007 THE PILOT REPORTED THE ENGINE CHIP WARNING LAMP ILLUMINATED.  THE AIRCRAFT WAS LANDED WITHOUT INCIDENT.	  THIS WAS THE FOURTH OCCURRENCE IN 10.9 HOURS.  THE ENGINE WAS REMOVED AND RETURNED TO MFG FOR EVALUATION AND REPAIR.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008013100303	20080131	00303	EA  	2008	1	31	2008FA0000062    	2	20080102	G	7314	2B664	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUEL SYSTEM	INOPERATIVE     	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			SO	05	202TC		2098 			318152037				ON 1/2/2008 THE PILOT WAS DEPARTING WHEN HE REPORTED THAT HE LOST SUBSTANTIAL POWER TO THE LT ENGINE JUST AFTER TAKEOFF 	AND THE LT LOW PRESSURE FUEL BOOST PUMP LIGHT ON THE AC ANNUNCIATOR PANEL ILLUMINATED.  PILOT LANDED AT AIRPORT AND CALL	ED AC TECH.  AIRCRAFT TECH ON LOCATION COULD NOT FIND ANY PROBLEMS WITH THE ENGINE DURING RUN UP OTHER THAN THE ELECTRIC	 LOW PRESSURE FUEL BOOST PUMP NOT SUPPLYING RATED PRESSURE.  THE ELECTRIC IN-LINE LOW PRESSURE BOOST PUMP IS INTENDED FO	R FLIGHT ABOVE 15,000 FT MSL AND CAN BE DEFERRED IAW PART 91 MEL.  AC WENT TO DEPART AIRPORT AND THE LT ENGINE LOST POWE	R AGAIN DURING THE TAKEOFF ROLL AT ABOUT 40 KNOTS OF AIRSPEED.  TROUBLESHOOTING OF ENGINE FUEL PUMP, FUEL NOZZLES REVEAL	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2008021200259	20080212	00259	CE  	2008	2	12	2008FA0000063    	1	20080116	G	3060	4E11883	BOOT            			BEECH 	60    	A60         	1153604	CE  	LYC   	O541  	TIO541*     	41536	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  	PROPELLER	DEBONDED        	B			PZ4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	4445W	4    				P245		DA684		PROP WAS SENT FOR REPAIRS CONSISTING OF FLUSH AND RESEAL OF PROP, PAINTING OF BLADES AND INSTALLATION OF NEW DEICE BOOTS	.  AC HAS FLOWN 3.5 HRS AND THREW A DEICE BOOT, DENTED THE RT NOSE SECTION OF THE AC.  SPEAKING WITH SERVICE REP, HE STA	TED THAT THE GLUE USED TO ADHERE THE BOOT HAD FAILED AFTER REVIEWING PHOTOS SENT TO HIM.  IF THIS IS THE CASE, A RECOMME	NDATION OF FINDING OUT LOT NUMBER OF ADHESIVE, AND RECALLING ANY WORK DONE USING THIS LOT NUMBER.  (K)			1	L	7	2 	3O	3	O		A12CE   	E10EA	5	C	P31EA	 
2008013100289	20080131	00289	CE  	2008	1	31	2008FA0000066    	1	20080122	G	3411		FITTING         			CESSNA	206   	T206H       	2073303	CE  	LYC   	O360  	O360E1A6D   	42305	EA  					STATIC SYS	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	2095S					T20608442				PRIOR TO COMPLIANCE WITH FAR 91.411, A STATIC SYSTEM CHECK WAS CONDUCTED. UNDER TEST SYSTEM SHOWED APPROXIMATELY 100 FPM	 DESCENT RATE. INSPECTION REVEALED THE 90 DEGREE PLASTIC FITTINGS (ONE ON EACH SIDE OF THE FORWARD FUSELAGE) FOR STATIC 	SYSTEM PLUMBING WERE MADE OF MOLDED PLASTIC AND INCLUDED A TINY RIDGE (MOLD LINE) ALONG THE THREADED AREA. ADDITIONALLY 	MFG INSTALLED THE PART WITHOUT THE USE OF PIPE SEALING COMPOUND MAKING AT LEAST PARTIAL FAILURE INEVITABLE.			1	H	7	1 	3O	3	O	RT	A4CE    	E286				 
2008020400106	20080204	00106		2008	2	4	2008FA0000068    	1	20080130	G	6500	538715	SHAFT           																	TAIL ROTOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										ONE PIECE TRANSVERSE CRACK AROUND THE AREA OF PART THAT HAD LONGITUDINAL INDICATIONS (ORIGIN UNKNOWN BUT POSSIBLY RELATE	D TO STRESS, FATIGUE OR WEAR), OTHER 4 PIECES ONLY WITH THE SAME LONGITUDINAL INDICATIONS.																		 
2008020400108	20080204	00108	EU  	2008	2	4	2008FA0000069    	1	20080123	G	5510	T700A5510065000	HINGE           			SOCATA	TBM   	TBM700      	8682000	EU  										STABILIZER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	800GS	857  	100  			149				HINGE FOUND CRACKED IN AREA OF CONCERN IDENTIFIED IN AD 99-07-11, PREVIOUS INSPECTION 100 HOURS EARLIER SHOWED NO SIGN O	F CRACKING.					1	L	7	1 	3T			RT	A60EU   					 
2008020400102	20080204	00102	EU  	2008	2	4	2008FA0000070    	1	20080131	G	5280	D605287300	HINGE           			DIAMON	DA42  	DA42        	2990004	EU  										MLG DOOR	BROKEN          	B			N3XR	O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			SO	15	902ER	195  	95   			42278				DURING FLIGHT WHEN THE LANDING GEAR WAS OPERATED, THERE WAS A NOISE HEARD BY THE CREW. UPON LANDING THE LT MAIN LANDING 	GEAR DOOR WAS ATTACHED ONLY BY THE LOWER DOOR CONTROL LINK. THE REAR GEAR DOOR HINGE, AFT BRACKET HAD BROKEN AT THE WELD	 OF THE PIECE BOLTED TO THE WING STRUCTURE. THE DOOR HAD FALLEN LOW ENOUGH TO WHERE THE FORWARD CORNER WAS WORN AWAY BY 	CONTACT WITH THE GROUND. THIS OPERATOR OPERATES A FLEET OF 9 DA42 AIRCRAFT. ON INITIAL INSPECTION MANY OF THE OTHER AIRC	RAFT HAD CRACKS DEVELOPING AT THE POINT OF FRACTURE OF THE DAMAGED AIRCRAFT. ALL OF THE HINGE POINTS ON ALL OF THE AIRCR	AFT WILL BE CHANGED.	1	L	7	2 	3I			RT	A57CE   					 
2008021200038	20080212	00038	NM  	2008	2	12	2008FA0000071    	1	20080204	G	5220		LANYARD         			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   	      	CFE73811B   	 	NE  					EMERGENCY WINDOW	MISSING         	B			CWQD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	275QS					75				ACCESS COVER FOR THE EMERGENCY WINDOW HANDLE DOES NOT HAVE A LANYARD WHEN IT IS REMOVED.  THE COVER HANGS BY THE WIRING 	THAT ILLUMINATES IT PUTTING STRESS ON THE SOLDERED CONNECTIONS TO BREAK CAUSING EITHER AN INOPERATIVE EMERGENCY LIGHT OR	 A SHORT CAUSING MORE THAN ONE EMERGENCY LIGHT TO NOT ILLUMINATE.  THIS COVER IS REMOVED ROUTINELY FOR SECURITY PINNING 	OF THE EXIT HANDLE AND FOR EMERGENCY WINDOW HANDLE INSPECTION.  THERE SHOULD BE A LANYARD TO PROVIDE STRESS RELIEF FOR T	HE ASSOCIATED WIRING MOUNTED ON THE COVER AND IN THE WINDOW ASSY.  (K)		2	L	7	2 	4F	4	F	RT	A50NM   	E44NE				 
2008021200037	20080212	00037	NE  	2008	2	12	2008FA0000072    	2	20080111	G	7250	1808M15G03	SUPPORT         	CFMINT      		AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565B42P  	13013	NE  					HPT NOZZLE	ERODED          	B			QEMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35					51X79408		779408			DURING DISASSEMBLY OF THE CORE MAJOR MODULE, REMOVED FROM ESN 779408, REMOVAL OF THE COMBUSTION LINER MODULE EXPOSED THE	 FWD INNER NOZZLE MODULE EXPOSED THE FORWARD INNER NOZZLE SUPPORT (FINS).  IT WAS NOTED THAT THE FINS HAD 1-OFF AREA OF 	LOCALIZED EROSION WHICH HAD RESULTED IN PENETRATION OF THE COMPONENT.  THE EROSION WAS LOCATED ON THE SUPPORT BODY SECTI	ON OF THE COMPONENT, JUST AFT OF THE FWD FLANGE AND ADJACENT TO THE NR 22 AND 23 BOLT HOLES (CLOCKWISE FROM TDC, ALF) TH	E CAUSE OF THE EROSION IS UNKNOWN.  CIRCUMFERENTIAL EROSION TO THE SUPPORT BODY OF THE FINS IS COMMON BUT LOCALIZED EROS	ION, AS SEEN IN THIS INSTANCE HAS NOT BEEN SEEN PREVIOUSLY.  ALL AFFECTED PARTS ARE SCHEDULED FOR RETURN TO MFG FOR FAIL	2	L	7	2 	4F	4	F	RT	A46NM   					 
2008021200035	20080212	00035	SO  	2008	2	12	2008FA0000073    	1	20080114	G	5341	62448003	ATTACH FITTING  			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	44542					287415662				THIS FUSELAGE REAR WING ATTACH FITTING WAS BEING REPLACED DUE TO CORROSION PITTS ON FRONT SURFACE.  UPON REMOVAL SOME SE	VERE PITTING WAS NOTED JUST IB OF THE .3125 INCH WING ATTACH BOLT HOLE ON THE REAR SIDE OF THE FITTING.  THIS AREA IS EX	POSED TO OUTSIDE AIR AND MOISTURE AND IS LOCATED IN A DIFFICULT AREA TO INSPECT.  THIS ARA IS ALSO MORE CRITICAL IN RELA	TION EVENTUAL PART FAILURE THAN THE FRONT SURFACE THAT IS VISIBLE FROM INSIDE THE FUSELAGE.  RECOMMEND CLEANING DIRT OUT	 OF AREA AND INSPECTING WITH A GOOD LIGHT.  (K)		1	L	7	1 	3O	3	O		2A13    	E274				 
2008021200032	20080212	00032	SO  	2008	2	12	2008FA0000074    	2	20080115	G	8530	AEC642068	CYLINDER        			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	NR 1	DAMAGED         	B			MS2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	1928X	247  				18256028	288449R	822386		WHILE PERFORMING A COMPRESSION CHECK TO FIND AN OIL LEAK, FOUND NR 1 CYLINDER WITH O COMPRESSION.  PULLED CYLINDER OFF A	ND FOUND THE PLATING ON THE CYLINDER LOOSE AND FLAKING OFF.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2008022000026	20080220	00026	SO  	2008	2	20	2008FA0000077    	2	20080207	G	7414	6310	CAM             			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					MAGNETO	WORN            	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			WP	27	878JM	444  	444  			TH2065	690181AND6			100 RPM MAGNETO DROP ON PRE-FLIGHT RUN-UP.  INSPECTED ALL (4) MAGNETOS ON BOTH ENGINES.  FOUND ALL MAGNETO CAMS WORN.  N	O LUBRICATION WAS FOUND ON THE CAMS. THESE MAGNETOS HAD 444.0 HRS TIME SINCE NEW, AND HAD COME INSTALLED ON NEW ENGINES.	 THEY HAD NOT HAD THEIR FIRST 500 HR INSPECTION, SO HAD NEVER BEEN INSPECTED/OPENED SINCE NEW.  MAGNETOS, SN'S: 06121306	, 06121346, 06120367, AND 06121304.			1	L	7	2 	3O	3	O		3A16    	E3SO				 
2008031700256	20080317	00256	EU  	2008	3	17	2008FA0000078    	1	20080125	G	2910	GCH1004	HYDRAULIC SYSTEM			UROCOP	EC120 	EC120B      	8680987	EU  											CONTAMINATED    	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			WP	28	179CB	555  	55   			1412				HYD POWER PACK PRE-CLOGGING INDICATOR IS DISPLAYED BEFORE FLIGHT.						1	G	7	2 	3U			NC	R0001RD 					 
2008031900262	20080319	00262	CE  	2008	3	19	2008FA0000082    	1	20080218	G	3397		CAPACITOR       			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	CABIN LIGHTS	BURNED          	E				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SO	14	662JS					LW176				AT CRUISE FL 150, CREW NOTICED SMOKE AND ELECTRICAL ODOR COMING FROM SIDEWALL UNDERNEATH EMERGENCY EXIT.  PIC DECLARED E	MERGENCY AND LANDED AC WITHOUT FURTHER INCIDENT.  UPON INSP OF  SIDEWALL UNDER EMERGENCY EXIT, IT WAS NOTICED THAT A SMA	LL HOLE WHICH APPEARED TO LOOK LIKE A CIGARETTE BURN AT FIRST HAD PENETRATED THROUGH HONEYCOMB MATERIAL AND THE ULTRA SU	EDE LINER THAT COVERS THE SIDEWALL.  UPON CLOSER INSP BEHIND SIDEWALL, NO ELECTRICAL COMPONENTS OR WIRING ARE LOCATED BE	HIND THE AREA WHERE THE HOLE IS LOCATED.  AFTER REMOVING THE VALANCE PANEL ON THE EMERGENCY EXIT WINDOW, IT WAS NOTICED 	THAT THE CAPACITOR AND THE DIODE FOR THE INDIRECT LIGHTING POWER SUPPLY WAS BURNED.	1	L	7	2 	3T	3	T		3A20    	E2NE	6	C	3PNE	 
2008040300040	20080403	00040	CE  	2008	4	3	2008FA0000084    	1	20080221	G	2910	1285094	LINE            			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					HYDRAULIC SYS	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	761AV	4400 				21062110				REPLACED HYDRAULIC TUBE 128509-4 DUE TO CHAFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE.  THIS WAS F	OUND BY INSPECTION AS DESCRIBED IN MFG SEB07-03 AND WHICH HAVE A SUPERSEDED PN AVAILABLE TO NULLIFY THE POTENTIAL PROBLE	M.  THIS SERIES AND OTHER MODELS SHOULD BE ADDED TO SERVICE BULLETIN APPLICABILITY.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
2008022500004	20080225	00004	CE  	2008	2	25	2008FA0000085    	1	20080221	G	2910	1285094	LINE            			CESSNA	210   	T210M       	2073451	CE  										HYDRAULIC SYS	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	761AV	4400 				21062110				REPLACED HYDRAULIC TUBE (PN 128509-4) DUE TO CHAFFING FROM LONG SCREW IN WRONG LOCATION OF INSPECTION COVER PLATE.  THIS	 WAS FOUND BY INSPECTION AS DESCRIBED IN SEB07-03 FOR 182 SERIES, AND WHICH 182'S HAVE A SUPERSEDED PN AVAILABLE TO NULL	IFY THE POTENTIAL PROBLEM.  THIS SERIES AND OTHER MODELS SHOULD BE ADDED TO SB APPLICABILITY.				1	H	7	1 	3O				3A21    					 
2008022500005	20080225	00005	CE  	2008	2	25	2008FA0000086    	1	20080215	G	5711	0411129	SPAR            			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200*       	17020	SO  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		3895 				15065116				WINGS WERE PREVIOUSLY REMOVED TO FACILITATE TRANSPORTATION. INSP OF THE LT AND RT FWD SPAR BEARING BLOCKS IN THE FUSELAG	E (P/N 0411129) FOUND SEVERE CORROSION DAMAGE. IT APPEARS TO BE DISSIMILAR METAL CORROSION BETWEEN THE SPAR BLOCKS AND T	HE AN3-21A ATTACHMENT BOLTS. THIS AREA WOULD BE VERY DIFFICULT TO INSPECT WITH THE WINGS ATTACHED. THE SAME P/N AND WING	 ATTACHMENT SYS IS USED ON MOST OF THE AC SERIES HIGH WING AIRCRAFT.			1	H	7	1 	3O	3	O		3A19    	E252				 
2008040300022	20080403	00022	CE  	2008	4	3	2008FA0000087    	1	20080215	G	5311	0411129	SPAR            			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200*       	17020	SO  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3816J	3895 				15065116				WINGS WERE PREVIOUSLY REMOVED TO FACILITATE TRANSPORTATION. INSPECTION OF THE LT AND RT FWD SPAR BEARING BLOCKS IN THE F	USELAGE (P/N 0411129) FOUND SEVERE CORROSION DAMAGE. IT APPEARS TO BE DISSIMILAR METAL CORROSION BETWEEN THE SPAR BLOCKS	 AND THE AN3-21A ATTACHMENT BOLTS. THIS AREA WOULD BE VERY DIFFICULT TO INSPECT WITH THE WINGS ATTACHED.				1	H	7	1 	3O	3	O		3A19    	E252				 
2008040200041	20080402	00041	SO  	2008	4	2	2008FA0000088    	2	20080207	G	7414	6310	CAM             			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					MAGNETO	WORN            	B				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			WP	27	878JM	444  	444  			TH2065	690181AND6			100 RPM MAGNETO DROP ON PRE-FLIGHT RUN-UP.  INSPECTED ALL FOUR MAGNETOS ON BOTH ENGINES.FOUND ALL MAGNETO CAMS WORN. NO	 LUBRICATION WAS FOUND ON THE CAMS. THESE MAGNETOS HAD 444.0 HRS TIME SINCE NEW, AND HAD COME INSTALLED ON NEW ENGINES. 	THEY HAD NOT HAD THEIR FIRST 500 HR INSPECTION, SO HAD NEVER BEEN INSPECTED/OPENED SINCE NEW.  SLICK 6310 MAGNETOS, SN'S	: 06121306, 06121346, 06120367, AND 06121304.			1	L	7	2 	3O	3	O		3A16    	E3SO				 
2008031000330	20080310	00330	CE  	2008	3	10	2008FA0000089    	1	20080129	G	2915	7629001004001	PRESSURE SWITCH 			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					HYDRAULIC SYS	FAILED          	B			WMYR	A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	444MW	2127 				131				LT HYDRAULIC PRESSURE SWITCH (S9) FAILED IN FLIGHT, RESULTING IN LOSS OF HYDRAULIC FLUID AND FAILURE OF BOTH LT AND RT H	YDRAULIC PUMPS.  NECESSITATED A FLIGHT DIVERSION TO AN ALTERNATE AIRPORT WITH AN EMERGENCY DECLARATION.  (K)					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2008031000332	20080310	00332	CE  	2008	3	10	2008FA0000091    	1	20080122	G	3245		TUBE            			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					LANDING GEAR	FAILED          	B			AW4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	784WW					17280816				FROM SEPT 7 TO PRESENT, AC HAS EXPERIENCED (3) LANDING GEAR TIRE TUBE FAILURES.  FAILURES ALL OCCURRED IN THE SIDEWALL O	F THE TUBES.  THERE WAS NO EVIDENCE OF THE TUBES BEING PINCHED OR OTHERWISE DAMAGED DURING INSTALLATION.  DAMAGE RANGED 	FROM SMALL (.1250 INCH) SPLITS TO A LARGE (.5 INCH) SPLIT.  EXAMINATION OF THE TUBE SIDEWALLS EVIDENCED WHAT APPEAR TO B	E SOME FORM OF (WEATHER CHECKING) THAT NORMALLY APPEARS ON OLD RUBBER COMPONENTS.  ALL TUBES WERE OF RECENT MANUFACTURE.	  ONE FAILURE OCCURRED ON A G15/6.00/6 TUBE (PN 302-246-401) WITH TT OF 123 HOURS.  (2) FAILURES OCCURRED ON 5.00 X 5 TU	BES (PN 302-013-400 AT 125 HOURS AND 112 HOUR RESPECTIVELY.  TUBES WERE FORWARDED TO MFG FOR EVALUATION.  EVALUATION IS 	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008031000333	20080310	00333		2008	3	10	2008FA0000092    	4	20080111	G	2564	100102303	LIFE RAFT       																	CABIN	UNWANTED DEPLOY 	D			JAVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	61										LIFE RAFT STARTED TO INFLATE WHILE PLACING ON AIRCRAFT WITH NORMAL HANDLING.  LIFE RAFT WAS IMMEDIATELY REMOVED AND HELD	 FOR VENDOR PICK-UP.  NOTE:  LIFE RAFT WAS A LOANER , OVERHAULED ON 7/26/07.  LIFE RAFT WAS RECEIVED AND INSPECTED ON 1/	11/2008 WITH NO DAMAGE NOTED.  (K)																	 
2008033100041	20080331	00041	GL  	2008	3	31	2008FA0000093    	3	20080204	G	6114		HUB             			CESSNA	188   	A188B       	2073005	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	731VX					18803200T		775315		PROPELLER HUB CRACKED.  (K)						1	L	7	1 	3O	3	O		A9CE    	E5CE	5	C	P3EA	 
2008031000334	20080310	00334	GL  	2008	3	10	2008FA0000094    	3	20080204	G	6114		HUB             	MCAULY      		CESSNA	337   	M337B       	2075708	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER	CRACKED         	D			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	373AZ				661450	337M0079				RELEVENT INDICATION (CRACKED).  (K)						1	H	7	2 	3O	3	O	RT	A6CE    	E1CE	5	C	P5EA	 
2008031000335	20080310	00335	GL  	2008	3	10	2008FA0000095    	3	20080204	G	6114		HUB             	MCAULY      		CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520*    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CRACKED         	D			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	95RG				779643	402B0538				RELEVENT INDICATION (CRACKED 2 PLACES).  (K)						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2008031000336	20080310	00336	SO  	2008	3	10	2008FA0000096    	1	20080128	G	5343	86282010	SPAR            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	856ND					4495001				THE SPAR ASSY WAS CRACKED AT THE LT SIDE NOSE GEAR SUPPORT FITTING.  THE CRACK RADIATED OUT FROM THE AFT LOWER BOLT ATTA	CHMENT ( AS VIEWED FROM  BELOW THE NOSE STRUCTURE FLOORING) ONCE THE A-FRAME SUPPORT WAS REMOVED, THERE WAS A (2 INCH) C	RACK IN THE SPAR WEB (NOT VISIBLE UNTIL THE SUPPORT WAS REMOVED).  THE LOWER EXTRUSION HAS BEEN REPLACED WITH NEW AT SOM	E POINT IN THE AIRPLANES HISTORY (NOT AT THIS SHOP).  THE EXTRUSION CRACKING WAS THE REASON FOR DISASSEMBLY AT THIS TIME	.  THIS IS ADDRESSED IN AD 81-10-01 BUT THE AD IS NOT APPLICABLE TO THIS SERIAL NUMBER AIRCRAFT.  SB NR 1143 COVERS THE 	LATER SN AC.  (K)	1	L	7	2 	3O	3	O		A19S0   	E286				 
2008031000346	20080310	00346	GL  	2008	3	10	2008FA0000099    	2	20080131	G	7230	23074076	SCROLL          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					COMPRESSOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	31PB	1082 				53569	CAC45245			COMPRESSOR (PN 23065593 SN CAC45245) WAS RECEIVED INTO THE SHOP FOR REMOVAL AND REPLACEMENT OF THE SCROLL (PN 23074076(B	) SN 40353) FOR A VISIBLE OPEN HOLE OR BROKEN OFF HEX EXTERNAL BOSS LOCATING PIN AT THE TURNING VANE LOCATION ON THE SCR	OLL.  THE OPERATOR CONDUCTS PATROLLING OR POLICE ACTIVITY USING THE AC AND FOUND THE DEFECT WHILE PERFORMING A 100 HR MA	INT TASK.  THE AFFECTED COMPRESSOR SCROLL WAS COATED WITH SERVETEL WHICH IS AN OEM APPROVED COATING FOR PROTECTION AGAIN	ST CORROSION AND AS INDIDCATED IN THE LOG BOOKS, THIS IS THE 2ND SCROLL TO HAVE BEEN REPLACED.  (K)		1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2008032400430	20080324	00430	CE  	2008	3	24	2008FA0000100    	1	20080205	G	2915	7629001004001	PRESSURE SWITCH 			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					HYDRAULIC SYSTEM	FAILED          	D				A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			SO	09	444MW					131				APPROXIMATELY 40 MIN IN TO PLANNED FLIGHT, WHILE AT FL410, IN FINAL CRUISE CONDITION, A WHITE ADVISORY CAS MESSAGE APPEA	RED INDICATING (MAIN HYD QTY LOW).  FLIGHT CREW OPENED THE APPROPRIATE CREW CHECKLIST AND FLIGHT MANUAL AND REFERENCED T	HE CHECKLIST WHICH SAID (MAIN HYDRAULIC QUANTITY IS LOW), WITH NO ACTION REQUIRED.  THE PF DIRECTED THE PNF TO REFER TO 	ANY ABNORMAL PROCEDURES OR ANY EMERGENCY CHECKLIST PAGE PROCEDURES AS A PRECAUTION FOR LOSS OF HYDRAULIC QUANTITY OR PRE	SSURE.  THE CREW REVIEWED THESE PROCEDURES AND CONTINUED IN CRUISE.  APPROX 15 MIN LATER, DURING DESCENT, A WHITE (L HYD	 PUMP LO) CAS MESSAGE BEGAN TO APPEAR INTERMITTENTLY, AND HYD PRESSURE FLUCTUATIONS WERE NOTED ON THE PRESSURE INDICATIO	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2008031900295	20080319	00295		2008	3	19	2008FA0000101    	4	20080108	G	2210	238006679	YAW DAMPER      			LEAR  	24    	24          	5170302	CE  											FAULTY          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	01	989TL					160				THIS PART FAILED TO OPERATE DURING FIRST FLIGHT, AFTER INSTALLATION, AT CRUISE.						2	L	7	2 	4J				A10CE   					 
2008040300055	20080403	00055		2008	4	3	2008FA0000104    	4	20080224	G	3197		WIRE HARNESS    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					INSTRUMENT PANEL	BURNED          	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CE	07	227BH	6    				172S10662				WIRING HARNESS BEHIND AUDIO PANEL WAS CHAFING ON BRACKET THAT HELPS SUPPORT STANDBY BATTERY ON THE PFD SIDE AND CAUSED W	IRING TO ARC AND BURN (NOTE: HARNESS IS FOR LIGHT DIMMING OF G-1000). FOUND HARNESS PULLED HARD AGAINST BRACKET.  THIS C	AUSED THE WIRE TO CHAFE THROUGH THE INSTALLATION AND SHORT OUT. HOWEVER, CIRCUIT BREAKERS AND TRANSISTORS FOR THE LIGHT 	DIMMING CIRCUIT DID AT NO TIME POP OR FAIL AND WOULD EXPECT TO HAPPEN WHEN THEIR IS A HARD SHORT SINCE THE WIRES ARE ASS	OCIATED WITH THE LIGHT DIMMING CIRCUIT. THE HARNESS WAS PULLED HARD AGAINST THE STRUCTURE AS TO CHAFE THROUGH THE INSULA	TION AND ARC/SCORCHED THE STRUCTURE. THE WIRE BURNED THROUGH AND ALSO, DAMAGED OTHER WIRES IN THE HARNESS. HARNESS WAS A	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008033100043	20080331	00043	CE  	2008	3	31	2008FA0000106    	1	20080211	G	5340		BRACKET         			CESSNA	500   	550         	2076604	CE  										VOLT REGULATOR	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	554MB					5500040				LT GENERATOR VOLTAGE REGULATOR MOUNT BRACKET FOUND TO HAVE CORROSION AT MOUNT SURFACE.  ELECTRICAL GROUND PATH AFFECTED.	  CORROSION REMOVED ALLOWING GOOD GROUND AND ABLE TO ADJUST VOLTAGE REGULATOR, TO SPEC.					1	L	7	2 	4F				A22CE   					 
2008033100044	20080331	00044	CE  	2008	3	31	2008FA0000107    	1	20080209	G	2910	98811241	POWERPACK       			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					HYD SYSTEM	WORN            	C				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			SW	17	127TC	3309 				21063381				SMOKE IN COCKPIT, GEAR NOT FULLY RETRACTED, EXTENDED OK.  FOUND HYDRAULIC POWERPACK MOTOR (ORIGINAL) WORNOUT.  REMOVED A	ND REPLACED WITH O/H UNIT.  OPS, OK.					1	H	7	1 	3O	3	O		3A21    	E8CE				 
2008033100045	20080331	00045	SW  	2008	3	31	2008FA0000108    	1	20080227	G	2841	5643860	GAUGE           			MOONEY	M20   	M20D        	5870210	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUEL SYSTEM	INACCURATE      	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			GL	15	6608U	5103 				103	L533036	CH26709E		FUEL GAUGE INDICATION IS APPROX 2.5 TO 3 GAL HIGHER THAN WHAT IS IN THE TANK.  (K)						1	L	7	1 	3O	3	O		2A3     	E286	5	C	P920	 
2008033100048	20080331	00048		2008	3	31	2008FA0000110    	4	20080215	G	2312		ANTENNA         			ISRAEL	1125  	ASTRASPX    	4500205	EU  										VHF SYSTEM	GOUGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	411MM					080				FOLLOWING REMOVAL OF SATCOM ANTENNA FROM UPPER FUSELAGE FOR INSPECTION, NOTICED FOOTPRINT OF PREVIOUSLY REMOVED NR 1 VHF	 ANTENNA.  UPON INSPECTION OF VHF ANTENNA FOOTPRINT, FOUND NUMEROUS APPARENT MECHANIC INDUCED GOUGES ON FUSELAGE OUTER S	KIN.  DAMAGE WAS APPARENTLY CAUSED BY IMPROPER REMOVAL OF PREVIOUSLY INSTALLED VHF ANTENNA.  REPAIR WAS TO BLEND OUT GOU	GES IAW DER EVALUATION.  (K)			2	L	7	2 	4F			RT	A16NM   					 
2008032500033	20080325	00033	GL  	2008	3	25	2008FA0000111    	1	20080304	G	6420	ECD00213	BEARING         			ENSTRM	F28   	280FX       	3300506	GL  	LYC   	O360  	HIO360F1AD  	41514	EA  					TAIL ROTOR	SEIZED          	D				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NM	03	285SH	1    				2120				THE THRUST BEARINGS IN THE TAIL ROTOR BLADE GRIPS ARE OF MATCHED SETS. THESE SETS HAVE A SPECIFIC INSTALLATION ORIENTATI	ON. ORIENTATION OF THESE BEARINGS ARE MARKED WITH A (V). THE (V) IS TO BE ORIENTED TOWARD THE CENTER OF THE TAIL ROTOR S	PINDLE HUB. ON THESE SPECIFIC BEARINGS THE (V) WAS MARKED POINTING THE WRONG DIRECTION LEADING TO A REVERSED INSTALLATIO	N CAUSING A SEIZURE OF THE BEARINGS. ALL BEARINGS WERE INSTALLED IN ACCORDANCE WITH ENSTROM SERVICE LETTER 133 DATED JUN	E 8, 1987 , SERVICE LETTER 153 DATED FEBRUARY 15, 2002 AND ENSTROM F SERIES MAINTENANCE MANUALS REVISION 1 DATED 4-3-86 	AND REVISION 2 DATED 11-18-88.	1	G	7	1 	3O	3	O		H1CE    	1E10				 
2008031700264	20080317	00264	EU  	2008	3	17	2008FA0000114    	1	20080129	G	2435	160SG140Q1XL	STARTER GEN     			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIUS2F    	60010	NE  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	28	179CB	558  	58   			1412				STARTER/GENERATOR FAILED TO ENERGIZE.						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008033100052	20080331	00052		2008	3	31	2008FA0000115    	4	20080118	G	6113	C2365	BULKHEAD        	SNSNCH      		MAULE 	MX7   	MXT7160     	5470204	SO  	LYC   	O320  	O320*       	41508	EA  	SNSNCH	74D	74DM        	EA  	PROP SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	57HS	3600 				17005C	RL1318639A	A57306		THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT MOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION.  (K)						1	H	7	1 	3O	3	O		3A23    	E274	5	N	P88614	 
2008033100053	20080331	00053		2008	3	31	2008FA0000116    	4	20080118	G	6113	C2367	BULKHEAD        	SNSNCH      		MAULE 	MX7   	MXT7180A    	5460187	SO  	LYC   	O360  	O360C4F     	42290	EA  	SNSNCH	76E	76EM8       	EA  	PROP SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	114HS	300  				21092C	L4051336A	37618K		THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION.  (K)						1	H	7	1 	3O	3	O	NC	3A23    	E286	5	N	P4EA	 
2008033100054	20080331	00054		2008	3	31	2008FA0000117    	4	20080118	G	6113	C2367	BULKHEAD        	SNSNCH      		MAULE 	MX7   	MXT7180A    	5460187	SO  	LYC   	O360  	O360C4F     	42290	EA  	SNSNCH	76E	76EM8       	EA  	PROP SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	171HS	200  				21096C	L4089636A			THE FWD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION. (K)						1	H	7	1 	3O	3	O	NC	3A23    	E286	5	N	P4EA	 
2008033100056	20080331	00056		2008	3	31	2008FA0000118    	4	20080118	G	6113	C2367	BULKHEAD        			MAULE 	MX7   	MXT7180A    	5460187	SO  	LYC   	O360  	O360C4F     	42290	EA  	SNSNCH	76E	76EM8S5     	EA  	FWD SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	125HS	200  				21093C	L4056636A	37939K		THE FWD BULKHEAD CRACKED THROUGHT THE MOUNT BOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION.  (K)						1	H	7	1 	3O	3	O	NC	3A23    	E286	5	N	P4EA	 
2008033100057	20080331	00057		2008	3	31	2008FA0000119    	4	20080118	G	6113	C2367	BULKHEAD        	SNSNCH      		MAULE 	MX7   	MXT7180A    	5460187	SO  	LYC   	O360  	O360C4F     	42290	EA  	SNSNCH	76E	76EM8       	EA  	PROP SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	152HS	200  				21095C	L4081336E	38281K		THE FORWARD BULKHEAD CRACKED THROUGH THE MOUNT BOLT HOLES.  THIS HAS OCCURED SEVERAL TIMES, WARRANTS ACTION.  (K)						1	H	7	1 	3O	3	O	NC	3A23    	E286	5	N	P4EA	 
2008033100059	20080331	00059	GL  	2008	3	31	2008FA0000120    	1	20080206	G	3020		CONTROL ARM     			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					CARB HEAT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	423FP	13   				40FC023				CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA	KE.  RECOMMEND INSTALLIING THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING/HEAT TREATING PROCESS, OR 	DIFFERENT ATTACHMENT PROVISION ALTOGETHER.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2008033100061	20080331	00061	GL  	2008	3	31	2008FA0000121    	1	20080206	G	3020	D4F732612001	CONTROL ARM     			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					CARB HEAT	BROKEN          	D			GO3S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	418FP	31   				40FC018				CARBURETOR HEAT CONTROL ARM BROKE OFF OF CARB AIR BOX CAUSING UNCONTROLLED SELECTION OF CARB HEAT VS RAM (COLD) AIR INTA	KE.  RECOMMEND INSTALLING THICKER MATERIAL ON CARB HEAT CONTROL ARM LEVER, DIFFERENT WELDING/HEAT TREATING PROCESS, OR D	IFFERENT ATTACHMENT PROVISION ALTOGETHER.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2008033100062	20080331	00062	CE  	2008	3	31	2008FA0000122    	1	20080206	G	2197		WIRE HARNESS    			BEECH 	90    	C90A        	1152911	CE  										A/C START CONT	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	4764A					LJ1161				AIR CONDITIONER NOT COOLING.  FOUND WIRING FOR AC START CONTROL PANEL AS WELL AS COMPRESSOR CLUTCH NOT IN PROPER CONFIGU	RATION IAW WIRING PRINT.  AFTER PROPER INSTALLATION OF WIRING AND SUBSEQUENT OPS CHECK, THE MOTOR AND SYS, THE AIR CONDI	TIONER WOULD CYCLE IN AND OUT OF ITS SOFT START CYCLE.  THIS IN TURN CREATED EXCESSIVE HEAT IN THE LOAD RESISTOR CIRCUIT	.  THIS CYCLING CONTINUED UNTIL AT SOME POINT THE SOFT START CIRCUIT FAILED, WHICH CAUSED THE LOAD RESISTOR TO OVERHEAT 	AND MELT THE PHENOLIC BLOCK SHIELDS WHICH CAUGHT  FIRE AND DAMAGED THE IMMEDIATE SURROUNDING STRUCTURE OF THE NOSE COMPA	RTMENT.  PROBABLE CAUSE WOULD INDICATE FAILURE OF THE AC START CONTROL PANEL CIRCUITRY THAT SUBSEQUENTLY LEAD TO A NOSE 	1	L	7	2 	3T			RT	3A20    					 
2008033100063	20080331	00063		2008	3	31	2008FA0000123    	4	20080114	G	6113	05502366	BULKHEAD        			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300*       	17022	SO  					PROP SPINNER	CRACKED         	D			HE8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	4987R	92   				17256341				PROP SPINNER FWD, BULKHEAD CRACKED NEAR MOUNT BOLTS.  PART PROBABLY NOT STURDY.  RECOMMEND PART BE MADE OF THICKER METAL	 DOUBLER INSTALLED.  ALSO, IT APPEARED THAT MOUNT BOLT HOLES MAY BE TOO LARGE.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2008032500068	20080325	00068	SW  	2008	3	25	2008FA0000124    	1	20080114	G	6220	NAS5161A	GREASE FITTING  	BELDEN      		BELL  	212   	212         	1181420	SW  										M/R HUB	BLOCKED         	W			DB5Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33										DURING LUBRICATION OF A MAIN ROTOR HUB, WE DISCOVERED THAT THE SPRING IN THE GREASE FITTING (NAS516-1A) WAS PRESSED OUT 	FROM THE FITTING AND BLOCKED THE GREASE PASSAGE.  THIS HAPPENED (3) TIMES.  WE FOUND THE SPRINGS AFTER EVERY ATTEMPT.  T	HIS COULD RESULT IN A LOOSE SPRING IN A ROTATING BEARING.  (K)				1	G	7	1 	4U				H4SW    					 
2008032500105	20080325	00105	WP  	2008	3	25	2008FA0000125    	2	20080212	G	7210	8937396	GEAR            			CASA  	C212  	C212CC      	2410204	EU  	GARRTT	TPE331	TPE33110R   	0517	WP  					GEAR BOX	BROKEN          	W			X1NY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	961BW	2170 			P5372	248				ENGINE RECEIVED WITH BROKEN FEATHER VALVE, NOSE CONE NUTS LOOSE, ROTATION OF ENGINE ROTATING COMPONENTS FOUND CLUNKY AND	 SEIZED.  MAGNETIC PLUG CONTAMINATED WITH FINE METAL PARTICLES.  NOSE CONE AND DIAPHRAGM REMOVED TO INVESTIGATE CAUSE OF	 FAILURE.  WHEN DIAPHRAGM ASSY WAS REMOVED BIG CHUNKS OF METAL NOTICED AT THE GEARBOX CAVITY IDENTIFIED AS BULL GEAR PIE	CES.  HIGH SPEED PINION GEAR HELICAL TEETH BROKEN OFF AND CRUNCHED.   SEVERAL BULL GEAR TEETH BROKEN OFF.  BIG PIECE (2-	3 INCH) OF GEAR RIM MISSING AND FOUND TRAPPED BETWEEN DIAPHRAGM HOUSING AND SCAVENGE PUMP CAUSING A RUPTURE OF THE PUMP 	HOUSING.  THE PRELIMINARY REASON FOR THE GEAR BOX FAILURE IS BELIEVED TO BE CAUSE BY BULL GEAR FAILURE.  THE SEPARATION 	2	H	7	2 	4T	4	T		A43EU   	E4WE				 
2008032500106	20080325	00106	NE  	2008	3	25	2008FA0000126    	2	20080111	G	7250	1808M15G03	SUPPORT         	CFMINT      		AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565B4P   	 	NE  					HPT NOZZLE	UNSERVICEABLE   	W			QEMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35					51X79408		799408			DURING DISASSY OF THE CORE MAJOR MODULE, REMOVED FROM ESN 779408, REMOVAL OF THE COMBUSTION LINER MODULE EXPOSED THE FWD	 INNER NOZZLE SUPPORT (FINS).  IT WAS NOTED THAT THE FINS HAD 1-OFF AREA OF LOCALIZED EROSION WHICH HAD RESULTED IN PENE	TRATION OF THE COMPONENT.  THE EROSION WAS LOCATED ON THE SUPPORT BODY SECTION OF THE COMPONENT, JUST AFT OF THE FWD (CL	OCKWISE).  THE CAUSE OF THE EROSION IS UNKNOWN.  CIRCUMFERENTIAL EROSION TO THE SUPPORT BODY OF THE FINS IS COMMON BUT L	OCALIZED EROSION, AS SEEN IN THIS INSTANCE HAS NOT BEEN SEEN, PREVIOUSLY.  ALL AFFECTED PARTS ARE SCHEDULED FOR RETURN T	O MFG FOR FAILURE ANALYSIS.  (K)	2	L	7	2 	4F	4	F	RT	A46NM   	E38NE				 
2008033100138	20080331	00138	EU  	2008	3	31	2008FA0000127    	1	20080206	G	2497		WIRE            			AMD   	FALC50	FALCON900   	2730160	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					ELECTRICAL	DAMAGED         	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			NM	09	900VL					60				WHILE TROUBLESHOOTING AC ELECTRICAL OUTLETS FOR BEING INOPERATIVE.  REMOVED FLOOR PANEL TO ACCESS AC INVERTER AND DETECT	ED BURNING PLASTIC.  FOUND SYSTEM HAD SELF RESETTING CIRCUIT BREAKERS INSTALLED THAT HAD BEEN AND WERE CONTINUING TO RES	ET AND ALLOWING THE KAPTON WIRE INSULATION AND SPIRAL WRAP TO BURN.  ONE OF THE AREAS THAT BURNED WAS ONLY 3 INCHES BELO	W A CARBON FLIGHT CONTROL ROD.  THIS HAPPENED ON A VERY LONG FLIGHT, THE OUTCOME COULD HAVE BEEN VERY TRAGIC.  REPLACING	 THES C/B`S WITH NON SELF RESETTING CB WOULD PREVENT THE DAMAGE FROM PROGRESSING TO THE POINT IN WHICH IT DID IN THIS IN	STANCE.  (K)	2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2008033100139	20080331	00139	GL  	2008	3	31	2008FA0000128    	1	20080215	G	2822	51000020	PUMP            			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					FUEL SYS	INOPERATIVE     	D			GO3S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	417FP	102  				40FC017				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				 
2008033100142	20080331	00142	GL  	2008	3	31	2008FA0000131    	1	20080307	G	2822	51000020	PUMP            			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					FUEL SYS	INOPERATIVE     	D			GO3S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	418FP					40FC018				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				 
2008033100143	20080331	00143	GL  	2008	3	31	2008FA0000132    	1	20080227	G	2822	51000020	PUMP            			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	O360A4M     	41514	EA  					FUEL SYS	INOPERATIVE     	D			GO3S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	419FP	265  				40FC019				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 FOR PROPER COOLING OF FUEL PUMP A	ND MOTOR.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E286				 
2008040200040	20080402	00040	CE  	2008	4	2	2008FA0000137    	1	20080123	G	3250	358250549	ARM             			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6*        	52043	EA  					STEERING	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	57SC	6028 				FL34				NOSE GEAR STEERING ARM WORN EXCESSIVELY AT ROD END ATTACHMENT POINT FOR STEERING PUSH PULL TUBE. LOSS OF NOSE GEAR STEER	ING WOULD OCCUR IF ARM WERE TO BREAK. THE ORIGINAL .2500 INCH BOLT HOLE WAS ELONGATED TO A .5 INCH SLOT. THE ARM IS ATTA	CHED TO THE PILOT'S RUDDER PEDAL TORQUE SHAFT AND IS LOCATED IN A SMALL UNPRESSURIZED PANEL AREA BELOW THE PILOT SIDE FL	OORBOARDS. INSPECTIONS ARE OVERLOOKED BECAUSE THIS SEALED PANEL IS NOT OPENED TYPICALLY DURING ROUTINE INSPECTIONS.			2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2008040200013	20080402	00013	CE  	2008	4	2	2008FA0000146    	1	20080129	G	3220	07436051	TORQUE LINK     			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470*       	17026	SO  					ZONE 700	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	82BG	2855 				18255427				ON INSPECTION, A CRACK WAS IDENTIFIED IN THE FORGING FOR THE UPPER TORQUE LINK FOR THE NOSE LANDING GEAR. THE CRACK WAS 	ON BOTH SIDES OF THE BEAM SECTION ADJACENT TO THE EXTENSION STOP FOR THE GEAR.(AFT SIDE)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2008033100175	20080331	00175	EU  	2008	3	31	2008FA0000148    	1	20080327	G	6320	C632A2103101	HOUSING         			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					GEARBOX	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	179CB	622  			M569	1412	34224			INPUT BOX HOUSING BEARING WORN. (SHOULDER)						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008040100109	20080401	00109	EU  	2008	4	1	2008FA0000149    	1	20080227	G	2497		CONNECTOR       			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE1250299  		EU  					FUEL RAIL	ARCED           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	28	4129M	480  				42AC068	020201611			CONNECTOR IS NOT MAKING GOOD CONTACT AND CAUSING ARCING.  PROBABLE CAUSE IS AUTOMOTIVE QUALITY AND NOT OF THE THREADED T	YPE.  TO PREVENT OCCURRENCE RECOMMEND USING AVIATION THREADED TYPE PLUG.  (K)					1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2008040100111	20080401	00111	CE  	2008	4	1	2008FA0000150    	1	20080307	G	2497	S26062	WIRE HARNESS    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	FLAP MOTOR	DETERIORATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	467CM					17280859	L2651551A	TJ040		UPON INSPECTION OF A PHASE II INSPECTION, IT WAS DISCOVERED THAT THE WIRE BUNDLE MOUNT PN S26062 THAT HOLDS THE FLAP MOT	OR WIRE HARNESS HAD DETACHED FROM THE RIB IN THE RT WING AND HAD ALLOWED THE WIRE BUNDLE TO CHAF INTO THE INSPECTION PAN	EL SUPPORT ON THE WING.  THE WIRE BUNDLE HAD (2) WIRES CHAFED THROUGH THE INSULATION AND WAS IN CONTACT WITH THE BARE WI	RE.  RECOMMEND INSPECTION OF THESE MOUNTS AND REPLACE AS NEEDED, OR ON CONDITION.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2008040100121	20080401	00121	EA  	2008	4	1	2008FA0000151    	2	20080305	G	8520	13B2713485	CRANKSHAFT      								LYC   	O360  	O360A4A     	41514	EA  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17										CRANKSHAFT HAS VERY LARGE RADIAL CRACKS AT THE BASE OF THE FORWARD THRUST FACE, EXTENDING APPROX. 85% OF THE WAY AROUND 	THE SHAFT. APPEARS TO HAVE BEEN A FRONTAL IMPACT ON THE CRANKSHAFT DRIVING IT REWARD IN THE ENGINE AND IMPACTING THE CRA	NKCASE.									3	O			E286				 
2008040400001	20080404	00001		2008	4	4	2008FA0000152    	1	20080304	G	4990	38809981	PUMP            																	APU OIL	FAILED          	B				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	99		13599	1468 							2 APUS WERE REPORTED LOP AUTO SHUTDOWN. HAVE RECEIVED APU P-195 AND P-141 FROM FOR THE SAME REASON OF REMOVAL. DISASSEMB	LY OF THE ENGINES REVEALED LP ROLLER BEARING FAILURE. ONE OF THE ENGINE'S BEARING DID NOT HAVE LUBRICATION AT ALL.  THE 	OIL PUMPS P/N 3880998-1 WERE ROUTED TO BENCH TEST AND LOW PERFORMANCE WAS NOTED. DISASSEMBLY OF THE OIL PUMP REVEALED PO	RT PLATE P/N 3603681-1 HAD SIGNIFICANTLY WORN. IT ALLOWED THE PORT PLATE MOVE TO RESTRICT THE OIL INLET PORT AND OUTLET 	PORT AND CAUSED LOW PUMP PERFORMANCE. THE BEARING FAILURE WAS A CONSEQUENCE OF INSUFFICIENT OIL PRESSURE.															 
2008040200043	20080402	00043	CE  	2008	4	2	2008FA0000153    	1	20080212	G	2810		CHAIN           			CESSNA	172   	172S        	2072439	CE  	CONT  	C85   	C8512F      	17008	SO  					FUEL CAP	LOOSE           	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	15	5055Q	4413 				8972				LT FUEL GAUGE INDICATED 10 GAL. IN TANK AT ALL FUEL LEVELS. THE TANK WAS DRAINED AND ACCESS COVER REMOVED. THE FUEL CAP 	RETAINING CHAIN WAS FOUND TO HAVE COME LOOSE ON THE TANK END (S) HOOK AND WRAPPED AROUND THE ARM ON THE FUEL LEVEL SENDI	NG UNIT LOCKING IT AT A 10 GAL. INDICATION.				1	H	7	1 	3O	3	O	NT	3A12    	E233				 
2008040300025	20080403	00025	CE  	2008	4	3	2008FA0000154    	1	20080215	G	5511	45A2111XXXX	RIB             			BEECH 	MU300 	400A        	1155402	CE  										HORIZONTAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	907JE	5335 				RK107				FOUND SEVERAL CRACKS (25) IN RIB TO LOWER SKIN ATTACH FLANGES, AT RIVET HOLES ,  IN 3 LT, AND 4 RT HORIZONTAL STABILIZER	 INNER SPAR RIBS. RIBS NR 234 ON LT SIDE, AND NR 2345 ON RT SIDE. AFFECTED.					2	H	7	2 	4F			RT	A16SW   					 
2008040300026	20080403	00026	CE  	2008	4	3	2008FA0000155    	1	20080215	G	5511	45A2111XXXX	RIB             			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	907JE	5335 				RK107				FOUND SEVERAL CRACKS (25) IN RIB TO LOWER SKIN ATTACH FLANGES, AT RIVET HOLES ,  IN 3 LT , AND 4 RT HORIZONTAL STABILIZE	R INNER SPAR RIBS. RIBS NR 234 ON LT SIDE, AND NR 2345 ON RT SIDE AFFECTED.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2008040300046	20080403	00046		2008	4	3	2008FA0000156    	4	20080222	G	2564	5A320410312	LIFE RAFT       			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	900KE		1    			052				RECEIVED SUBJECT LIFE RAFT FOR ANNUAL INSPECTION FROM REGISTERED OWNER. THE LIFE RAFT WAS RECEIVED BY THIS REPAIR STATIO	N IN A PACKED CONDITION AND IN ITS "AS-REMOVED" CONDITION FROM THE AIRCRAFT.  DURING DISASSEMBLY AND PRELIMINARY INSPECT	ION OF SUBJECT LIFE RAFT, FOUND A STEEL SAFETY PIN INSTALLED IN THE LIFE RAFT INFLATION BOTTLE. THE LIFE RAFT WOULD NOT 	HAVE BEEN OPERABLE WITH THIS SAFETY PIN INSTALLED HAD THIS LIFE RAFT BEEN CALLED UPON TO FUNCTION IN AN ACTUAL EMERGENCY	.		2	L	7	3 	4F	4	F		A46EU   	E6WE				 
2008040300048	20080403	00048		2008	4	3	2008FA0000157    	4	20080108	G	2210	238006679	YAW DAMPER      			LEAR  	24    	24          	5170302	CE  										ZONE 300	FAULTY          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	01	989TL					160				THIS PART FAILED TO OPERATE DURING FIRST FLIGHT AFTER INSTALLATION AT CRUISE.						2	L	7	2 	4J				A10CE   					 
2008040300049	20080403	00049	SO  	2008	4	3	2008FA0000160    	1	20080225	G	3245	0923150	TUBE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					LT TIRE	CUT             	B				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			GL	21	359ND	118  				2842187				UPON LANDING, LT MAIN TIRE DEFLATED UPON DISASSEMBLY TUBE WAS FOUND TO HAVE A SMALL SLIT IN THE OUTSIDE OF THE CIRCUMFER	ENCE OF THE TUBE. THIS SLIT HAS BEEN FOUND ON NUMEROUS TUBE FAILURES FOUND BY THIS REPAIR STATION. DISCUSSION WITH TUBE 	MFG HAVE BEEN FRUITLESS AS THEY FEEL IT IS A FOLD INDUCED DURING INFLATION BUT THEIR INSTALLATION PROCEDURES HAVE BEEN F	OLLOWED TO THE LETTER AND PROBLEM STILL EXIST DURING EXTREME TEMP CHANGES EXPERIENCED IN OUR CLIMATE (NORTH DAKOTA).			1	L	7	1 	3O	3	O		2A13    	E274				 
2008040300051	20080403	00051	SO  	2008	4	3	2008FA0000161    	1	20080225	G	3245	0923150	TUBE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					LT TIRE	CUT             	B				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			GL	21	359ND	118  				2842187				UPON LANDING, LT MAIN TIRE DEFLATED.   UPON DISASSEMBLY, TUBE WAS FOUND TO HAVE A SMALL SLIT IN THE OUTSIDE OF THE CIRCU	MFERENCE OF THE TUBE.  THIS SLIT HAS BEEN FOUND ON NUMEROUS TUBE FAILURES FOUND BY THIS REPAIR STATION. DISCUSSION WITH 	TUBE MFG HAVE BEEN FRUITLESS AS THEY FEEL IT IS A FOLD INDUCED DURING INFLATION BUT THEIR INSTALLATION PROCEDURES HAVE B	EEN FOLLOWED TO THE LETTER AND PROBLEM STILL EXIST DURING EXTREME TEMP CHANGES EXPERIENCED IN OUR CLIMATE (NORTH DAKOTA)	.		1	L	7	1 	3O	3	O		2A13    	E274				 
2008040300052	20080403	00052	EA  	2008	4	3	2008FA0000164    	2	20080110	G	7414	6393	MAGNETO         			GULSTM	500   	500S        	0141107	SW  	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	100  				3298				ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING OUT OF LIMITS, DISASSEMBLED MAG AND FOUND T	HE CAM WORN OUT . 100.3 HRS SINCE NEW					1	H	7	2 	3O	3	O		6A1     	1E4				 
2008040300054	20080403	00054	EA  	2008	4	3	2008FA0000167    	2	20080226	G	7414	6393	MAGNETO         			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE	WORN            	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			GL	15	51RF	81   				3298				ENGINE WAS GETTING HARD TO START, CHECKED MAG TIMING AND FOUND LT MAG TIMING OUT OF LIMITS, DISASSEMBLED MAG AND FOUND T	HE CAM WORN OUT . 81.1 HRS SINCE NEW.					1	H	7	2 	3O	3	O		6A1     	1E4				 
2008040300056	20080403	00056	SO  	2008	4	3	2008FA0000168    	1	20080226	G	3245	0923080	TUBE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					TIRE	FAILED          	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	21	437ND	28   				2842214				NOSE TIRE FOUND FLAT IN HANGER. DISASSEMBLE FOUND SMALL SLIT IN OUTSIDE CIRCUMFERENCE OF TUBE TYPICAL OF OTHER FLAT TIRE	S FROM SAME MFG.  SAMPLE FAILED TUBES HAVE BEEN RETURNED TO MFG FOR EVALUATION.					1	L	7	1 	3O	3	O		2A13    	E274				 
2008040300061	20080403	00061	CE  	2008	4	3	2008FA0000169    	1	20080220	G	2820	057313K001301	LINE            			CESSNA	172   	172S        	2072439	CE  	THIELT	TAE125	TAE1250299  		EU  					FUEL SYSTEM	CRACKED         	C				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			SO	19	1735L	3    				172S10647	020201880			PILOT WAS FLYING AT 5,500 FEET WHEN THE ENGINE STARTED RUNNING ROUGH. WITHIN MOMENTS THE FADEC (A) LIGHT CAME ON THEN FA	DEC (B) ILLUMINATED. THE PILOT TRIED TO ACTIVATE THE MANUAL OVERRIDE BUT WAS UNABLE TO PUT OUT THE WARNING LIGHTS. THE R	PMS DROPPED UNTIL ENGINE STOPPED, THEN THE PROP STOPPED. THE PILOT DID A GREAT JOB AND FOUND A SAFE ROAD TO LAND ON, AND	 COMMUNICATED WITH ATC THAT HE PLANNED TO MAKE AN EMERGENCY LANDING. WHEN THE PILOT LANDED HE ADVISED ATC THAT HE WAS SA	FE AND DID NOT REQUIRE ANY SERVICES (FIRE, PARAMEDICS). ATC NOTIFIED THE LOCAL SHERIFFS DEPARTMENT AND A DEPUTY WAS SEN	T OUT TO CONFIRM. THE PILOT MOVED THE AC FROM THE ROADWAY TO AVOID DAMAGE OR ANY INCIDENT WITH TRAFFIC. UPON REACHING TH	1	H	7	1 	3O	3	B	NT	3A12    	E00069EN				 
2008040300062	20080403	00062	SO  	2008	4	3	2008FA0000173    	1	20080228	G	3245	0923080	TUBE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					TIRE	FLAT            	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	21	350ND	70   				2842179				ON LANDING, RT MAIN LANDING GEAR TIRE FLAT.  UPON DISASSEMBLY FOUND A SMALL SLIT IN THE OUTSIDE CIRCUMFERENCE OF THE TUB	E.  HAVE FOUND MANY SIMILAR SLITS IN OTHER FAILED TUBES FROM MFG.					1	L	7	1 	3O	3	O		2A13    	E274				 
2008040300064	20080403	00064		2008	4	3	2008FA0000177    	1	20080229	G	6100	5038004811	RELAY           								PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  		BURNED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	964LB									UPON LANDING A POWER/ TORQUE SURGE OF THE LT ENGINE WAS ENCOUNTERED.  THE INCREASED THRUST FROM THE LT SIDE AND ICE COVE	RED RUNWAY CONDITIONS CAUSED AN OFF RUNWAY INCURSION.  INVESTIGATION OF THE GROUND FINE SOLENOID SYSTEM RESULTED IN A BU	RNED K4 RELAY ON THE AFFECTED PC CARD CONTROLLING THE GROUND FINE SYSTEM ON THE LT SIDE.									4	T			E4EA	6	C	P56GL	 
2008040300065	20080403	00065	NM  	2008	4	3	2008FA0000179    	1	20080229	G	5712		RIB             			UNIVAR	415   	415E        	0420308	NM  	CONT  	C85   	C85*        	17008	SO  					RT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	87346					519				COMPLIANCE WITH AD 2002-26-02 DETECT AND CORRECT CORROSION IN WING CENTER SECTION.  FOUND 5 RIVETS CORRODED OFF THE LOWE	R CENTER RIB ON THE RT WING WALKWAY BOX.					1	L	7	1 	3O	3	O		A787    	E233				 
2008040300089	20080403	00089	CE  	2008	4	3	2008FA0000180    	1	20080229	G	3232	65412045	STUD            			CESSNA	501   	501         	2076603	CE  										LT MLG ACTUATOR	BROKEN          	D				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			SO	09	793AA					5010106				LT MLG ACTUATOR TO GEAR STUD BROKEN OFF AT BASE OF THE NUT ON THE TAPER SIDE, NUT AND WASHER SET MISSING AND STUD WAS NO	T TIGHT IN THE GEAR.					1	L	7	2 	4F				A27CE   					 
2008040300091	20080403	00091	SO  	2008	4	3	2008FA0000181    	2	20080304	G	8530	AEC633099	PISTON          			BEECH 	35    	B35         	1151506	CE  	CONT  	E225  	E2258       	17015	SO  					ENGINE	FAILED          	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CE	07						D3633	03593D58			NR 6 PISTON DISINTEGRATED.  CAUSE UNKNOWN.  PISTON P/N AEC633099 WAS ORIGINALLY MANUFACTURED BY AIRMOTIVE ENGINEERING, I	NC.(AEC).  ENGINE COMPONENTS, INC. (ECI) HAS SINCE BOUGHT OUT AEC.  ECI HAS NOT PRODUCED THIS P/N.					1	L	7	1 	3O	3	O		A777    	E267				 
2008040300096	20080403	00096	NE  	2008	4	3	2008FA0000183    	2	20080304	G	7250	304997801	TURBINE         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	185XP	4837 	1771 			BB952	93220			DURING PERFORMANCE OF A SCHEDULED 1800 HOUR HOT SECTION INSPECTION OF THE RT ENGINE, AT 1771 HOURS AND 7 YEARS TIME IN S	ERVICE SINCE OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWAB	LE FOR RETURN TO SERVICE.  IT WAS NOTED THAT THERE WAS SOME METAL BUILD-UP ON THE SHROUD SEGMENTS IN THE 4 O'CLOCK THRU 	6 O'CLOCK POSITIONS.  NO IMPACT DAMAGE WAS NOTED TO ANY OF THE CT BLADES OR THE CT NOZZLE.  SEVERAL CRACKS WERE ALSO NOT	ED IN THE OUTER SECTION OF THE COMBUSTION LINER.  AFFECTED COMPONENTS WILL BE SENT TO A P&WC APPROVED REPAIR FACILITY FO	R REPAIRS OR REPLACEMENT AS NECESSARY.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2008041400002	20080414	00002	NE  	2008	4	14	2008FA0000184    	2	20080304	G	7230	304997801	COMPRESSOR      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					RT ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	185XP	4837 	1771 			BB952	93220			DURING PERFORMANCE OF A SCHEDULED 1800 HOUR HOT SECTION INSPECTION OF THE RT ENGINE, AT 1771 HOURS AND 7 YEARS TIS SINCE	 OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWABLE FOR RETUR	N TO SERVICE.  IT WAS NOTED THAT THERE WAS SOME METAL BUILD-UP ON THE SHROUD SEGMENTS IN THE 4 O'CLOCK THRU 6 O'CLOCK PO	SITIONS.  NO IMPACT DAMAGE WAS NOTED TO ANY OF THE CT BLADES OR THE CT NOZZLE.  SEVERAL CRACKS WERE ALSO NOTED IN THE OU	TER SECTION OF THE COMBUSTION LINER.  AFFECTED COMPONENTS WILL BE SENT TO A MFG APPROVED REPAIR FACILITY FOR REPAIRS OR 	REPLACEMENT AS NECESSARY.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2008040300098	20080403	00098	CE  	2008	4	3	2008FA0000186    	1	20080306	G	7120	051351119	MOUNT BRACKET   			CESSNA	172   	R172K       	2072431	CE  										LT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	758PX					R1723262				FOUND UPPER LT ENGINE MOUNT BRACKET CRACKED WHILE INSPECTING FOR CESSNA SEB07-2 REV 2.  THIS SERVICE BULLETIN DOES NOT A	PPLY TO THIS SERIAL NUMBER, ALTHOUGH A CRACK WAS FOUND.  RECOMMEND INCREASING THE SERIAL NUMBER RANGE OF AFFECTED AIRCRA	FT.  THIS SHOP HAS ALSO NOTED SEAPLANES HAVE A DIFFERENT LOWER MOUNT BRACKET THAN THAT WHICH IS CALLED OUT IN THE SERVIC	E BULLETIN.  RECOMMEND INCLUDING THE PROPER SEAPLANE MOUNT BRACKET NUMBERS FOR AIRCRAFT SO EQUIPPED.			1	H	7	1 	3O				3A17    					 
2008041000203	20080410	00203	SO  	2008	4	10	2008FA0000187    	1	20080402	G	8097	767391	SOLENOID        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					STARTER	SHORTED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	350ND					2842179				DURING PRE-FLIGHT WHEN MASTER SWITCH WAS TURNED ON, THE PROP BEGAN TO ROTATE UNCOMMANDED. TROUBLESHOT TO FUSED STARTER S	OLENOID. THIS IS THE SECOND SOLENOID FAILURE OF THIS TYPE IN ONE WEEK TIME, SAME MODEL AIRCRAFT. REPLACED WITH NEW PART,	 OPS CHECKED GOOD.				1	L	7	1 	3O	3	O		2A13    	E274				 
2008040400006	20080404	00006	CE  	2008	4	4	2008FA0000188    	1	20080310	G	3233	2000300003	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	PWA   	JT12  	JT12A8      	52042	NE  					LT MLG	BYPASSING       	D				O				OTHER                   				S			AFFECT SYSTEMS            			CL	CLIMB          	1			CE	09	828CA	3137 				159				LT MLG ACTUATOR BYPASSING ON RETRACTION CAUSING INTERFERENCE WITH IB DOOR ROLLERS. NO EXTERNAL FAILURE INDICATION. UPON 	TEARDOWN, IT WAS DISCOVERED THAT THE CYLINDER WAS SCRATCHED AND THE PISTON SEAL WAS DAMAGED.					2	L	7	2 	4F	4	J	RT	T00008WI	1E9				 
2008041000231	20080410	00231	EA  	2008	4	10	2008FA0000190    	2	20080313	G	7322		NUT             	PREAIR      		PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL SERVO	LOOSE           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	283PA		263  		62760	2844059				AD 2008-06-51 IS NOT APPLICABLE DUE TO THE ENGINE AND FUEL SERVO WERE OVERHAULED BY MFG ON MARCH 03, 2006 (OUTSIDE THE D	ATE RANGE OF THIS AD).  HOWEVER, WE DECIDED TO CHECK ALL OF OUR AIRCRAFT AND DURING THIS INSPECTION FOUND THE HEX NUT WA	S LOOSE ON THIS PARTICULAR SERVO.				1	L	7	1 	3O	3	O		2A13    	1E10				 
2008041000235	20080410	00235	EA  	2008	4	10	2008FA0000191    	2	20080331	G	7322	30802	FLOAT           	PREAIR      	MA45        	MAULE 	M7235 	M7235C      	5460110	SO  	LYC   	O540  	O540B4B5    	41532	EA  					CARBURETOR	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	249RD	439  			75103715	25069C	L2571940A			CARBURETOR FLOAT PN 30-802 PLASTIC FLOAT, THE CARBURETOR HAD A HIGH FLOAT LEVEL TWICE AFTER SETTING THE FLOAT TO SPEC IA	W MM. THE FLOAT WAS REMOVED DUE TO THE FLOAT LEVER TANG WAS BENDING UNDER NORMAL USE CONTACTING THE NEEDLE VALVE AND RES	ULTING IN A HIGH FLOAT LEVEL AND ROUGH RUNNING ENGINE. IT WAS NOTICED THAT THE FLOAT LEVER TANG ON THE PLASTIC FLOAT PN 	30-802 MADE OF STAINLESS STEEL IS ABOUT .5 THE THICKNESS THAT OF THE BRASS FLOAT PN 30-764 WHICH HAS HAD NO PROBLEMS WIT	H THE LEVER TANG BENDING IN NORMAL USE. A PN 30-764 FLOAT WAS INSTALLED AND ENGINE WAS NORMAL, NO ROUGHNESS NOTED.  PLEA	SE LOOK IN TO THIS PROBLEM SO AS NO ONE HAS A ROUGH AND RICH RUNNING ENGINE DUE TO THIS PROBLEM AND POSSIBLE EARLIER THA	1	H	7	1 	3O	3	O	NC	3A23    	E295				 
2008041000241	20080410	00241	SO  	2008	4	10	2008FA0000192    	1	20080218	G	3230	9582900	LINK ASSY       			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	SHEARED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	17	1031U					347250012				ACFT EXPERIENCED A NLG COLLAPSE UPON LANDING.  INSPECTION OF ACFT, NLG DOWNLOCK LINK ASSY FOUND SHEARED NEAR ATTACHMENT 	TO DOWNLOCK ASSY BODY.  IT IS NOT KNOW WHAT CAUSED THIS LINK ASSY TO SHEAR.  DETERMINED THAT NOT ALL THE REQUIREMENTS OF	 AD 2005-13-16 WERE ACCOMPLISHED DURING THE LAST ANNUAL, AND IT IS POSSIBLE THIS COULD HAVE BEEN A CONTRIBUTING FACTOR. 	 NUMEROUS COMPONENTS OF THE NLG REQUIRE MX ACTIONS & REPETITIVE INSPECTIONS.  FRACTURE MODE OF SHEARED ASSY COULDN`T DET	ERMINE IF PART FAILED INSTANTANTLY OR PROGRESSIVELY, SIGNATURE SUGGESTS A FATIGUE FRACTURE MAY HAVE BEEN PRESENT. AD2005	-13-16 ADDRESSES CONCERNS THAT HAVE RESULTED FROM SDR`S RELATED TO THE COLLAPSE OR INVOLUNTARY RETRACTION OF THE NLG ON 	1	L	7	2 	3O	3	O		A7SO    	1E10				 
2008041000244	20080410	00244	SO  	2008	4	10	2008FA0000193    	1	20080321	G	5720	902010XXX	SUPPORT BRACKET 	GRUMAV      		AMRGEN	AA5   	AA5A        	3960106	SO  										ZONE 600	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15		2850 	100  			SERIES				WHILE COMPLYING WITH AD 79-22-04 ON AILERON CONTROL SYS INSP AND SB 165A, 100 HOUR REPETITIVE INSP, FOUND LT OB AILERON 	HINGE SUPPORT BRACKET, 902010-501 CRACKED. CRACKED VISUALLY SEEN WITH OUT DISASSEMBLY USING A STRONG LIGHT AND SYSTEM LO	ADING.  HOWEVER, WHEN REMOVED FOR REPLACEMENT WITH NEW SUPPORT, THERE WERE 3 ADDITIONAL CRACKS GIVING A TOTAL OF (4) ON 	THIS COMPONENT, PAINT AND LOCATION OF CRACKS PRACTICALLY IMPOSSIBLE TO DISTINGUISH WITH COMPONENT INSTALLED.			1	L	7	1 	3O				A16EA   					 
2008040400010	20080404	00010	NM  	2008	4	4	2008FA0000194    	1	20080319	G	8120		PIPE            			COLUMB	LC40  	LC40550FG300	5150010	NM  	CONT  	O550  	TSIO550C    		SO  					TURBOCHARGER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	1024Z	438  			1CF730011	41097	802744			RT TURBO TRANSITION PIPE CRACKED. THIS IS THE THIRD ONE INTO OUR SHOP.						1	L	7	1 	3O	3	O	NT	A00003SE	E5SO				 
2008040400004	20080404	00004	EA  	2008	4	4	2008FA0000195    	2	20080229	G	7320	25244509	FUEL CONTROL    			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE	LOOSE           	C				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			GL	11	540PU	2900 	695  			2844096	L3103051A			RAN ENGINE AFTER INSPECTION AND FOUND FUEL FLOW AT TO POWER SETTING TO BE QUITE LOW.  INVESTIGATED AND FOUND PLUG LOOSE 	ON SIDE OF INJECTION SERVO.  CONTACTED ENGINE SHOP FOR FIX.					1	L	7	1 	3O	3	O		2A13    	1E10				 
2008041400012	20080414	00012	EA  	2008	4	14	2008FA0000197    	2	20080321	G	8530		CYLINDER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	NR 3	SEPARATED       	C				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			EA	21		126  				277554157	RL77048	HCE2YR2KBS		NR 3 CYLINDER SEPARATED FROM ENGINE CASE.						1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2008041400008	20080414	00008	SO  	2008	4	14	2008FA0000198    	2	20080318	G	8530	SA530348P15	PISTON          			CESSNA	150   	150D        	2071810	CE  	CONT  	O200  	O200A       	17020	SO  					NR 3 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	6029T	885  				15060729				REMOVAL OF NR 3 CYLINDER FOR REPLACEMENT REVEALED A 1.5 INCH CRACK IN THE UPPER PISTON SKIRT STARTING FROM THE BOTTOM OF	 THE PISTON. 885 HOURS SINCE NEW.					1	H	7	1 	3O	3	O		3A19    	E252				 
2008041400006	20080414	00006	SO  	2008	4	14	2008FA0000199    	2	20080318	G	8500		CASE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					RT ENGINE	CRACKED         	B				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	09	12RJ	1748 	937  			421C0306	292115R			REMOVED THIS ENGINE FROM THE RT POSITION FOR SHIPMENT BACK TO RAM AC DUE TO A DAMAGED CASE.  DAMAGE APPEARS TO BE CAUSED	 BY A FAILED CONNECTING ROD THAT BROKE APART AND PUNCTURED (2) LARGE HOLES IN THE CRANKCASE.  BRIEF ENGINE HISTORY: 347 	HOURS PRIOR TO THE FAILURE THE ENGINE DEVELOPED AN OIL LEAK FROM A HAIRLINE CRACK IN THE RT CASE. THE ENGINE WAS SHIPPED	 TO RAM WHERE IT WAS DISASSEMBLED, CLEANED AND INSPECTED BEFORE GETTING REASSEMBLED USING A SERVICEABLE CRANKCASE, NEW C	AMSHAFT, LIFTERS, MAIN AND ROD BEARINGS.		1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2008041400009	20080414	00009	SO  	2008	4	14	2008FA0000200    	2	20080318	G	8530		CYLINDER        			CESSNA	150   	150D        	2071810	CE  	CONT  	O200  	O200A       	17020	SO  					NR 1	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	6029T		885  			15060729				MUFFLER PRESSURE TEST REVEALED CRACKS IN NR 1 CYLINDER EXHAUST PORT, FWD SIDE. UNKNOWN CYLINDER TIME, WAS BORED .015 INC	H OVERSIZE.					1	H	7	1 	3O	3	O		3A19    	E252				 
2008041400007	20080414	00007	CE  	2008	4	14	2008FA0000201    	1	20080318	G	7820		FLAME TUBE      	CESSNA      		CESSNA	150   	150D        	2071810	CE  	CONT  	O200  	O200A       	17020	SO  					MUFFLER	RUPTURED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	6029T	3900 				15060729				RT MUFFLER P/N 0450400-26 WAS REMOVED FOR CYLINDER REPLACEMENT, INSP REVEALED DETERIORATED FLAME TUBES IN OUTLET PIPE AN	D NR1 INLET PIPE. OUTLET PIPE FLAME TUBE IS NOT READILY VISIBLE LOOKING UP TAIL PIPE. NO ENTRIES IN LOGBOOK INDICATING R	EPLACEMENT OF EITHER MUFFLER.				1	H	7	1 	3O	3	O		3A19    	E252				 
2008041400018	20080414	00018	CE  	2008	4	14	2008FA0000202    	1	20080328	G	7120		MOUNT           			CESSNA	172   	172D        	2072410	CE  										ENGINE	WRONG PART      	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21										AN UNKNOWN AMOUNT OF AC FIREWALL ATTACH ASSEMBLIES (ENGINE MOUNTS) THAT WERE NOT FAA-PMA APPROVED. THE MIDO ATTEMPTED TO	 CONTACT THE OWNER OF MFG CONCERNING THIS MATTER, HOWEVER, ALL PHONE CALLS WERE NOT RETURNED, AND CERTIFIED LETTERS NOT 	ACCEPTED. AS OF THIS TIME, THE COMPANY HAS CLOSED DOORS, HOWEVER, A FIREWALL ASSEMBLY WAS FOUND ON AC. THE OWNER OF THE 	AIRCRAFT WAS ADVISED THAT THE PART WAS NOT APPROVED AND IT HAD TO BE REMOVED. THE MIDO WAS INFORMED OF THE UNAPPROVED MO	UNT. THE MOUNT DOES NOT HAVE A PART NUMBER. THE MIDO WILL CONTACT THE FAA SUP OFFICE TO PUT OUT A NOTICE. RECOMMEND THAT	 INFORMATION BE DISSEMINATED TO THE AC MFG COMMUNITY TO ADVISE OWNERS, PILOTS, AND MECHANICS IF THEY HAVE ANY OF THESE M	1	H	7	1 	3O			NT	3A12    					 
2008040800001	20080408	00001	SW  	2008	4	8	2008FA0000203    	1	20080320	G	8011	14912LS	STARTER         			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	9615M		62   			670192	L189451	CH388859B		THIS STARTER WAS PURCHASED NEW FROM A LOCAL VENDOR.  THE STARTER FAILED TO OPERATE AFTER LESS THAN A YEAR AND LESS THAN 	100 HOURS OF SERVICE. THE OWNER\OPERATOR WANTED TO HAVE THE OLDER, HEAVIER STARTER INSTALLED HOWEVER NONE WERE AVAILABLE	, AFTER CONTACTING SEVERAL PARTS VENDORS. THE OPERATOR OPTED TO HAVE THE STARTER REPAIRED BY THE MFG. THE REPAIRED START	ER WAS INSTALLED BUT FAILED AGAIN SEVEN MONTHS AND 62.3 OPERATING HOURS LATER. A SERVICABLE STARTER WAS LOCATED AND INST	ALLED IAW ENGINE SERVICE INSTRUCTION 1154L DATED JANARY 27, 2006.  OUR SHOP RECOMMENDED THIS CHANGE DUE TO A TREND WE AR	E SEEING IN THE LIGHT WEIGHT STARTERS. WE HAVE SEEN AT LEAST 6 FAILURES OR THE STARTER DRIVE GEAR EITHER FAILING TO ENGA	1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
2008041400010	20080414	00010	NM  	2008	4	14	2008FA0000206    	1	20080319	G	8120	654327E	TURBOCHARGER    			COLUMB	LC40  	LC40550FG300	5150010	NM  	CONT  	O550  	TSIO550C    		SO  					RIGHT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21		438  				41097	802744			RT TURBO TRANSITION PIPE CRACKED. THIS IS THE THIRD ONE INTO OUR SHOP.						1	L	7	1 	3O	3	O	NT	A00003SE	E5SO				 
2008041400019	20080414	00019	SO  	2008	4	14	2008FA0000208    	1	20080328	G	2910	1159SCH2393	SHUTOFF VALVE   			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6108     	 	NE  					HYD SYSTEM	SEIZED          	C				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	23	312EL	7509 				1105				WHILE AT CRUISE ALTITUDE, THE COMBINE HYDRAULIC SHUTOFF VALVE FAILED TOWARD CLOSED POSITION WHICH IS INDICATED IN THE CO	CKPIT ON THE EICAS WITH DASHED LINES (VALVE IN TRANSITION) THUS TAKING AWAY YOUR HYDRAULIC PRESSURE INDICATION.  WHEN TH	E VALVE IS FULLY CLOSED THE INDICATION ON THE EICAS IS DIAGONAL SOLID LINES.  THE ONLY WAY TO GET THIS VALVE TO MOVE CLO	SED IS WITH THE FIRE L HANDLE.			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2008041400036	20080414	00036	EA  	2008	4	14	2008FA0000209    	2	20080401	G	7414	M11522	BREAKER POINTS  	SLICK       	6393        	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MAGNETO	WORN            	E				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	17	62BA	87   			0700226	274859	L1947848A			ENGINE BECAME INCREASINGLY DIFFICULT TO START, CHECKED IGNITION TIMING AND FOUND LT MAGNETO OUT OF TOLERANCE. INSPECTED 	LT MAGNETO, POINTS FAILED TO OPEN DUE TO EXCESSIVLY WORN BREAKER POINT CAM. 87 HOURS SINCE NEW					1	L	7	2 	3O	3	O		1A10    	1E4				 
2008041400013	20080414	00013	SO  	2008	4	14	2008FA0000210    	1	20080325	G	8011	701122223	SOLENOID        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					STARTER	STICKS          	B				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	21	245ND					2842086				WHEN BATTERY MASTER TURNED ON PROP BEGAN ROTATING UNCOMMANDED. TROUBLESHOT TO FUSED STATER SOLENOID. REPLACED SOLENOID W	ITH NEW OEM PART PROBLEM PERSISTED.  NEW SOLENOID WAS STRUCK WITH A SIDE BLOW AND CONTACTS FREED. REPLACED WITH ANOTHER 	NEW OEM PART, PROBLEM CORRECTED.				1	L	7	1 	3O	3	O		2A13    	E274				 
2008041400004	20080414	00004	SO  	2008	4	14	2008FA0000211    	2	20080312	G	8500	654327E	DUCT            			LANCAR	LC41  	LC41550FG   	5150001	NM  	CONT  	O550  	TSIO550A    	41516	SO  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21		154  				41722	914564			RT TURBO TRANSITION DUCT CRACKED. (NOTE: THIS IS THE SECOND TIME WE HAVE SEEN THIS)						1	L	7	1 	3O	3	O	NT	A00003SE	E5SO				 
2008041400011	20080414	00011	EA  	2008	4	14	2008FA0000212    	2	20080319	G	7322	383493	GASKET          	PREAIR      		CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					FUEL SERVO	UNKNOWN         	D				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			NM	01	2446X				70A59005	20608097	RL3065348A			INSPECTED FUEL SERVO PLUG IAW SBPRS-107, REVISION 1, DATED MARCH 6, 2008. NO DAMAGE FOUND ON THE THREADS OF THE PLUG OF 	THE SERVO UNIT. INSTALLED PLUG AND SAFETIED IAW INSTRUCTIONS.					1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2008041400005	20080414	00005	CE  	2008	4	14	2008FA0000214    	1	20080207	G	3040	FED2000	DEFOG SYSTEM    			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	BURNED          	G				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			NM	01	60WL					382				RIGHT AFTER TAKEOFF, AUX DE-FOG UNIT ON CO-PILOT SIDE BURNED AND SMOKE FROM BLOWER FAILURE. NO WIRE PROBLEMS OR CIRCUIT 	BREAKER ISSUES FOUND. UNIT FAILURE CAUSED SMOKE IN COCKPIT, CREW DECLARED EMERGENCY AND RETURNED TO AIRPORT WITHOUT FURT	HER INCIDENT.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2008041000186	20080410	00186	CE  	2008	4	10	2008FA0000215    	1	20080204	G	2800		NUT             			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					FUEL SERVO	LOOSE           	B			Z08R	A				UNSCHED LANDING         				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	168JS	302  				T20608735				WHILE PERFORMING SB PRS-107, FOUND PN 383493 HEX NUT ACCESS PLUG FINGER LOOSE.  ALSO, FOUND RED DYE INSIDE FUEL SERVO AI	R CHAMBER.  THIS AC HAS HAD AN ISSUE WITH LEAN IDLE MIXTURE IN THE PAST.  NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARM	ED UP.  SUSPECT UNDERTORQUED FROM FACTORY AND RED DYE NOT FLUSHED FROM CHAMBER.  SENT TO OVERHAUL FACILITY TO HAVE CORRE	CTED AND PERFORMED THE REQUIREMENTS OF PRS-107 SB.  (K)			1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2008041000170	20080410	00170	EA  	2008	4	10	2008FA0000216    	2	20080204	G	7200		NUT             			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	LOOSE           	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	227BH					172S10662				WHILE PERFORMING SB PRS-107, FOUND PN 383493 HEX NUT PLUG FINGER LOOSE.  OTE: HEX NUT WILL BECOME LOOSE IF ENGINE IS WAR	MED UP.  SUSPECT UNDERTORQUED FROM THE FACTORY.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008041000184	20080410	00184	EA  	2008	4	10	2008FA0000217    	2	20080204	G	7320		SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	UNDERTORQUED    	C			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	719JW					172S10527				WHILE PERFORMING SB PRS-107, FOUND PN 383493, HEX NUT PLUG FINGER LOOSE.  NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARM	ED UP.  SUSPECT UNDERTORQUED FROM FACTORY					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008041000193	20080410	00193	EA  	2008	4	10	2008FA0000218    	2	20080204	G	7300		SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENG FUEL	LOOSE           	B			Z08R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CE	07	452SM					172S10528				WHILE PERFORMING SB PRS-107 FOUND PN 383493 HEX NUT PLUG FINGER LOOSE.  NOTE: HEX NUT WILL BE LOOSER IF ENGINE IS WARMED	 UP.  SUSPECT UNDERTORQUED FROM THE FACTORY.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008041400043	20080414	00043	SW  	2008	4	14	2008FA0000219    	1	20080205	G	2820		SELECTOR VALVE  			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360*       	41514	EA  					FUEL SYSTEM	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	6529U					2312				FUEL SELECTOR VALVE SEIZED IN THE (OFF) POSITION DURING A ROUTINE FUEL TANK SWITCHOVER.  FAILURE CAUSED BY CORROSION ON 	SELECTOR VALVE SHAFT WHERE IT PASSES THROUGH THE UPPER VALVE HOUSING.  POOR DESIGN.  NO PROVISION MADE TO PREVENT SPILLE	D LIQUIDS OR MOISTURE FROM CARPET FROM ENTERING UPPER HOUSING VALVE SHAFT BORE.  (K)				1	L	7	1 	3O	3	O		2A3     	E286				 
2008041400044	20080414	00044	CE  	2008	4	14	2008FA0000220    	1	20080222	G	2701	05131682	CONTROL WHEEL   			CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300*       	17022	SO  						BROKEN          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	08	34264					625				ON TAXI FROM REFUELING PILOT WAS MAKING A LT TURN IN FRONT OF HANGER.  PULLED CONTROL WHEEL FULL AFT (TO TAKE WEIGHT OFF	 OF FRONT WHEEL) CONTROL WHEEL BROKE OFF IN HIS HAND.  (OUTSIDE TEM APPROX 20 DEGREES) BREAK WAS FROM LWR LT (7 OCLOCK) 	TO UPPER RT (2 OCLOCK).  (K)				1	H	7	1 	3O	3	O		3A12    	E253				 
2008041000246	20080410	00246	EA  	2008	4	10	2008FA0000221    	1	20080220	G	7921	269D45031	SCROLL          			SCWZER	269   	269D        	8059501	EA  	ALLSN 	250C  	250C20      	03013	GL  					OIL COOLER FAN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	411HU					0040				UPON INSPECTION OF OIL COOLER FAN ASSY, FOUND MANY CRACKS AROUND THE TOP MOUNT OF SCROLL ASSY.  (K)						1	G	7	1 	3U	3	U	0	4H12    	E4CE				 
2008041000205	20080410	00205	CE  	2008	4	10	2008FA0000223    	1	20080308	G	5753	052390133	SKIN            			CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470*       	17026	SO  					TE FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	71784	5800 	1200 			18259755				ON INSPECTION BOTH FLAPS RT AND LT TOP AND BOTTOM FLAP SKINS WERE CRACKED 6 TO 8 INCHES ALONG THE T/E, ON THE RIVET LINE	.  ALSO SHEERED RIVETS ON (3) OF THE (4) FLAP TRACK LOWER TRACK TO RIBS.  RESKINNED FLAPS AND INSTALLED MS21042 STEEL SC	REWS IN REPLACEMENT OF THE SHEERED RIVETS.  PROBABLE CAUSE BY FLAP OVERSPEED WITH HIGH G, LOADS.  THIS AIRCRAFT TOWS GLI	DERS ALL THE TIME.  (K)			1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2008041000194	20080410	00194	SO  	2008	4	10	2008FA0000224    	1	20080321	G	2910	1159SCH5197	SIGHT GLASS     			GULSTM	GVSP  	GVSPG550    	3980203	SO  	RROYCE	BR700 	BR700710A110	 	NE  					HYD TANK	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	57UH					5163				SIGHT GLASS CRACKED IN SEVERAL LOCATIONS AND LEAKS HYDRAULIC FLUID.  THIS TANK IS ONE OF SEVERAL RETURNED FOR THE SAME D	EFECT.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2008041000234	20080410	00234	NM  	2008	4	10	2008FA0000225    	1	20080401	G	8120	654327	TRANSITION DUCT 			LANCAR	LC41  	LC41550FG   	5150001	NM  	CONT  	O550  	TSIO550C    		SO  					TURBOCHARGER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	431PC					41050				DURING ANNUAL INSP FOUND TURBO TRANSITION PART OF EXHAUST CRACKED ALL THE WAY THRU FRONT RADIUS OF THE PIPE.  (K)						1	L	7	1 	3O	3	O	NT	A00003SE	E5SO				 
2008042800298	20080428	00298	SO  	2008	4	28	2008FA0000226    	1	20080321	G	2910	1159SCH5197	SIGHT GLASS     			GULSTM	GIVX  	GIVXG450    	3980205	SO  	RROYCE	TAY   	TAY6118     	 	EU  					HYD SYSTEM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	612AF	224  				4069				SIGHT GLASS CRACKED IN SEVERAL LOCATIONS AND LEAKS HYDRAULIC FLUID, THIS TANK IS ONE OF SEVERAL RETURNED FOR THE SAME DE	FECT.   (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2008041000219	20080410	00219	SO  	2008	4	10	2008FA0000227    	1	20080225	G	3210	86262003	TUBE            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					MLG	WORN            	D			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5341Z	2193 				4496107				NOSE GEAR DOOR TUBE PN 86262003 FOUND WITH GROOVE WORN INTO TUBE AT APPROX 65 PERCENT OF TUBE THICKNESS IN THE AREA OF T	HE LT AND RT SUPPORTS PN 86262-005 AND 86262-012 RESPECTIVELY.  THIS TUBE CONNECTS TO THE LT AND RT NOSE GEAR DOOR RODS 	AND PIVOTS AS THE GEAR IS RAISED AND LOWERED AND IT IS AT THE PIVOT POINT OF THE TUBE WHERE THIS WEAR IS OCCURRING.  CUR	RENTLY THERE IS A NYLON BUSHING PN 452647 THAT IS INSERTED AT THIS PIVOT POINT TO PROVIDE FOR SOME PROTECTION OF THE TUB	E.  THERE IS HOWEVER, NO WEAR TO THIS NYLON BUSHING.  IT CAN BE ASSUMED THAT THIS NYLON BUSHING IS THE CAUSE OF THE WEAR	 AND PROVIDES NO GUARD AGAINST PROTECTING THE INTEGRITY OF THE TUBE.  CURRENTLY THERE IS NO REQUIREMENT FOR LUBRICATION 	1	L	7	2 	3O	3	O		A19S0   	E286				 
2008041400053	20080414	00053	SO  	2008	4	14	2008FA0000229    	1	20080408	G	8011	701122223	SOLENOID        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					STARTER	STICKS          	B				H				DEACTIVATE SYST/CIRCUITS				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			GL	21	436ND	3478 				2842213				AFTER START, STARTER ANNUNCIATOR DID NOT EXTINGUISH. ENGINE SHUTDOWN WITH MIXTURE BUT CONTINUED TO CRANK OVER WITH MASTE	R TURNED ON. TROUBLESHOOTING REVEALED STARTER CONTACTOR STUCK CLOSED. WHEN STRUCK CONTACTS WOULD OPEN BUT WHEN POWER APP	LIED WOULD STICK CLOSED UNTIL STRUCK.				1	L	7	1 	3O	3	O		2A13    	E274				 
2008041400058	20080414	00058	SW  	2008	4	14	2008FA0000230    	1	20080331	G	2731		CONTROL TUBE    			ECLIPS	EA500 	ECLIPSEEA500	3350000	SW  										PITCH TRIM	OUT OF ADJUST   	B			CJ6R	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	03	875NA					000018				AC EXPERIENCED A PITCH TRIM MALFUNCTION ON TAKEOFF ACCOMPANIED BY A WARNING MESSAGE.  AN EMERGENCY WAS DECLARED AND THE 	AC WAS RETURNED TO BASE.  PROBLEM WAS DUPLICATED ON THE GROUND.  AFTER TROUBLESHOOTING, IT WAS DETERMINED THAT A REPLACE	MENT ACTUATOR SHOULD BE INSTALLED.  AFTER INSTALLING NEW PART, DEFECT STILL EXISTED.  FURTHER TROUBLESHOOTING REVEALED T	HAT THE CONTROL TUBES CONNECTED THE ACTUATOR TO THE CONTROL SURFACE WERE NOT SIMILARLY ADJUSTED.  THIS CONDITION CAUSED 	A BINDING OF THE SYS MECHANICS AND THE SUBSEQUENT FAILURE.  WHEN THE CONTROL TUBES WERE SIMILARLY ADJUSTED, THE SYSTEM O	PERATED CORRECTLY ON GROUND AND IN SUBSEQUENT OPERATIONAL CHECK FLIGHT.  (K)	1	L	7	2 	4J			RT	A00002AC					 
2008041400060	20080414	00060	CE  	2008	4	14	2008FA0000231    	1	20080331	G	2820		LINE            			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					GAS COLATOR	LEAKING         	C				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			SO	03	20935					18261306				FUEL LEAKING FROM GAS COLATOR BOWL, TIGHTENED AT FACTORY DURING ACCEPTANCE FLIGHT (5.0 HOURS).  FUEL LEAKING FROM GAS CO	LATOR INLET LINE (10 HOURS SINCE NEW) RESULTED IN OFF-AIRPORT LANDING DUE TO FUEL QUANTITY.  (K)					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2008041400061	20080414	00061	WP  	2008	4	14	2008FA0000232    	1	20080331	G	2621	130835	CARTRIDGE       			DOUG  	DC3   	DC3CR183090C	3021466	WP  	PWA   	PT6   	PT6*        	52043	EA  					FIRE BOTTLE	FAILED          	G			VWBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	300BF				03692C1	26744				THE FIRE BOTTLE WAS BEING DISCHARGED FOR AN OVERHAUL.  THE CARTRIDGE FIRED BUT DID NOT DISCHARGE THE BOTTLE.  SUSPECT IM	PROPER SETUP OF CARTRIDGE IN BOTTLE.  (K)					2	L	7	2 	4R	3	T		A669    	E2NE				 
2008041400062	20080414	00062	EA  	2008	4	14	2008FA0000233    	2	20080318	G	8530	IO360AV	CYLINDER        			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	79337					547		CH42539B		PILOT REPORTED PARTIAL POWER LOSS ON TAKEOFF.  ENG INSP REVEALED THE FOLLOWING DISCREPANCIES AND CORRECTIONS AS NOTE: CY	L NR 1 HAD BAD INTAKE VALVE SEAT WITH EXCESSIVE WEAR, AND FUEL INJECTOR AIR SCREEN CONTAMINATED.  THIS POSSIBLY CAUSED C	YL TO BURN LEAN AND CAUSED EXCESSIVE WEARING ON VALVE SEAT.  THIS IN TURN WOULDNT ALLOW THE INTAKE VALVE TO CLOSE PROPE	RLY, CRATING ROUGH ENG RUNNING AND OCCASIONAL BACK-FIRING.  COMPLETE STUD ASSY WAS REPLACED WITH REBUILT ASSY SN 162, UN	DER WO 032608AA.  CYL NR 4 HAD EXCESSIVE ROCKER ARM SIDE CLEARANCE.  ROCKER ARM SIDE CLEARANCE WAS RESHIMMED AS SERVICE 	INSTRUCTIONS IN SB NR 225B BY ADDING ADDITIONAL SHIMS TO BRING ROCKER ARM SIDE.	1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
2008041400064	20080414	00064	SO  	2008	4	14	2008FA0000234    	1	20080307	G	7160		VALVE           			MAULE 	M4    	M4210C      	5460112	SO  	CONT  	IO360 	IO360*      	17025	CE  					ALT AIR VALVE	BROKEN          	G				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	11	51430					1097C				THE ENG AUTOMATIC ALTERNATE INDUCTION AIR VALVE THAT IS PARTIALLY LOCATED INSIDE THE CYLINDRICAL PAPER INDUCTION AIR FIL	TER CAME APART AND SOME OF ITS PART (2 INCH LONG, .2500 INCH DIAMETER BOLT.  2 INCH LONG SPIRAL SPRING WASHER, AND COTTE	R PIN) WERE INGESTED INTO THE ENGINE INTAKE MANIFOLD, ENG CYL VALVES AND THE ENG CYL.  THIS CAUSED A MAJOR LOSS OF POWER	 AFTER TAKEOFF, THE PILOT WAS ABLE TO GET BACK TO THE RUNWAY, BUT HE GROUND LOOPED THE AIRPLANE CAUSING AN ACCIDENT DUE 	TO SUBSTANTIAL DAMAGES TO THE AIRPLANE.  POST ACCIDENT INVESTIGATION FOUND THAT AT AN EARLIER DATE THE PREVIOUS OWNER HA	D DISASSEMBLED THE ALTERNATE AIR VALVE TO PAINT IT AND HE MAY HAVE IMPROPERLY REINSTALLED THE COTTER PIN INTO THE CASTEL	1	H	7	1 	3O	3	O		3A23    	E1CE				 
2008041400065	20080414	00065	CE  	2008	4	14	2008FA0000235    	1	20080301	G	2510	MS27039116	SCREW           			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					UNDER REAR SEAT	IMPROPER PART   	D			LN7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	757XU					R18201273				MFG SB NR SEB07-3 TO CHECK THE LENGTH OF THE SCREWS IN ACCESS PLATE UNDER REAR SEAT.  THE PLATE MAY HAVE HAD TOO LONG A 	SCREW INSTALLED WHICH COULD CAUSE A FAILURE OF THE LANDING GEAR TO OPERATE DOWN.  THE SB LISTED THE PROPER SCREWS TO USE	 IN EACH HOLE IN THE PLATE.  THE SCREWS LISTED ARE THE ONES IN THE PARTS CATALOG.  THOSE ARE THE SCREWS THAT ARE TOO LON	G.  IF ANYBODY PUT IN THE PROPER LENGTH SCREW, (MS27039-1-12), THEN THE AC WOULD BE LESS SAFE AFTER COMPLYING WITH THE S	B.  THE PLATE NEEDS 17 EA MS27039-1-12, AND 1 MS27039-1-09.  (K)		1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2008041400066	20080414	00066	EU  	2008	4	14	2008FA0000236    	1	20080227	G	3222	5322012039	PIN             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					NLG STRUT	MISMANUFACTURED 	B			Z4MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	672SD					666				DURING NOSE STRUT RESEALING, TORQUE LINKS WERE REMOVED.  BEFORE REASSEMBLY THE PINS WERE CHECKED TO VERIFY GREASE WOULD 	PASS THROUGH.  GREASE WOULD PASS THROUGH THE LOWER BUT NOT THE UPPER (UPPER AND LOWER PINS THAT CONNECT THE TORQUE LINKS	 TO THE GEAR ARE THE SAME PN).  AFTER CLEANING, FOUND THAT THE UPPER PIN COUNTER BORE ONLY WENT PART WAY THROUGH THE PIN	.  (K)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2008041400067	20080414	00067	NE  	2008	4	14	2008FA0000237    	1	20080221	G	6410	7610105017045	SPAR            			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6*        	52043	EA  					T/R BLADE	CRACKED         	C			CW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	780P	2905 				760359				DURING A ROUTINE INSP A SLIGHT, OCCASIONAL CLICK WAS HEARD WHILE FLEXING TAIL ROTOR BLADE.  BLADE ASSY PN 761005501042, 	SN A245-00153 WAS REMOVED FOR PRECAUTIONARY MEASURES SENT FOR INSPECTION/ EVALUATION. UPON DISASSEMBLY AND INSPECTION SP	AR WAS FOUND TO HAVE CRACKS COMING FROM ELLIPTICAL PLUG AREA.  SPAR WAS SUBSEQUENTLY CHANGED, BLADE INSPECTED AND RETURN	ED TO SERVICEABLE CONDITION.  SCRAPED SPAR.			1	G	7	2 	4U	3	T		H1NE    	E2NE				 
2008041400076	20080414	00076	GL  	2008	4	14	2008FA0000238    	1	20080227	G	3411	51815001	BUSHING         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					REDUCER	INCORRECT       	C			LN7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	362HE					1263				STATIC SYSTEM FAILED LEAK CHECK DURING 2 YEAR STATIC SYS IFR CERTIFICATION, LEAKS WERE CAUSED BY REDUCED BUSHING FAILING	 TO SEAL STATIC LINE SUMP.  (ON BOTH SIDES, PILOT AND COPILOT).  TO REPAIR THE LEAKAGE, PIPE THREAD TAPE (TEFLON TAPE) W	AS USED ON THE REDUCER BUSHING BEFORE MATING IT WITH THE STATIC LINE SUMP.  THE TYPE OF THREAD ON THESE ITEMS SHOULD NOT	 REQUIRE TEFFLON TAPE TO SEAL.  SB 2X-34-22R1 (REVISED 10 OCT 2006) STEP L (FOR KIT 701164-001) STATES (APPLY THREAD SEA	LANT TO ALL MALE PIPE THREAD FITTINGS PRIOR TO STATIC LINE SUMP ARE NOT PIPE THREAD, AND THEREFOR WERE NOT (TAPED).  REC	OMMEND CHANGING PROCEDURE TO STATE (APPLY THREAD SEALANT TO ALL MALE FITTINGS PRIOR TO ASSY).  (K)	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2008041400093	20080414	00093	WP  	2008	4	14	2008FA0000239    	1	20080115	G	6410	MHS54896	NUT             			HUGHES	369   	369E        	4470707	WP  										TAIL ROTOR BLADE	SPLIT           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	9460T					0238E				ON FINAL TORQUE OF TAIL ROTOR BLADES RETENTION BOLT, NEW NUT SPLIT PRIOR TO ACHIEVING TORQUE.  NEW NUT, IS THINNER AND L	IGHTER STRENGTH THAN PREVIOUSLY MFG OLDER PN.  NEW BOLTS ALSO REQURIE A NEW HIGHT TORQUE VALUE.  (K)					1	G	7	1 	3U				H3WE    					 
2008041400094	20080414	00094	EA  	2008	4	14	2008FA0000240    	2	20080307	G	8520		BOLT            			BEECH 	80    	65B80       	1152812	CE  	LYC   	O540  	IGO540B1A   	41532	EA  					CONNECTING ROD	FAILED          	G			KZ5R	A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			GL	15	103BA					LD435				NR 1 ENGINE SHUTDOWN IN FLIGHT.  SUSPECTED NR 7 CONNECTING ROD BOLT FAILURE.  CAUSING CYL SEPARATION FROM CASE AND CRANK	 CASE CRACK.  AC LANDED SAFELY WITHOUT OTHER DAMAGE.  (K)					1	L	7	2 	3O	3	O		3A20    	1E11				 
2008041400063	20080414	00063	EU  	2008	4	14	2008FA0000241    	2	20080409	G	8500		ENGINE          			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE1250299  		EU  					LEFT	POWER LOSS      	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			SO	15	49OTS					42AC090	020201763			AFTER TAKEOFF AND PULLING LANDING GEAR UP, LT ENGINE POWER REDUCTION TO 75 PERCENT FOR ABOUT ONE MINUTE AND POWER WAS RE	STORED. THIS SAME ISSUE HAS BEEN INDUCTED TWICE IN LESS THAN 24 HRS. THERE IS NO FEDAC WARNINGS SHOWN ON SYS. A REPORT H	AS BEEN SENT TO MFG.				1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2008041400098	20080414	00098	SO  	2008	4	14	2008FA0000243    	1	20080410	G	8120		TURBOCHARGER    			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					ENGINE	FOD             	D				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			SO	05	47550					28R7703397	232784B			TURBOCHARGER COMPRESSOR DAMAGED BY FOD INGESTED THROUGH THE ALTERNATE AIR DOOR. THIS DOOR IS ON TOP OF THE AIR FILTER BO	X ALLOWING ANY OBJECT THROWN UP BY THE NOSE WHEEL TO ENTER THE INDUCTION SYSTEM WHEN THE DOOR IS ACTIVATED DURING PREFLI	GHT CHECKS.				1	L	7	1 	3O	3	O		2A13    	E9CE				 
2008041400059	20080414	00059	CE  	2008	4	14	2008FA0000245    	1	20080409	G	2731		TRIM SYSTEM     			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					ELEVATOR	ICED            	P				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			EA	21	200TR	400  				LJ1067				WHEN THE AIRPLANE HAS SET ON THE RAMP IN THE RAIN, THEN TAKES OFF WITH A QUICK CLIMB TO COLDER TEMPERATURES AT ALTITUDE,	 THE ELEVATOR TRIM FREEZES. THE AUTOPILOT KICKS OFF BECAUSE IT IS UNABLE TO RESPOND. THE PILOT THEN HANDFLYS WITH THE EL	EVATOR FORCE LOADED UP AND UNABLE TO TRIM.  WITH LITTLE NUDGES BACK AND FORTH ON THE TRIM WHEEL FOR ABOUT 10 MINUTES, TH	E SYSTEM BECOMES FREE.  EACH TIME I REPORT THIS TO MECHANICS, THEY INSPECT AND LUBRICATE THE SYSTEM AND REPORT EVERYTHIN	G IS SATISFACTORY.  THIS WAS MY EXPERIENCE FROM 1984 TO 2005. THE PLANE WAS NORMALLY KEPT IN A HANGAR SO OCCURRENCES WER	E INFREQUENT.	1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2008041400104	20080414	00104	EA  	2008	4	14	2008FA0000246    	2	20080411	G	8530		CYLINDER        			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540*     	41532	EA  					NR 5	DAMAGED         	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			GL	21	476EB	1400 	1400 			317612059	L167768A			NR 5 CYL EXHAUST VALVE BROKEN, SENDING THE HEAD OF THE VALVE THROUGH THE EXHAUST AND LODGING ITSELF INTO THE TURBOCHARGE	R, EXTENSIVE DAMAGE TO THE CYLINDER, PISTON, AND TURBO.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2008042500057	20080425	00057	CE  	2008	4	25	2008FA0000247    	1	20080131	G	3245	22X8007008	TUBE            	CLEVELAND   		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					NOSE WHEEL	TORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	694MA	69   				208B0694				PILOT REPORTED NOSE TIRE FLAT.  UPON DISASSEMBLY OF NOSE TIRE, FOUND MIDDLE SEAM ON OUTSIDE OF TUBE, TORN/SPLIT, APPROX 	1 INCH IN LENGTH. (K)					1	H	7	1 	3T	3	T		A37CE   	E2NE				 
2008041700024	20080417	00024	CE  	2008	4	17	2008FA0000248    	1	20080204	G	3260		THROTTLE SWITCH 			CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520*      	17032	SO  					COCKPIT	INTERMITTENT    	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	23	1333T					T21059108				GEAR WARNING HORN WAS INOPERATIVE.  AC LANDED WITH LANDING GEAR UP.  SUBSEQUENT INVESTIGATION DETERMINED THROTTLE MICROS	WITCH WAS MAKING INTERMITTENT CONTACT WHEN ENGAGED AND GROUND CONNECTION WAS INSUFFICIENT.  CORRECTED BY REPLACING SWITC	H AND REPAIRING GROUND CONNECTION.  HORN OPERATION SHOULD BE CHECKED VIA TEST FEATURE DURING PREFLIGHT.  (K)				1	H	7	1 	3O	3	O		3A21    	E5CE				 
2008042500069	20080425	00069	CE  	2008	4	25	2008FA0000249    	1	20080207	G	3233	MS28775112	SEAL            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					NLG ACTUATOR	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	6562V					172RG0775				AFTER REPEATED TOUCH AND GO PROCEDURES, THE AC FAILED TO RETRACT THE LANDING GEAR DUE TO A LACK OF HYDRAULIC FLUID. THIS	 RESULTED IN A GEAR UP LANDING.  DURING THE ACCIDENT INVESTIGATION IT WAS DETERMINED THAT THE HYDRAULIC FLUID RESERVOIR 	WAS DEPLETED OF FLUID BY CYCLING THE LANDING GEAR.  THE NLG ACTUATOR WAS LEAKING STEADILY WHILE THE HYDRAULIC PUMP WAS C	YCLING.  DAMAGE TO THE AC WAS LIMITED DUE TO THE PROPER EXECUTION OF EMERGENCY LANDING PROCEDURES.  THERE WERE NO INJURI	ES.  (K)		1	H	7	1 	3O	3	O		3A17    	E286				 
2008042500106	20080425	00106	WP  	2008	4	25	2008FA0000250    	2	20080305	G	7200		ENGINE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R321	R321482F8   	GL  		OVERHEATED      	W			LY0F	E				ENGINE SHUTDOWN         				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			SO	23	139LC	24465				AC732	P44344	DRG856029		IN CRUISE TO 8000 FT, INDICATION OF RED LIGHT OF OIL PRESSURE WITH 870 DEGREE TEMPERATURE.  LIGHT TURNS OFF.  AFTER 15 S	ECONDS, THE LIGHT TURNS ON AGAIN WITH 870 DEGREE TEMPERATURE, BUT THE PRESSURE DOWN NEAR ZERO.  THE CREW  MADE THE SHUTD	OWN ENGINE PROCEDURE.  LANDING WITHOUT NOVELTY. AT THE MOMENT THE ENGINE IS WAITING TECH INSPECTOR.  (K)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2008042500112	20080425	00112	CE  	2008	4	25	2008FA0000252    	1	20080305	G	8011		MOUNT           			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					STARTER	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	214CE	1    				T20608592				ORIGINAL STARTER (TT 433.4) WAS REMOVED BECAUSE IT FAILED (SMELLED BURNED).  A REPLACEMENT WAS ORDERED FROM MFG AND INST	ALLED.  CHANGED THE SPARK PLUGS AND CHECKED ENGINE TIMING, WHICH WAS FOUND GOOD.  AFTER INSTALLATION OF STARTER STARTED 	THE AC (5) TIMES AND OPS CHECKED GOOD.   2/29/2008 THE PILOT TRIED TO START THE ACFT AND HEARD A GROWLING SOUND.  OPENED	 THE COWLINGS AND FOUND THE STARTER MOUNT CRACKED THROUGH THE BELL HOUSING.  NOTIFIED MFG AND THEY ASSURED ME THIS WAS N	ORMAL WHEN AN AC HAS A KICKBACK.  THE PILOT STATED HE DID NOT HAVE A KICKBACK.  SENT THE STARTER FOR REPAIR AND WHEN RET	URNED, INSTALL AND AGAIN CHECKED THE IGNITION SYS WITH NO ABNORMITIES FOUND.  STARTED THE AC (5) TIMES AND HAD THE OWNER	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2008042500127	20080425	00127	CE  	2008	4	25	2008FA0000254    	2	20080305	G	7310		SERVO           			DIAMON	DA40  	DA40        	2990002	GL  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCC2Y	HCC2YR1     	GL  	FUEL INJECTION	DAMAGED         	D			U1VS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103UV	687  				40683	L3284951A	CH40160B		WHILE PERFORMING A 100 HR INSP, THE TECH DISCOVERED FINE METAL PARTICLES COVERING THE THROAT AND VALVE OF THE FUEL INJEC	TION SERVO (2576568-1, SN 70B10709).  THE SERVO WAS SENT TO A REPAIR FACILITY TO DETERMINE WHETHER OR NOT ANY OF THE MET	AL PARTICLES ENTERED THE SERVOS BLAST TUBES.  IT HAS BEEN DETERMINED THAT THE METAL ORIGINATED FROM THE CHAFING OF THE L	OOSE FITTING INLET RING (ITEM 220) WITHIN THE FLANGE (ITEM 20).  THE LOOSE FIT IS DUE TO MFG.  MFG HAS NOT COME UP WITH 	A FIX AS OF THIS DATE.  FOR NOW WE ARE CEMENTING THE INLET RING TO THE FLANGE WHILE AWAITING A PERMANENT FIX.		1	L	7	1 	3O	3	O	NT	A47CE   	E1CE	5	C	P920	 
2008042800300	20080428	00300	CE  	2008	4	28	2008FA0000256    	1	20080321	G	2520	17001277	PANEL           			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					CABIN	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	97660	15328				18267161				DURING AN AGING AC INSP OF FLEET AC, VEERING SEVERITY OF SURFACE CORROSION HAS BEEN FOUND IN AC CONTAINING SOUNDPROOFING	 PANELS SHOWN IN MFG IPC FIG 90.  THE HEAVIEST AND MOST SEVERE CORROSION WAS FOUND UNDER SOUNDPROOFING PANELS PN 0700076	2-23 ITEM 7, PN 1700127-7 AND -10, ITEMS 10 AND 13, PN 1200217-8, ITEM 14 AND 1200193-11, ITEM 15.  REMOVAL OF SURFACE C	ORROSION, CLEANING, BRIGHTING, AND ALODINING THE EFFECTED AREAS TO REMOVING OF COMPLETE SKIN PANELS TO RESTORE STRUCTURA	L INTEGRITY OF THE AC.  PROBABLE CAUSE IS THE MFG TO PROVIDE A SUITABLE CORROSION BARRIER TO PROTECT THE AC STRUCTURAL I	NTEGRITY AND THE SKIN PANELS BEING EXPOSED TO CHEMICAL ACTION OF THE ADHESIVES USED TO ATTACH THE SOUNDPROOFING PANELS T	1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2008042800304	20080428	00304	NE  	2008	4	28	2008FA0000257    	2	20080311	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						MALFUNCTIONED   	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CE	03	957FE					208B0070	17431			AS PILOT OF FLT 7575, LEVELED OFF AT 9000 FT, HEARD A LOUD POP NOISE COME FROM THE ENGINE AND NOTICED TRQ DROPPED BELOW 	600 LBS AND ITT STARTED RISING.  PILOT NEVER LOST POWER BUT DUE TO TEMP RISING HE DECLARED AN EMERGENCY AND LANDED SAFEL	Y.  AFTER TALKING TO PILOT AND CHECKING POWER ANALYZER AND RECORDER (PAR) THE ITT TEMP REACHED 926 DEGREES.  ACCORDING T	O MM, ANYTHING OVER 900 DEGREES IN CRUISE FLT REQUIRES TO BE PULLED AND SENT TO OVERHAUL SHOP FOR INSPECTION.  WE HAVE B	OROSCOPED THE ENGINE AND SEE NO EVIDENCE OF ANY FOD ACCORDING TO OUR CONTRACT MAINT.  THERE IS SIGNS OF AN OVERTEMP.  FI	GURED THAT WITH WHAT THE PAR SHOWS.  NOT SURE WHAT CAUSE THE LOUD POP AND THE OVER TEMP.  MAYBE THE COMPRESSOR BLEED VAL	1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2008042800307	20080428	00307	CE  	2008	4	28	2008FA0000258    	1	20080228	G	5730		TAPE            			CESSNA	140   	140         	2071602	CE  	CONT  	C90   	C90*        	17009	SO  					WING	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	3527V					14796				DURING FLIGHT, THE FABRIC PATCH CAME OFF.  THE AC WAS LANDED WITH SOME DIFFICULTY BUT WITHOUT INCIDENT.  IT IS SPECULATE	D THE AIR STREAM GOT UNDER A LOOSE TAPE AND LIFTED THE ENTIRE PATCH FROM THE WING INCLUDING RIPPING THE FABRIC CLIPS OUT	 OF THE RIBS.  IT IS FURTHER SPECULATED THE PILOTS PREFLIGHT HAD FAILED TO IDENTIFY A POTENTIAL PROBLEM ARISING FROM A L	OOSE TAPE.  NEW SYS VI DIFFERS FROM THE OLDER PROCESS IN THE TYPE OF BASE PRIMER AND FINISHING PAINT.  CURRENT SYS CALLS	 FOR BRUSHING A COAT OF THINNED U500 ADHESIVE WHERE THE TAPE WILL BE LAID.  THIS IS ALLOWED TO DRY.  TAPE IS THEN LAID D	OWN AND BRUSHED WITH CEMENT, WORKING THE CEMENT UP INTO THE WEAVE OF THE TAPE AND PAYING SPECIAL ATTENTION TO WORKING TH	1	H	7	1 	3O	3	O	NC	A768    	E252				 
2008042800308	20080428	00308	GL  	2008	4	28	2008FA0000259    	1	20080314	G	2780		SLAT SYSTEM     			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A110	 	NE  						MALFUNCTIONED   	D				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			SW	05	917GL					9117				FLIGHT CREW REPORTED THAT SHORTLY AFTER ROTATION (AFTER T/O) THEY HAD A (FLICKERING) SLAT HALF SPD AND SLAT/FLAP HALF SP	D EICAS MESSAGE.  SHORTLY THEREAFTER THEY HAD AN AMBER SLAT FAIL, STALL WARN ADVANCE EICAS MESSAGE, C/B TRIP (E-2 SLAT/F	LAP PWR 2) AND FLIGHT SPOILER FAULT EICAS MESSAGE.  THEY WERE ABLE TO LAND AT HOME BASE WITH SLATS OUT/FLAPS 0, WITHOUT 	INCIDENT (SLATS WERE AVAILABLE, FLAPS WERE NOT AVAILABLE.  THE CAS MESSAGES WERE STILL PRESENT WHEN THEY PARKED THE AC A	ND THE FOLLOWING FDE MESSAGES: RT MFS NR 3 ACTUATOR/WRG 27656232SX; FLT CONT 2B FAULT (FCU 2 27654282SX; FLAP FAIL LATCH	ED FAULT NR1 2751000STD.  TROUBLESHOOTING BY MAINT AND DEBRIEF FROM THE FLT CREW REVEALED A BOTTLE OF DRINKING WATER HAD	2	L	7	2 	4F	4	F	RT	T00003NY	E00057EN				 
2008042800309	20080428	00309	SO  	2008	4	28	2008FA0000260    	2	20080227	G	8530	712BCA	CYLINDER        			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	5421M	544  				402B0021				CRACKED BETWEEN FIN NR1-3, BEHIND INJECTOR.  DEFECTIVE PRODUCT.  (K)						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
2008042800395	20080428	00395	SO  	2008	4	28	2008FA0000261    	2	20080317	G	8520	639193	BUSHING         								CONT  	O520  	TSIO520WB   	17040	SO  					COUNTER WEIGHT	BROKEN          	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19		32   					518853			RECEIVED ENGINE IN AFTER 32.2 HOURS SINCE MAJOR OVERHAUL.  ENGINE WAS DAMAGED BY COUNTERWEIGHT FAILURE ON CRANKSHAFT.  D	AMAGED TO THE CRANKCASE, CYLINDERS AND ROD WAS FROM WHAT APPEARED TO BE A BROKEN COUNTERWEIGHT PIN OR FAILURE OF THE COU	NTERWEIGHT BUSHING.  THE BUSHING WAS FOUND IN SEVERAL PIECES.  (K)									3	O			E8CE				 
2008042800396	20080428	00396	CE  	2008	4	28	2008FA0000262    	1	20080401	G	5410		HINGE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENG COWLING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	XCBCN					BB435	PCE80952			ENGINE ICE VANE HINGE ASSY, BROKEN.  HINGE ASSY BREAKS AND FRAGMENTS INTO SMALL PIECES THAT TEND TO BE INGESTED INTO ENG	INE, CAUSING FOD.  (K)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2008042800386	20080428	00386	EA  	2008	4	28	2008FA0000263    	2	20080403	G	8530	LW12993	CYLINDER        			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					NR 2	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8200M	1311 				328006048	L1642048AC			NR 2 CYL CRACKED FROM UPPER SPARK PLUG HOLE TO THE EXHAUST VALVE SEAT.  CRACK IN HEAD LED TO FAILURE OF EXHAUST PUSHROD 	HOUSING, AND DEFORMATION OF THE EXHAUST PUSHROD.  AC LANDED WITHOUT INCIDENT.  (K)					1	L	7	1 	3O	3	O		A3SO    	1E4				 
2008042800387	20080428	00387	CE  	2008	4	28	2008FA0000264    	1	20080402	G	3710	RA442CW12	PUMP            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					VACUUM SYSTEM	FAILED          	B			PZ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	8050U					TH1657				VACUUM PUMP FAILED TO DEVELOP ANY AIR OUTPUT UPON INSTALLATION.  REMOVED PUMP AND INSPECTED, SUSPECT VANES ARE NOT SLIDI	NG OUT AGAINST CYLINDER WALL THUS NOT ALLOWING ANY AIR TO BE DEVELOPED.  (K)					1	L	7	2 	3O	3	O		3A16    	E3SO				 
2008042800388	20080428	00388	WP  	2008	4	28	2008FA0000265    	2	20080322	G	7230	307241616	COMPRESSOR      			RAYTHN	900   	HAWKER900XP 	4220011	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					ENGINE	SEPARATED       	B			ZN3R	O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			WP	07	897QS	135  				HA0014	P122133			ON CLIMB THROUGH FL140 CREW HEARD BANG FROM RT ENGINE WITH VIBRATION.  RT ITT INCREASED 150C BUT NO OVER TEMP.  REDUCED 	POWER, THEN BROUGHT POWER BACK UP, WITH SAME RESULT.  CREW LANDED WITHOUT INCIDENT AND ENGINE REMOVED AND SENT FOR REPAI	R AND OVERHAUL.  (K)				1	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2008042800389	20080428	00389	CE  	2008	4	28	2008FA0000266    	1	20080409	G	2820	1200406245	FUEL LINE       			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					FUEL SYSTEM	DEFORMED        	B			HP6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	22479	732  				17264066				DURING ANNUAL INSPECTION OF THE MAIN FUEL LINE, BELOW FLOOR, JUST AFT OF FIREWALL, WAS FOUND DEFORMED (TWISTED).  PILOT 	DID NOT REPORT LOW POWER.  (K)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2008042800390	20080428	00390	SW  	2008	4	28	2008FA0000267    	1	20080407	G	5751		RIB             			BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320B2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	RT AILERON	BOWED           	C			V36R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	872JM					42299	L1907339A	AA57931		REMOVED THE RT AILERON DUE TO REPORTS OF BINDING BETWEEN THE AILERON AND WING DURING AEROBATIC MANEUVERS.  ON THE GROUND	 THE IB AILERON TO AILERON BAY RIB CLEARANCE WAS APPROX .0625 INCH.  IAW TECH SUPPORT THE CLEARANCE SHOULD BE .2500 INCH	.  THE WING IB AILERON BAY RIB APPEARED TO HAVE BOWED DUE TO FABRIC SHRINKAGE OVER TIME, CAUSING THE INTERFERENCE.  THE 	IB AILERON RIB FABRIC WAS OPENED, THE RIB WAS RELOCATED OB .1875 INCH, AND THE FABRIC WAS REPAIRED UTILIZING NEW TAPES A	ND THE SUPERFLITE PROCESS.  THE REPAIR WAS PAINTED WITH FLEX AGENT ADDED.  IAW TECH SUPPORT, AILERON BALANCING WAS NOT R	EQUIRED.  REINSTALLED AILERON.  AILERON CLEARANCE AND OPERATION SATISFACTORY.  (K)	1	H	7	1 	3O	3	O		A759    	E274	5	N	P88614	 
2008050800007	20080508	00007	CE  	2008	5	8	2008FA0000268    	1	20080304	G	3800		DRAIN           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					FUSELAGE	PLUGGED         	B			MT9R	O				OTHER                   				S			AFFECT SYSTEMS            			DE	DESCENT        	1			SW	05	9546B					208B0126				DURING FLT IN MODERATE TURBULENCE THE AP STARTED TO DISCONNECT, TWICE.  THIRD ATTEMPT TO ENGAGE THE AP, THE AC MADE AN U	NCOMMANDED 1500 FPM DESCENT.  ATTEMPT TO CORRECT THE ATTITUDE WITH THE CWS FUNCTION WAS MADE BUT THE AP WOULD NOT DISENG	AGE.  THE AP DISCONNECT BUTTON WOULD NOT LET GO EITHER.  HAD TO OVERPOWER THE AP CLUTCHES TO REGAIN CONTROL AND ATTEMPTE	D TO DISCONNECT THE SYS WITH THE C/B, THE AP REMAINED ON AND LIT AFTER PULLED.  RECYCLED THE C/B AND WAS SUCCESSFUL.  TH	IS HAPPENED ON DESCENT, THE SYS HAD BEEN FUNCTIONING NORMALLY PRIOR TO THE INCIDENT.  MX FOUND WATER ACCUMULATED BEHIND 	THE REAR CURTAIN.  THIS IS THE AREA THAT THE PITCH SERVO IS LOCATED.  THEY FOUND THAT THE SERVO HAD A SOLENOID STUCK CLO	1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2008042800394	20080428	00394	NM  	2008	4	28	2008FA0000269    	1	20080401	G	8120	654327	TRANSITION DUCT 			LANCAR	LC41  	LC41550FG   	5150001	NM  	CONT  	O550  	TSIO550C    		SO  					TURBOCHARGER	CRACKED         	B			L9OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	139DC	714  				41056	914313			DURING ANNUAL INSPECTION FOUND TURBO TRANSITION PART OF EXHAUST CRACKED ALL THE WAY THRU FRONT RADIUS OF THE PIPE.  (K)						1	L	7	1 	3O	3	O	NT	A00003SE	E5SO				 
2008050800009	20080508	00009	CE  	2008	5	8	2008FA0000270    	1	20080403	G	3222	07436062	ATTACH FITTING  			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					NLG	CRACKED         	B			7TFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	783WB	1044 				18281512	L3000248			DISCOVERED CRACK DURING ANNUAL INSPECTION.  (2) LONG CRACKS APPROXIMATELY (1) INCH ON (1) SIDE OF THE FITTING ONLY,  (1)	 AT THE LT LOWER ATTACHMENT AND THE OTHER JUST AFT AND LT OF THE AREA WHERE THE STRUT BARREL IS SECURED.  SUSPECT HARD L	ANDING BUT NO OTHER DAMAGE NOTED.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2008050800010	20080508	00010	WP  	2008	5	8	2008FA0000271    	1	20080403	G	2820		LINE            			HUGHES	269   	269C        	4470504	WP  										FUEL SYSTEM	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	111AB	5    	5    			S1911				FUEL LEAKING FROM GASCOLATOR INLET LINE, APPROX 5.0 HRS SINCE NEW.  (K)						1	G	7	1 	3O				4H12    					 
2008050800011	20080508	00011	CE  	2008	5	8	2008FA0000272    	1	20080112	G	5280	3901104580007	DOOR            			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					LT MLG	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	7088S	264  				RB188				AFTER ROUTINE FLIGHT, THE PILOT WAS PERFORMING HIS PREFLIGHT WALKAROUND INSP IN PREPARATION FOR THE NEXT LEG OF THE FLIG	HT.  HE NOTICED THAT BOTH MLG OUTER DOORS WERE DAMAGED.  MECHANIC/MAINT WENT TO EVALUATE THE DAMAGE TO THE DOORS.  RECOM	MENDED THAT THE AIRPLANE BE FLOWN BACK UNDER SPECIAL FLIGHT PERMITS.  THE DOORS WERE EVALUATED BY MAINT AND QUALITY DEPT	, AS WELL AS TECH REP, DETERMINED UNREPAIRABLE.  NEW DOORS WERE ORDERED, RECEIVED, INSTALLED, RIGGED AND TESTED SATISFAC	TORILY.  AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM.  (K)		1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
2008050800012	20080508	00012	CE  	2008	5	8	2008FA0000273    	1	20080112	G	5280	390110458008	DOOR            			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					RT MLG	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	7088S	264  				RB188				AFTER ROUTINE FLIGHT, THE PILOT WAS PERFORMING HIS PREFLIGHT WALKAROUND INSP IN PREPARATION FOR THE NEXT LEG OF THE FLIG	HT.  HE NOTICED THAT BOTH MLG OUTER DOORS WERE DAMAGED.  MECH/ MAINT WENT TO EVALUATE THE DAMAGE TO THE DOORS.  RECOMMEN	DED THAT THE AIRPLANE BE FLOWN BACK UNDER SPECIAL FLIGHT PERMITS.  THE DOORS WERE EVALUATED BY MAINT AND QUALITY DEPT, A	S WELL AS TECH REP, DETERMINED UNREPAIRABLE.  NEW DOORS WERE ORDERED, RECEIVED, INSTALLED, RIGGED AND TESTED SATISFACTOR	ILY.  AC HAS SINCE BEEN RETURNED TO SERVICE WITH NO FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM.  (K)		1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
2008050800014	20080508	00014	CE  	2008	5	8	2008FA0000274    	1	20080128	G	5280	3901104500017	DOOR            			RAYTHN	390   	390         	7150030	CE  										LT MLG	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	34GN	1121 				RB58				THE PILOT WAS INFORMED BY THE FUEL TRUCK DRIVER THAT THE LT MLG IB DOOR WAS NOT PROPERLY LOCKED IN THE UP POSITION, AND 	THE OB PORTION OF THE DOOR HAD MADE CONTACT WITH THE RUNWAY DURING LANDING.  ENGINEERING DEPT RECOMMENDED THAT THE AIRPL	ANE BE FLOWN BACK UNDER THE AUSPICES OF FAR PART 21.197, SPECIAL FLIGHT PERMITS.  THE DOOR WAS EVALUATED BY MAINT AND QU	ALITY DEPT, AS WELL AS BY THE LOCAL TECH REP, AND DETERMINED UNREPAIRABLE.  AC HAS SINCE BEEN RETURNED TO SERVICE WITH N	O FURTHER INCIDENTS WITH THE LANDING GEAR SYSTEM.  (K)		1	L	7	2 	3F			RT	A00010WI					 
2008050800015	20080508	00015	CE  	2008	5	8	2008FA0000275    	1	20080128	G	3297		WIRE            			RAYTHN	390   	390         	7150030	CE  										LT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	34GN					RB58				AFTER LANDING, THE PILOT WAS INFORMED BY FUEL TRUCK DRIVER THAT LT MLG IB DOOR WAS NOT PROPERLY LOCKED IN THE UP POSITIO	N, AND THE OB PORTION OF THE DOOR HAD MADE CONTACT WITH THE RUNWAY DURING LANDING.  ENGINEERING DEPT RECOMMENDED THAT TH	E AC BE FLOWN BACK UNDER AUSPICES OF FAR PART 21.197, SPECIAL FLIGHTS PERMITS.  THE DOOR WAS EVALUATED BY MAINT, QUALITY	 DEPT, AND BY TECH REP, AND DETERMINED UNREPAIRABLE.  ADDITIONAL TROUBLESHOOTING REVEALED THAT WIRING FOR THE UPLOCK MIC	ROSWITCH WAS BROKEN, AND IT WAS THIS BROKEN WIRING THAT CAUSED THE MICROSWITCH TO FAIL TO ALLOW THE UPLOCK TO PROPERLY E	NGAGE THE LOCKING LUG  ON THE DOOR.  MICROSWITCH AND A NEW LT MLG IB DOOR WERE ORDERED RECEIVED, INSTALLED, RIGGED AND T	1	L	7	2 	3F			RT	A00010WI					 
2008042800324	20080428	00324	GL  	2008	4	28	2008FA0000278    	1	20080415	G	2100		VALVE           			DIAMON	DA40  	DA40        	2990002	GL  	CONT  	IO360 	IO360*      	17025	CE  						LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	105UV					40685	L3277551A			THE ALTERNATE AIR VALVE IS VIBRATING AND CAUSING FRETTING BETWEEN THE INLET RING, PN D41-7166-20-31 AND FLANGE, PN D41-7	166-20-33. THE "DUST" IS BEING INGESTED INTO THE FUEL CONTROL SERVO AND ENGINE. THERE NEEDS TO BE A TIGHTER FIT BETWEEN 	THESE PARTS.				1	L	7	1 	3O	3	O	NT	A47CE   	E1CE				 
2008042800327	20080428	00327	EA  	2008	4	28	2008FA0000280    	2	20080112	G	8550	16991000327	HOSE            			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4G     	41514	EA  					OIL COOLER	LEAKING         	G				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			EA	17	2102W		26   			M1429	L1673536A			THE AC EXPERIENCED AN EMERGENCY LANDING AFTER THE PILOT REPORTED SMOKE IN THE COCKPIT.  INSP AND INVESTIGATION REVEALED 	AN OIL COOLER LINE HAD BEEN MAKING CONTACT WITH THE NR4 EXHAUST STACK (RISER), EVENTUALLY CAUSED THE FIRE SHEATHING AND 	OIL LINE TO DETERIORATE, CAUSING THE OIL TO LEAK INTO THE HEAT EXCHANGER, WHICH CAUSED SMOKE IN THE COCKPIT OBSERVED BY 	THE PILOT.  UPON INSP, ALL BUT 16 OZ OF OIL LEAKED OUT OF ENGINE, WELL BELOW THE MINIMUM SAFE QUANTITY FOR THE MODEL INS	TALLED ON THIS AC.  PILOT IN THIS CASE WAS ABLE TO KEEP OIL PRESSURE UPON LANDING, THUS AVOIDING A POTENTIALLY SERIOUS S	ITUATION.  AS A RESULT OF THIS OCCURRENCE, ENGINE HAD TO BE DISASSEMBLED, CLEANED, INSPECTED, REPAIRED AS NECESSARY, AND	1	L	7	1 	3O	3	O		A1CE    	E286				 
2008042800328	20080428	00328	CE  	2008	4	28	2008FA0000281    	1	20080416	G	7120	051313211	MOUNT           			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					LT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	6620E	1927 	723  			56120				INSP FOUND UPPER LT BRACKET (0513132-11) WITH A SMALL CRACK ORIGINATING FROM THE LOWER EDGE OF THE ENGINE MOUNT BOLT WAS	HER.  ONLY A SMALL BEND LINE WAS VISIBLE FROM THE COCKPIT SIDE OF THE BRACKET VIA BOROSCOPE.  AFTER REMOVAL OF THIS BRAC	KET A CRACK WAS CLEARLY VISIBLE ON THE ENGINE SIDE OF BRACKET. FOUND UPPER RT BRACKET WITH (3) CRACKS SEPARATING THE BRA	CKET INTO 4 PIECES.  THE THRESHOLD FOR THIS INSP SHOULD BE REDUCED FROM 2500 HRS.  A MORE FREQUENT BOROSCOPE INSP WITHOU	T REMOVAL OF THE ENGINE TRUSS MOUNT BOLTS WOULD PROVIDE AN EQUAL LEVEL OF SAFETY AS LONG AS A LARGER AREA WASHER HAS NOT	 BEEN INSTALLED.  INSTALLATION OF A LARGER AREA WASHER MAY REDUCE THE STRESS POINT AND IMPROVE THE LIFE OF THE BRACKET.	1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2008050800051	20080508	00051	EA  	2008	5	8	2008FA0000285    	1	20080402	G	2822	1D217	PUMP            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FUEL SYSTEM	FAILED          	B			SCIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	359AR					359				BOOST PUMP FAILS AT 11,000 TO 12,000 FT OF ALTITUDE.  WORKS FINE ON GROUND.  (K)						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2008050800052	20080508	00052	EA  	2008	5	8	2008FA0000286    	2	20080414	G	8530	AEL61247	COVER           			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	98874	632  				17276370	L1379939A	EF023		FOUND ROCKER BOX COVER WITH MULTIPLE CRACKS DURING AC FLEET INSPECTION, FOLLOWING DISCOVERY OF ANOTHER CRACKED COVER ON 	A DIFFERENT AC.  CRACKS CAUSED, DUE TO IMPROPER CLEARANCE BETWEEN COVER AND ROCKER ARMS ALLOWING ROCKER ARMS TO CONTACT 	COVER.  THERE IS A NOTABLE CLEARANCE DIFFERENCE BETWEEN ORIGINAL MFG COVER AND THE OTHER MFG COVER AT THE LOWER PORTION 	OF THE COVER.  RECOMMEND REPLACEMENT OF ALL SS COVERS PN AEL61247 WITH ORIGINAL MFG OR SUITABLE SUBSTITUTE.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2008050800054	20080508	00054	EA  	2008	5	8	2008FA0000287    	2	20080414	G	8530	AEL61247	COVER           			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	63450	191  				17275434	L1420839A	TK039		FOUND ROCKER BOX COVER CRACKED DURING 100 HOUR INSPECTION.  CRACKS CAUSED DUE TO IMPROPER CLEARANCE BETWEEN COVER AND RO	CKER ARMS ALLOWING ROCKER ARMS TO CONTACT COVER.  THERE IS A NOTABLE CLEARANCE DIFFERENCE BETWEEN AN  ORIGINAL MFG COVER	 AND THE OTHER MFG COVER AT THE LOWER PORTION OF THE COVER.  (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2008050800064	20080508	00064	CE  	2008	5	8	2008FA0000288    	1	20080401	G	5712	12210628	BULKHEAD        			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360*       	41514	EA  					RT WING	CRACKED         	B			H5GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	99NA	6339 				17702697				DURING ROUTINE INSPECTION, FOUND PART CRACKED.  CHECKED (2) OTHER CARDINALS THAT HAPPENED TO BE IN OUR SHOP AND FOUND (1	) OF THEM TO HAVE A SIMILAR CRACK.  THIS SECTION OF THE BULKHEAD IS THE ATTACH STRUCTURE FOR THE LOWER ATTACH ANGLE FOR 	THE IB FLAP DRIVE BELLCRANK.  IT IS CURIOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN	 THIS POSITION IN THE LT WING.  THERE ARE EVEN SOME (PILOT DRILL) (PD) HOLES DRILLED AT THE FACTORY IN THE RIB AND HEAVY	 ATTACH ANGLE ON THE AFFECTED RT SIDE.  IT WOULD APPEAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE THE SAME FORE-AF	T FORCES BY AIR LOADS ON THE FLAPS.  SO WHY REINFORCE ONLY ONE SIDE? IS IT POSSIBLE THAT THE FACTORY ASSY LINE NEGLECTED	1	H	7	1 	3O	3	O		A13CE   	E286				 
2008050800065	20080508	00065	CE  	2008	5	8	2008FA0000289    	1	20080401	G	5712	12210628	BULKHEAD        			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					RT WING	CRACKED         	B			H5GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	52543	4336 				177RG1206				DURING ROUTINE INSP, FOUND PART CRACKED.  CHECKED (2) OTHER CARDINALS THAT HAPPENED TO BE IN OUR SHOP AND FOUND (1) OF T	HEM TO HAVE A SIMILAR CRACK.  THIS SECTION OF THE BULKHEAD IS THE ATTACH STRUCTURE FOR THE LOWER ATTACH ANGLE FOR THE IB	 FLAP DRIVE BELLCRANK.  IT IS CURIOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS 	POSITION IN THE LT WING.  THERE ARE EVEN SOME (PILOT DRILL) (PD) HOLES DRILLED AT THE FACTORY IN THE RIB AND HEAVY ATTAC	H ANGLE ON THE AFFECTED RT SIDE.  IT WOULD APPEAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE THE SAME FOR-AFT FORCE	S BY AIR LOADS ON THE FLAPS.  SO WHY REINFORCE ONLY ONE SIDE?  IS IT POSSIBLE THAT THE FACTORY ASSY LINE NEGLECTED TO IN	1	H	7	1 	3O	3	O		A20CE   	1E10				 
2008050800059	20080508	00059	EU  	2008	5	8	2008FA0000290    	1	20080423	G	3210	DIN47108VERZ	FASTENER        	DIAMON      		DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE1250299  		EU  					MLG	MISSING         	B			NX4S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	966WW	179  	79   			42106				DURING PREFLIGHT, THE CREW NOTICED THAT THE SMALL CIRCLIP (PN DIN471-08-VERZ) THAT SECURES THE MLG DOWNLOCK HOOK PIN IN 	POSITION WAS MISSING. MAINT JACKED THE AC AND INSTALLED A NEW CLIP. WHEN THIS CLIP IS NOT IN PLACE, THE PIN MIGRATES AFT	 AND IN SOME CASES DAMAGES THE AFT LIP OF THE WHEEL WELL MATERIAL. THIS OPERATOR HAS 9 OF THESE AIRPLANES AND THERE HAVE	 BEEN OTHER INSTANCES OF THIS DISCREPANCY.			1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2008050800089	20080508	00089		2008	5	8	2008FA0000291    	4	20080424	G	3425	011N097200	UNKNOWN         			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540*     	41532	EA  					COCKPIT	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	488PJ	75   				T18208333				WHEN TURNING THE (CRS) COURSE KNOB, THE INNER KNOB (BARO) BAROMETRIC PRESSURE KNOB WOULD TURN ALSO.  CHANGING THE ALTITU	DE INDICATED.					1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2008050800067	20080508	00067	EA  	2008	5	8	2008FA0000292    	2	20080423	G	7414		CAM             	SLICK       		PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					MAGNETO	WORN            	C			UXCR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	05	855P	49   			07100592	4692014	L1291661A			BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW.  TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICUL	T TO START.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
	20080707		EA  	2008	7	7	2008FA0000293    	2	20080423	G	7414		CAM             	SLICK       		PIPER 	PA46  	PA46R350T   	7104610	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					MAGNETO	WORN            	C			UXCR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	05	855P	49   			07100592	4692014	L1291661A			BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW.  TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICUL	T TO START.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
	20080707		EA  	2008	7	7	2008FA0000294    	2	20080423	G	7414		CAM             	SLICK       		PIPER 	PA46  	PA46R350T   	7104610	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					MAGNETO	WORN            	C			UXCR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	05	855P	49   			07100592	4692014	L1291661A			BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW.  TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICUL	T TO START.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
	20080707		EA  	2008	7	7	2008FA0000295    	2	20080423	G	7414		CAM             	SLICK       		PIPER 	PA46  	PA46R350T   	7104610	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					MAGNETO	WORN            	C			UXCR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	05	855P	49   			07100592	4692014	L1291661A			BREAKER CAM WORN BEYOND SERVICEABLE LIMITS, 49.9 HOURS SINCE NEW.  TIMING HAD CHANGED CONSIDERABLY AND AIRCRAFT DIFFICUL	T TO START.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2008050800109	20080508	00109		2008	5	8	2008FA0000296    	4	20080425	G	3425	011N097200	UNKNOWN         			CESSNA	182   	T182        	2072736	CE  	LYC   	O540  	TIO540*     	41532	EA  					COCKPIT	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	488PJ	75   				T18208333				WHEN TURNING THE INNER "CRS" COARSE KNOB THE OUTER "BARO" BAROMETRIC PRESSURE KNOB WOULD TURN ALSO. CHANGING THE ALTITUD	E.					1	L	7	1 	3O	3	O		3A13    	E14EA				 
2008050800117	20080508	00117		2008	5	8	2008FA0000297    	2	20080426	G	8550		ADAPTER         																	OIL SYSTEM	MISMANUFACTURED 	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	15										ORDERED SPIN ON OIL FILTER ADAPTER MODEL NR (TAFL).  MACHINED PART WAS NOT COMPLETELY FINISHED.  AN IMPORTANT HOLE IN TH	E OIL PASSAGE DID NOT CONNECT WITH THE OIL DELIVERY LINE BECAUSE IT WASN'T DRILLED DEEP ENOUGH.  MFG HAS BEEN COOPERATIV	E AND AGREES TO REPLACE, HOWEVER IF ANY OF THESE DEFECTIVE PARTS HAVE BEEN INSTALLED IN THIS CONDITION, ENGINE FAILURE C	OULD RESULT.  (SN 28653L)																 
200805141    	20080514	1    	CE  	2008	5	14	2008FA0000300    	1	20080422	G	5312	45A3490111	BULKHEAD        			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					FUSELAGE	CRACKED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	400SF					RK221				WHILE PERFORMING AN (A-B) INSPECTION FOUND RT AFT FUSELAGE BLEED AIR LINE ATTACH BRACKETS PULLED FROM AFT FUSELAGE BULKH	EAD RESULTING IN CRACKS IN THE BULKHEADS AT FRAME STA 329.92.  RECOMMEND INSPECTING AREA THOROUGHLY AT EACH INSPECTION. 	 RECOMMEND CONTACTING MFG FOR REPAIR OPTIONS.  THIS IS THE 5TH AIRCRAFT IN A ROW THAT THE BULKHEAD HAS BEEN CRACKED.  TH	E CRACK HAS BEEN FOUND ON BOTH SIDES OF THE AC.  (K)			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
200805141    	20080514	1    	SO  	2008	5	14	2008FA0000301    	1	20080418	G	7160	U086126	MUFF            			LUSCOM	8     	8E          	8190112	SO  	CONT  	C85   	C8512F      	17008	SO  					RT CARB	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2004	561  				5937	2244612C			AFTER A FLIGHT, IT WAS NOTED THAT A PORTION OF SCAT HOSE WAS HANGING FROM THE BOTTOM OF COWLING OPENING.  UPON INSPECTIO	N IT WAS FOUND THAT THE CARBURETOR HEAT FLANGE HAD SEPARATED WITH THE SCAT HOSE ATTACHED WITH CLAMP FRO THE IB HALF OF T	HE RT CARB HEAT MUFF.  THE CARB HEAT MUFF HALVES WERE REMOVED AND INSPECTED.  EXAMINATION OF THE FAILED ROUND DUCT FLANG	E FOUND THE ENTIRE TUBE BROKE OFF AT THE CIRCUMFERENCE ALONG THE EDGE OF THE WELD.  SECONDLY, THERE WERE ABOUT (6) SPIDE	R LIKE CRACKS AROUND THE BROKEN HOLE WHICH PROPAGATED OUTWARD.  A TOTAL OF APPROX 16 CRACKS, BROKEN TABS INCLUDING A PRE	VIOUS (PATCH) REPAIR WERE NOTED ON BOTH IB AND OB MUFF HALVES.  AN INNER MUFF RIB WHICH WAS TACK WELDED IN (3) PLACES HA	1	H	7	1 	3O	3	O		A694    	E233				 
	20080520		CE  	2008	5	20	2008FA0000302    	1	20080419	G	7921	649964	GASKET          			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520*      	17032	SO  					OIL COOLER	FAILED          	D				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			SW	09	132WB	140  				21060114	295375R			THE OIL COOLER ADAPTER GASKET TAILED IN FLIGHT CAUSING (2) QUARTS OF OIL IN ONE HOUR TO BE PUMPED INTO THE ENGINE COWLIN	G.  THIS ENGINE IS A FACTORY REMANUFACTURED ENGINE WITH 140 HOURS SINCE REMAIN.  ON INSPECTION AND DISASSEMBLY THE OIL C	OOLER ADAPTER BOLTS DID NOT APPEAR TO BE TORQUED ENOUGH BUT THE GASKET ITSELF WAS BRITTLE AND LEAKING.  THE ENGINE AND A	DAPTER SURFACE WERE FLAT AND CLEAN.  THE REPLACEMENT GASKET APPEARS TO BE A BETTER QUALITY.  (K)			1	H	7	1 	3O	3	O		3A21    	E5CE				 
	20080520		SO  	2008	5	20	2008FA0000303    	1	20080421	G	3222	86280003	DRAG LINK       			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NOSE GEAR	CRACKED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5328L					4496108				NOSE GEAR DRAG LINK (PN 86280-003) CRACK LOCATED IN PIVOT BOLT HOUSING ON DRAG LINK WHERE A STANDARD (AN175-22A) BOLT AT	TACHES NOSE GEAR DOWN LOCK (PN 86275-004).  PROBABLE FATIGUE CRACK FROM NORMAL CYCLE TIME ON GEAR.  RECOMMEND VISUAL INS	P OF AREA AT A SPECIFIC PERIOD OF TIME TO BE DETERMINED BY THE MFG.  (K)				1	L	7	2 	3O	3	O		A19S0   	E286				 
	20080520			2008	5	20	2008FA0000304    	4	20080125	G	2300	G6860113	CONTROL HEAD    			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	BURNED          	D				G				O2 MASK DEPLOYED        				O			OTHER                     			DE	DESCENT        	1			SO	15	970S					238				DURING NORMAL DESCENT, AT JUST PRIOR TO 18000 FT, CREW NOTICED DISTINCT BURNING ELECTRICAL ODOR, OXY MASK PULLED AND THE	 SMOKE CHECKLIST WAS RUN.  EMERGENCY PRIORITY REQUESTED UPON ARRIVAL, POSSIBLE LIGHT SMOKE IN COCKPIT ONLY WITH NONE IN 	THE CABIN.  IN LESS THAN (1) MINUTE THE ODOR WAS NOT INCREASING AND SUBSEQUENTLY BEGAN TO CLEAR.  THROUGH 10000 FT IT WA	S NOTED THAT THE NR 2 NAV CONTROL HEAD WAS BLANK AND SUSPECTED AS THE PROBABLE CAUSE AS IT WAS CLOSE TO THE STRONGEST SM	ELL.  NO CIRCUIT BREAKERS POPPED.  REMOVAL OF UNIT NAV/COM CONTROL HEAD (PN G6860113 SN298)  NOTED ELECTRICAL BURNED SME	LL WITH UNIT.  PART HAS 9 HOURS SINCE REPAIR/MODIFICATION.  UNIT TO BE SENT BACK FOR REPAIR.  (K)	2	L	7	3 	4F	4	F		A46EU   	E6WE				 
200805141    	20080514	1    	CE  	2008	5	14	2008FA0000305    	1	20080429	G	3246	FN22A524	NUT             			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					WHEEL	MISMANUFACTURED 	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01	733A					258687				WHEEL LOCK NUT (P/N FN22A-524) WAS BEING INSTALLED TO COMPLY WITH SB 32-1374 AND WAS FOUND TO HAVE ZERO RUN ON TORQUE. T	HIS IS A NEW PART AND HAS NEVER BEEN INSTALLED. ONLY ONE OF 24 BOUGHT FROM MFG THAT WAS BAD. THIS BOLT/NUT COMBINATION I	S WHAT HOLDS THE (2) HALVES OF THE WHEEL TOGETHER.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
	20080520		EU  	2008	5	20	2008FA0000306    	1	20080501	G	3520	17408031	OXYGEN MASK     			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN	COLLAPSED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15										DURING AN OPS INSPECTION OF THE PASSENGER OXYGEN DROP DOWN MASKS, THERE WAS ONE THAT WOULD NOT LET OXYGEN FLOW THRU THE 	CONNECTION BETWEEN THE LARGER LINE ATTACHED TO THE BARBED FITTING ON THE OXYGEN DROP DOWN BOX AND THE SMALLER LINE THAT 	GOES TO THE MASK. IN THIS CASE THE SMALLER LINE WAS SQUEEZED SHUT AND WOULD NOT ALLOW OXYGEN TO FLOW TO THE MASK. THE PN	 IN QUESTION IS A 174080-31 REV "K".			2	M	7	2 	4F	4	F		A2SW    	E6WE				 
	20080520		GL  	2008	5	20	2008FA0000307    	1	20080225	G	7921	646880	OIL COOLER      			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  						WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	476DA	300  								THE OIL COOLER SUPPORT SHOE RUBBER COATING IS FAILING AND EATING INTO THE OIL COOLER .020 TO .040 OF AN INCH.  IAW MM IT	 IS INSTALLED AT ENGINE ASSY AND ADJUSTED AFTER INITIAL TEST RUN. THERE IS NO PUBLISHED IN SERVICE INSTRUCTION FOR IT. I	F THIS CONDITION IS NOT ADDRESSED BY REPLACEMENT OF SHOE AND OIL COOLER THE POSSIBILITY OF LOSS OF ENGINE OIL IS HIGH. T	HE 5 AIRCRAFT THAT WE HAVE FOUND, ON THOSE AC THE OIL COOLER HAD TO BE REPLACED. IN ADDITION TO THAT WE HAVE TO REPLACE 	18 OIL COOLER SHOE'S PN 632983. THE FAILURE TIME FROM NEW TO HAVING WORN INTO THE ENGINE OIL COOLER IS LESS THEN 600HRS 	TTAF. THIS IS DUE TO THE RUBBER PORTION OF SHOE FAILING AND ALLOWING THE STEEL PART TO CUT INTO THE OIL COOLER.	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
	20080520		EU  	2008	5	20	2008FA0000308    	1	20080501	G	3520	17408031	OXYGEN MASK     			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN	COLLAPSED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15										DURING AN OPS INSPECTION OF THE PASSENGER OXYGEN DROP DOWN MASKS, THERE WAS ONE THAT WOULD NOT LET OXYGEN FLOW THRU THE 	CONNECTION BETWEEN THE LARGER LINE ATTACHED TO THE BARBED FITTING ON THE OXYGEN DROP DOWN BOX AND THE SMALLER LINE THAT 	GOES TO THE MASK. IN THIS CASE THE SMALLER LINE WAS SQUEEZED SHUT AND WOULD NOT ALLOW OXYGEN TO FLOW TO THE MASK. THE PN	 IN QUESTION IS A 174080-31 REV "K".			2	M	7	2 	4F	4	F		A2SW    	E6WE				 
2008050800001	20080508	00001	SO  	2008	5	8	2008FA0000309    	1	20080507	G	2720	2223900	TORQUE TUBE     			PIPER 	PA24  	PA24260     	7102406	SO  										RUDDER CONTROL	BROKEN          	B				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	05	9506P	3404 				245023				DURING MAINTENANCE RUNUP AND TAXI CHECK AFTER MAINTENANCE THE LEFT RUDDER TORQUE TUBE BROKE OFF. IT APPEARED TO HAVE BEE	N CRACKED FOR SOME TIME PRIOR TO FAILING DURING TAXI.  IT IS SUGGESTED THAT THE AREA BE CLEANED AND INSPECTED WITH A 10X	 MAGNIFYING GLASS. A BORESCOPE WITH A SIDE VIEW END COULD ALSO BE INSERTED IN THE TUBE TO INSPECT IT FROM THE INSIDE. IF	 THIS HAD HAPPENED DURING LANDING AND HAD BROKEN AT INITIAL BRAKE APPLICATION, THE AIRCRAFT WOULD PROBABLY HAVE DEPARTED	 THE RUNWAY.		1	L	7	1 	3O				1A15    					 
	20080522		NE  	2008	5	22	2008FA0000310    	2	20080506	G	7200	0319008000	ENGINE          			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIUS2F    	60010	NE  						MAKING METAL    	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			DE	DESCENT        	1			SO	07	197CB	278  	84   			1448	34546			ENGINE CHIP DETECTOR LIGHT ILLUMINATED.  INSPECTED CHIP DETECTORS, AND FOUND METAL SLIVERS ON MODULE NR 1 CHIP DETECTOR.	 ENGINE REMOVED FROM SERVICE.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
	20080522		NE  	2008	5	22	2008FA0000311    	2	20080502	G	7261		LINE            			AEROSP	SA365 	SA365N1     	8680668	EU  	TMECA 	ARRIEL	ARRIEL2C    	60054	NE  					P2 OIL	LOOSE           	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	NR	NOT REPORTED   	1			EA	07	95MD	2551 	50   			6320	24072			ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNIN	G LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED.					1	G	7	2 	3U	4	U		H10EU   	E00054EN				 
	20080522		NE  	2008	5	22	2008FA0000312    	2	20080502	G	7261		LINE            			AEROSP	SA365 	SA365N1     	8680668	EU  	TMECA 	ARRIEL	ARRIEL2C    	60054	NE  					P2 OIL	LOOSE           	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	NR	NOT REPORTED   	1			EA	07	95MD	2551 	50   			6320	24072			ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNIN	G LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED.					1	G	7	2 	3U	4	U		H10EU   	E00054EN				 
	20080522		NE  	2008	5	22	2008FA0000313    	2	20080502	G	7261		LINE            			AEROSP	SA365 	SA365N1     	8680668	EU  	TMECA 	ARRIEL	ARRIEL2C    	60054	NE  					P2 OIL	BACKED OUT      	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	NR	NOT REPORTED   	1			EA	07	95MD	2551 	50   			6320	24072			ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNIN	G LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED.					1	G	7	2 	3U	4	U		H10EU   	E00054EN				 
	20080522		NE  	2008	5	22	2008FA0000314    	2	20080502	G	7261		LINE            			AEROSP	SA365 	SA365N1     	8680668	EU  	TMECA 	ARRIEL	ARRIEL2C    	60054	NE  					P2 OIL	BACKED OUT      	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	NR	NOT REPORTED   	1			EA	07	95MD	2551 	50   		NA	6320	24072			ENGINE NR2 P2 LINE TO THE M5 MODULE WORKED LOOSE INFLIGHT RESULTING IN A LOSS OF OIL PRESSURE WITH THE ASSOCIATED WARNIN	G LIGHT LOGIC. ENGINE NR2 WAS SHUTDOWN BY THE PILOT AND A UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED.					1	G	7	2 	3U	4	U		H10EU   	E00054EN				 
	20080602		CE  	2008	6	2	2008FA0000317    	1	20080506	G	3246	10320400AN53	BOLT            	PARKERHANFIN		RAYTHN	36    	G36         	7150061	CE  										ZONE 700	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	222GL	479  	479  			E3763				THE PILOT REPORTED A "POP" AS HE WAS GROUND HANDLING THE AIRCRAFT ON THE RAMP (IN A STRAIGHT DIRECTION USING AN AIRTUG).	  FURTHER INVESTIGATION REVEALED 1 NUT/BOLT COMBINATION HAD SHEARED ON THE INBOARD WHEEL HALF OF THE RIGHT MAIN LANDING 	GEAR ASSEMBLY.  THE BOLT HAD SUBSEQUENTLY BACK OUT APPROXIMATELY 1/4 INCH.  THIS AIRCRAFT HAS BEEN THROUGH 1 ANNUAL INSP	ECTION AND HAS NEVER HAD THE WHEEL HALVES DISASSEMBLED.  UPON DISCOVERY OF THE SHEARED BOLT, THE LEFT AND RIGHT WHEELS W	ERE DISASSEMBLED, CLEANED, INSPECTED AND REASSEMBLED WITH NEW BOLTS AND NUTS.  DURING DISASSEMBLY OF THE WHEEL HALF RETA	INING BOLTS IT WAS NOTED THAT VERY LITTLE FORCE WAS REQUIRED TO BREAK THE NUTS LOOSE.  THE NOSE WHEEL WAS THEN CHECKED F	1	L	7	1 	3O			RT	3A15    					 
	20080603		EA  	2008	6	3	2008FA0000318    	2	20080422	G	8520	13B27134	CRANKSHAFT      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			UC2R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	19	4149T					2843192				AC WAS FLYING AT 5000 FT, WHEN ENGINE STARTED TO LOSE POWER AND FAILED.  AC LANDED SAFELY IN A FIELD.  ENGINE WAS FOUND 	TO BE LOCKED UP.  ENGINE WAS DISASSEMBLED AND COMPONENTS INSPECTED.  CRANKSHAFT WAS FOUND TO HAVE CRACK, CAUSING ENGINE 	TO LOCK UP.  PROBABLE CAUSE: UNDERTERMINED AT THIS TIME.  (K)				1	L	7	1 	3O	3	O		2A13    	E286				 
	20080603		CE  	2008	6	3	2008FA0000320    	1	20080425	G	5100	S34691	BEARING         			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	ACTUATOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	52156	4247 			1533	177RG1180	L1699351A	771391		WHERE THE ROD END BEARING ATTACHES TO THE LATERAL BOLT, FWD.  THIS BEARING (S34691 FAILED AT THE BEARING END.  THIS BEAR	ING IS UNDER EXTREEM TENSION LOAD AND WAS ORIGINAL.  AGE WAS A FACTOR IN FAILING.  REPLACING THIS BEARING AT 1000 HR INT	ERVALS IS NECESSARY.  DATE OF THE ACTUATOR WAS 10/77.  (K)				1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
2008051500001	20080515	00001	CE  	2008	5	15	2008FA0000321    	1	20080425	G	5711	00011001316	SPAR CAP        	BEECH       		BEECH 	90    	E90         	1152914	CE  										RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	692M	8812 	400  			LW228				THE CRACK EMANATES FROM THE 5TH RIVET OUTBOARD OF THE LOWER FORWARD WING BOLT FITTING, (4TH RIVET FROM END OF SPAR CAP)I	N THE REAR ROW OF RIVETS, & EXTENDS TO THE TRAILING EDGE OF CAP. THE A/C PASSED 2-400 HR WING SIRM INSPECTIONS. THE CRAC	K WAS DETECTED AT THE CURRENT 400 HR INTERVAL WING SIRM INSPECTION. NOTE:BEECH HAS REDUCED INTERVAL FOR EDDY CURRENT INS	PECTION ITEM OF SPAR CAP TO 200 HRS DUE TO RECURRENCE OF THIS PROBLEM. REF 8110-4 FOR N776DC FOR SIMILAR DETAILS. A/C IS	 ON USFS CONTRACT.		1	L	7	2 	3T				3A20    					 
	20080602		SO  	2008	6	2	2008FA0000322    	1	20080505	G	8010	701122223	SOLENOID        			PIPER 	PA28  	PA28161     	7102803	SO  										STARTER	SHORTED         	B				H				DEACTIVATE SYST/CIRCUITS				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			GL	21	238ND	817  				2842101				WHEN MASTER SWITCH TURNED ON PROP BEGAN TO ROTATE UNCOMMANDED.  TROUBLESHOT TO STUCK STARTER SOLENOID.  SOLENOID REPLACE	D, OPS CHECK GOOD.					1	L	7	1 	3O				2A13    					 
	20080602		SW  	2008	6	2	2008FA0000323    	1	20080504	G	2720	183M	SLEEVE          			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2D     	41508	EA  					RUDDER CABLE	CRIMPED         	D				A				UNSCHED LANDING         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	03	53718					86775				RIGHT RUDDER CABLE SEPARATED AT RUDDER BELLCRANK DURING RECOVERY OF INTENTIONAL LEFT SPIN.  CABLE APPARENTLY PULLED OUT 	OF NICOPRESS SLEEVE.  AIRPLANE WAS LANDED AT KCHA, WITHOUT INCIDENT, AFTER DECLARING AN EMERGENCY.					1	H	7	1 	3O	3	O	NC	A759    	E274				 
	20080602		SW  	2008	6	2	2008FA0000324    	1	20080507	G	3110	011097203	DISPLAY         			BBAVIA	7     	7DC         	2110116	SW  										INSTRUMENT PANEL	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	555Y	93   				7DC2078				PRIMARY FLIGHT DISPLAY PANEL HAS A MALFUNCTION IN THE COARSE/BAROMETRIC PRESSURE ADJUSTMENT KNOB.  THE DESIGN INCORPORAT	ES A DUAL FUNCTION TYPE CONTROL KNOB.  THE CENTER KNOB ADJUSTS THE DESIRED NAVIGATIONAL COARSE DISPLAYED ON THE HSI NAV 	DISPLAY.  THE OUTER KNOB ADJUSTS THE PRIMARY ALTIMETER BAROMETRIC PRESSURE SETTING.  AT TIMES DURING FLIGHT ADJUSTMENT O	F THE INNER COARSE KNOB RESULTS IN AN INADVERTENT CHANGE IN THE BAROMETRIC PRESSURE.  THIS MALFUNCTION CAN BE QUITE DANG	EROUS, ESPECIALLY WHEN SHOOTING AN INSTRUMENT APPROACH, PILOT CHANGES COARSE HEADING DURING AN APPROACH AND MAY, WITHOUT	 KNOWING, CHANGE THE BAROMETRIC PRESSURE THUS CAUSING THE ALTITUDE DISPLAY TO BE INACCURATE.	1	H	7	1 	3O				A759    					 
	20080602		CE  	2008	6	2	2008FA0000326    	1	20080425	G	5711	00011001316	SPAR CAP        			BEECH 	90    	E90         	1152914	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	776DC	8204 	181  			LW235				THE CRACK EMANATES FROM THE 5TH RIVET OUTBOARD OF THE LOWER FORWARD WING BOLT FITTING, 4TH RIVET FROM END OF SPAR CAP, I	N THE FRONT ROW OF RIVETS, AND EXTENDS TO THE LEADING EDGE OF CAP.  THE A/C PASSED 2-400 HOUR WING SIRM INSPECTIONS.  18	1 HRS INTO NEXT INTERVAL WAS WHEN CRACK WAS DETECTED DURING ROUTINE MAINTENANCE.  BEECH HAS REDUCED INTERVAL FOR EDDY CU	RRENT INSP OF SPAR CAP TO 200 HRS DUE TO RECURRENCE OF THIS PROBLEM REF 8110-4 FOR N692M FOR SIMILAR DETAILS.  A/C IS ON	 USFS CONTRACT.		1	L	7	2 	3T				3A20    					 
	20080603		EU  	2008	6	3	2008FA0000330    	1	20080502	G	3242	244755	BRAKE DISC      	BFGOODRICH  		PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	708AF	1656 			0563	708	PR0583	KX309		WHILE REMOVING RIGHT MAIN WHEEL ASSEMBLY DISCOVERED THE OUTBOARD BRAKE DISC OF THE RIGHT BRAKE BROKEN INTO TWO PIECES.  	REPLACED RIGHT BRAKE ASSEMBLY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080603		EU  	2008	6	3	2008FA0000331    	1	20080506	G	3242	244755	BRAKE DISC      	BFGOODRICH  		PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	776AF	1103 			0715	776	PR0657	KX423		FLIGHT CREW REPORTS RIGHT BRAKE GRABBING.  REMOVED RIGHT MAIN TIRE ASSEMBLY AND DISCOVERED THE OUTBOARD BRAKE DISC WAS B	ROKEN INTO TWO PIECES.  REPLACED THE RIGHT BRAKE ASSEMBLY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080603		EU  	2008	6	3	2008FA0000332    	1	20080506	G	3242	244755	BRAKE DISC      	BFGOODRICH  		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE ASSY	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	591AF	875  	875  		0213	591	PR0454	KX164		FLIGHT CREW REPORTS LEFT BRAKE GRABBING.  REMOVED LEFT MAIN TIRE ASSEMBLY TO INVESTIGATE DISCREPANCY AND DISCOVERED THE 	OUTBOARD BRAKE DISC BROKEN INTO THREE PIECES.  REPLACED THE LEFT BRAKE ASSEMBLY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080603		EU  	2008	6	3	2008FA0000333    	1	20080425	G	3520		INDICATOR       			ISRAEL	1124  	1124        	4500102	EU  										OXYGEN MASK	INOPERATIVE     	C				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	05	500KE	379  				360				PASSENGER OXYGEN MASK FLOW INDICATOR INOPERATIVE.  THIS UNIT CAME FROM LOT LC 0521 K OR LOT LC 0526K						2	M	7	2 	4F				A2SW    					 
	20080701		CE  	2008	7	1	2008FA0000335    	1	20080418	G	2140	88D7015EL	TUBE            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	HEATER	CRACKED         	B			YWBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17	873AN	453  			A04010003	TH1680				WHILE PERFORMING A PRESSURE DECAY TEST IAW AD2004-21-05, THE COMBUSTION TUBE WOULD NOT AINTAIN PRESSURE AND AIR LEAKING 	WAS NOTED. INVESTIGATION FOUND A .75 INCH LONG CRACK IN THE AFT END OF THE COMBUSTION TUBE NEAR THE RADIUS. CRACK MAY HA	VE BEEN CAUSED BY STRESS INDUCED WHILE FORMING  THE END CAP ALONG WITH NORMAL HEATING AND COOLING OF THE HEATER. HEATER 	HAD 98 HOURS SINCE LANST PRESSURE TEST. A FACTORY REBUILT UNIT WAS INSTALLED AND AIRCRFAT RETURNED TO SERVICE.			1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P22EA	 
	20080701		EU  	2008	7	1	2008FA0000336    	1	20080527	G	7920	307194912	PUMP            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					ENGINE OIL	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	970S	70   				238				IAW MFG RECOMMENDATION, WE REMOVED THE ENGINE OIL PUMP, PN 3071949-11,  AND INSTALLED PN 3071949-12 PUMP BECAUSE OF AN I	SSUE (ENGINE HIDING OIL) NOT ABLE TO GET A PROPER OIL QUANITITY READING AFTER SHUTDOWN. MFG SAID THE PN 3071949-12 PUMP 	SHOULD CORRECT THAT, WHICH IT DID. THE PUMP WE INSTALLED PN 3071949-12, SN 7018, TSO 20 HOURS WITH A ZERO TIME SINCE REP	AIRED 8130 FROM MFG TRACKING NR 41056, WO NR 877515-001, DATED 2-4-2008 WITH NO FAULT FOUND. AFTER APPROXIMATELY 10 HOUR	S, WE HAD WRITE UP OF OIL PRESSURE FLUCTUATING. GROUND RUN AND COULD NOT DUPLICATE, SO WE SWAPPED OIL PRESSURE TRANSMITT	ERS AND GAUGE WITH OTHER ENGINES FOR TROUBLESHOOTING. THEN THE AIRCRAFT FLEW APPROXIMATELY 38 HOURS WITH EVERYTHING NORM	2	L	7	3 	4F	4	F		A46EU   	E6WE				 
	20080701		SW  	2008	7	1	2008FA0000337    	1	20080701	G	6400	206011725011	ROD             			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					TAIL ROTOR	CHAFED          	B			ULXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	83WP					51359				DURING AN INSPECTION THE THE TAIL ROTOR PITCH CONTROL TUBE SLEEVES, WE DISCOVERED THAT BELLCRANK PN 206-001-763-001 HAD 	BEEN CHAFED INTO BY THE RIVET SECURING THE ROD END OF ROD ASSEMBLY PN 206-011-725-001. THIS WEAR OCCURS WHEN LEVER ASSEM	BLY PN 206-011-722-105 PIVOT DURING CONTROL MOVEMENTS, CHANGING THE PLANE OF THE ROD. THE MM DOES NOT TELL YOU WHICH WAY	 TO INSTALL THE ROD, HOWEVER, ALL OF THE ILLUSTRATIONS SHOW THE RIVETED END OF THE ROD TO BE CONNECTED TO THE BELLCRANK.	 PLEASE SEE BHT-206L-SERIES-IPB, FIG 64-1 AND FIG 67-12 AND BHT-206L-MM, PARA 67-63, FIG 67-17 DETAIL D, PARA 64-20 AND 	FIG 64-14. THIS CAN BE CURED BY INSTALLING THE ROD WITH THE ADJUSTABLE END CONNECTING TO THE LEVER.	1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20080701		SW  	2008	7	1	2008FA0000338    	1	20080530	G	6200	407310104103	SPRING          	BELL        		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FRAHM ASSY	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	701WP					53542				ONE OF EIGHT SPRINGS BROKEN CAUSING DAMAGE TO LOWER HOUSING. LOWER HOUSING, SPRINGS 2 EA. AND PLUGS WERE REPLACED. UNKNO	WN WHI SPRING BROKE, SPRING WAS FOUND BROKEN ON SCHEDULED 300 HOUR INSPECTION. (K)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20080701		CE  	2008	7	1	2008FA0000339    	1	20080512	G	5610	10138402521	WINDSHIELD      			BEECH 	90    	C90         	1152913	CE  										COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	585R	4772 				LJ1169				PILOT WAS ON TAKEOFF AND HAD JUST LEVELED OUT FOR FLIGHT AND WINDSHIELD CRACKED ON THE INNER PANE. PILOT RETURNED TO BAS	E AND THE WINDSHIELD WAS REPLACED. WINDSHIELD WAS SENT TO INSURANCE CO. LAB FOR EVALUATION. (K)					1	L	7	2 	3T				3A20    					 
	20080701		EU  	2008	7	1	2008FA0000340    	1	20080512	G	3233	C239251103	ACTUATOR        			AMD   	FALC50	FALCON50MYST	2730106	EU  										MALF	MALFUNCTIONED   	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	900KE	9497 				052				WHILE PERFORMING THE LANDING GEAR GRAVITY EXTENSION CHECK (MP32-470) DURING THE (B) INSPECTION IT WAS DISCOVERED BOTH MA	IN LANDING GEAR ACTUATORS WOULD EXTEND PARTIALLY (APPROXIMATELY 30 PERCENT OF NORMAL TRAVEL) AND STOP. FURTHER TROUBLESH	OOTING REVEALED IT TOOK EXTREME PRESSURE TO MOVE THE ACTUATORS TO THE DOWN AND LOCKED POSITION. THE ACTUATORS NORMALLY F	REE-FALL TO THE EXTENDED POSITION AND NEED TO BE PULLED INTO THE DOWN AND LOCKED POSITION. BOTH ACTUATOR WERE REPLACED W	ITH OVERHAULED ACTUATORS. THE FAULTY ACTUATORS WERE SENT TO THE MFG REPAIR FACILITY FOR TEARDOWN AND EVALUATION. THE ACT	UATOR PART AND SERIAL NUMBER ARE AS FOLLOWS: LT ACTUATOR/ PN C23925-1103, SN U22, RT ACTUATOR/ PN C23926-1103.	2	L	7	3 	4F				A46EU   					 
	20080701		EU  	2008	7	1	2008FA0000341    	1	20080512	G	3233	C239261103	ACTUATOR        			AMD   	FALC50	FALCON50MYST	2730106	EU  										MLG	MALFUNCTIONED   	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	900KE					052				WHILE PERFORMING THE LANDING GEAR GRAVITY EXTENSION CHECK (MP32-470) DURING THE (B) INSPECTION IT WAS DISCOVERED BOTH MA	IN LANDING GEAR ACTUATORS WOULD EXTEND PARTIALLY (APPROXIMATELY 30 PERCENT OF NORMAL TRAVEL) AND STOP. FURTHER TROUBLESH	OOTING REVEALED IT TOOK EXTREME PRESSURE TO MOVE THE ACTUATORS TO THE DOWN AND LOCKED POSITION. THESE ACTUATORS NORMALLY	 FREE-FALL TO THE EXTENDED POSITION AND NEED TO BE PULLED INTO THE DOWN AND LOCKED POSITION. BOTH ACTUATORS WERE REPLACE	D WITH OVERHAULED ACTUATORS. THE FAULTY ACTUATORS WERE SENT TO THE MANUFACTURER`S REPAIR FACILITY FOR TEARDOWN AND EVALU	ATION.  LT ACTUATOR, PN C239251103, SN U22 / RT ACTUATOR PN C239261103, SN U22. (K)	2	L	7	3 	4F				A46EU   					 
	20080715		GL  	2008	7	15	2008FA0000343    	1	20080618	G	5210		HINGE           			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360LYC*   	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	DOOR	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	686US					40640	L3262751A	CH39554B		FOUND CRACKS IN AFT DOOR HINGE.  (K)						1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	P920	 
	20080715		GL  	2008	7	15	2008FA0000345    	1	20080616	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       			CL	CLIMB          	1			WP	07	605US	536  				40675	L3276151A	CH399768		ON TAKEOFF CLIMB OUT, AFT PASSENGER DOOR DEPARTED AIRFRAME. (K)						1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	P920	 
	20080715		GL  	2008	7	15	2008FA0000346    	1	20080625	G	5210	D4152210000	HINGE           			DIAMON	DA40  	DA40        	2990002	GL  										REAR CABIN DOOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4189U	991  				40768				REAR HINGE DEVELOPING CRACKS IN FIBERS.  NORMAL OPERATING CONDITION.  PROBABLE CAUSE IS REAR HOLD OPEN CYLINDER CAUSING 	STRESS ON HINGE POINT. (K)					1	L	7	1 	3O			NT	A47CE   					 
	20080715		GL  	2008	7	15	2008FA0000347    	1	20080625	G	5210	D4152210000	HINGE           			DIAMON	DA40  	DA40        	2990002	GL  										REAR CABIN DOOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4191M					40769				REAR HINGE DEVELOPING CRACKS IN FIBERS. NORMAL OPERATING CONDITION. PROBABLE CAUSE IS REAR HOLD OPEN CYLINDER CAUSING ST	RESS ON HINGE POINT. (K)					1	L	7	1 	3O			NT	A47CE   					 
	20080715		CE  	2008	7	15	2008FA0000348    	1	20080318	G	2711	EM408810	ACTUATOR        			RAYTHN	390   	390         	7150030	CE  										ROLL TRIM	MALFUNCTIONED   	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	837JM	758  				RB169				IN CONJUNCTION WITH REPAIRS FOR UNCOMMANDED ROLL, TRIM ACTUATION AT KMDW REPLACED RT ROLL TRIM ACTUATOR (HBC PN 390-3810	090010) WITH RAPID SUPPLIED REPAIRED UNIT. ATTEMPTED TO PERFORM ROLL TRIM FUNCTIONAL CHECKS IAW THE 390 MM 27-10-00-501 	AFTER ACTUATOR REPLACEMENT BUT FOUND ROLL TRIM CIRCUIT BREAKER TRIPPING UPON POWER APPLICATION.  (K)				1	L	7	2 	3F			RT	A00010WI					 
	20080715		CE  	2008	7	15	2008FA0000349    	1	20080502	G	3220	12434262	TORQUE LINK     			CESSNA	210   	210M        	2073450	CE  										NLG	CRACKED         	B			ONFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	70HG	4609 				21062120				OUR REPAIR STATION HAS REPLACED SEVERAL OF THESE SAME UPPER TORQUE LINKS DUE TO FINDING THEM BENT AT INSPECTION (APPROX 	5 TOTAL) THIS IS THE FIRST ONE FOUND CRACKED.  PROBABLE CASUE IS WHAT I BELIEVE IS LANDING IMPACT WITH MORE THAN RECOMME	NDED STRUT ESTENSION (5.00 INCH MAX) IAW SRM FIGURE 5-15 WHICH IS ADJUSTABLE BY ADDING SHIMS (ITEM 15) MAXIMUM OF THREE,	 PN 12436182 IAW THE NOTE OF FIGURE 5-18 OF THE SRM. (K)			1	H	7	1 	3O				3A21    					 
	20080715		CE  	2008	7	15	2008FA0000350    	1	20080429	G	3520	38101550360	HOSE            			CESSNA	500   	560CESSNA   	2076750	CE  										LAV OXYGEN	LEAKING         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	501CW					5600050				DURING SCHEDULED PHASE INSPECTION NOTED HOSE ASSY.  SUPPLYING OXYGEN TO LAVATORY OXYGEN MASK COMPARTMENT FROM MAIN UPPER	 CABIN OXYGEN LINE ASSY LEAKING. FURTHER INVESTIGATION SHOWED MULTIPLE HOLES IN OXYGEN HOSE ASSY FLEXIBLE HOSE SECTION. 	SUSPECT HOSE ASSY DETERIORATED FROM AGE AND POSSIBLY HEAT FROM AIRCRAFT BEING PARKED OUTDOORS FOR EXTENDED PERIODS. RECO	MMEND TECH CLOSELY INSPECT CABIN OXYGEN SYSTEM COMPONENTS DURING SCHEDULED INSPECTIONS ON OLDER AND HIGH-TIME SERIES AC 	FOR AGE RELATED DEFECTS. (K)		2	L	7	2 	4F			RT	A22CE   					 
	20080715		CE  	2008	7	15	2008FA0000351    	1	20080429	G	5230	991434317	LATCH           			CESSNA	500   	560CESSNA   	2076750	CE  										CARGO DOOR	BROKEN          	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	501CW					5600050				DURING SCHEDULED PHASE INSPECTION, FOUND AFT BAGGAGE COMPARTMENT DOOR AFT LATCH ASSY, NOT LOCKING. FURTHER INVESTIGATION	 FOUND AFT DOOR LATCH ASSY, BROKEN.  REPLACED LATCH ASSY W/ SERVICEABLE LATCH ASSY, OPERATIONS NORMAL. RECOMMEND FURTHER	 INVESTIGATION BY MFG TO DETERMINE IF MFGED LATCHES PRONE TO EARLY FATIGUE FAILURE AND ISSUE SB TO REPLACE IF HIGH FAILU	RE RATES NOTED.  TECHS SHOULD INSPECT THESE LATCHES CLOSELY DURING SCHEDULED PHASE CHECKS TO PREVENT POSSIBLE DOOR OPENI	NG IN FLIGHT. (K)		2	L	7	2 	4F			RT	A22CE   					 
	20080715		NM  	2008	7	15	2008FA0000352    	1	20080514	G	5712	41513017	RIB             			UNIVAR	415   	415D        	0420306	NM  										LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	94052	3674 				1375				SUBJECT PART WAS FOUND TO BE CORRODED WHILE PERFORMING INSPECTION IAW AD 2002-26-02 (D) (3 YEAR REQUIREMENT). LEFT REAR 	CENTER SECTION RIB, CORRODED AROUND LARGE HOLE THROUGH WHICH PITOT AND STATIC LINES, AND NAV LITE WIRE PASS TO OUTER WIN	G PANEL. REMOVED DEFECTIVE PART AND INSTALLED NEW PART (415-13017) SUPPLIED BY MFG.  CAUSE OF CORROSION UNKNOWN, AS SURR	OUNDING STRUCTURE WAS NOT AFFECTED. CORRODED PART IS UNTREATED (NOT CORROSION PROOF IN ANY WAY). SUGGEST WING CENTER SEC	TION OF THESE AIRCRAFT BE CORROSION PROOFED WITH ACF-50 OR WITH CORROSION X OR EQUIVALENT COMPOUND TO PREVENT FURTHER PR	OBLEMS OF THIS NATURE. (K)	1	L	7	1 	3O				A787    					 
	20080715		CE  	2008	7	15	2008FA0000353    	1	20080516	G	3233		SHAFT           			BEECH 	80    	65A80       	1152808	CE  	LYC   	O540  	IGSO540B1A  	41532	EA  					NLG ACTUATOR	LACK OF LUBE    	D				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SW	13	6AQ	4434 				LD214				NOSE LANDING GEAR WOULD NOT DEPLOY ON APPROACH TO LANDING. AFTER NLG REMOVAL, IT WAS DISCOVERED THAT THE NLG ACTUATOR DR	IVE SHAFT PN 50820218 INTERNAL SPLINE WAS WORN AND SHEARED.  LUBE POINTS ON DRIVE SHAFT TO LUBE SPLINES TO REDUCE WEAR. 	(K)				1	L	7	2 	3O	3	O		3A20    	1E7				 
	20080715		NE  	2008	7	15	2008FA0000354    	3	20080603	G	6110	7826691	BOLT            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER	SHEARED         	B			S88R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	802MR	1613 			20050318	612	PCEAG0125	20050318		WHILE DOING A RGB CHANGE ON THE NR 1 ENGINE OF DASH-8, N802MR, DURING REINSTALLATION OF THE PROPELLER WHILE DOING THE TO	RQUE SEQUENCE, WE BROKE ONE PROP MOUNTING BOLT. WE SENT THE HUB OUT FOR REPAIR AND SENT THE TORQUE WRENCH TO THE CAL PLA	CE TO BE VERIFIED. THEY REPLACED 3 MOUNTING BOLTS. WHEN THE HUB CAME BACK FROM REPAIR WE PROCEEDED TO INSTALL THE BLADE 	USING A DIFFERENT TORQUE WRENCH. AS WE WERE DOING THE CRISSCROSS PATTERN, I NOTICED THAT THE BOLTS THAT WERE NOT REPLACE	D WOULD NOT GRAB TORQUE THE TORQUE WRENCH WOULD  CLICK ONCE BUT ON THE SECOND CLICK IT WOULD MOVE OVER .2500 OF A TURN, 	THE 3 NEW SCREWS CLICK FINE CLICK CLICK.  WE FIGURED THAT THE BOLTS HAD JUST BEEN REMOVED AND REINSTALLED AND THEY WERE 	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080715			2008	7	15	2008FA0000355    	4	20080513	G	2215	L109BBM	ACTUATOR        			SKRSKY	S76   	S76B        	8143007	NE  										AUTOPILOT SYS	MALFUNCTIONED   	G				O				OTHER                   				F	P		FLT CONT AFFECTED         	NO WARNING INDICATION     		CR	CRUISE         	1			EA	63	150US					760312				PILOT HSI SPINS WILDLY TO THE RIGHT AND DISPLAYS A HEADING FLAG. PILOT`S FLIGHT DIRECTOR MAINTAINS HEADING AND ALTITUDE 	FOR APPROXIMATELY 30 SECONDS THEN LOSES ALL INPUT. THE AIRCRAFT THEN TURNS AND DESCENDS AT WILL.  WHILE THIS HAPPENS THE	 LEFT ANTI-TORQUE PEDAL DRIVES FORWARD PLACING THE HELICOPTER OUT OF TRIM. THE PILOT SIDE HEADING COMMAND BARS JUMP WILD	LY AND TURN TO THE LEFT WHILE THE AIRCRAFT IS IN STRAIGHT AND LEVEL FLIGHT. ONCE THE FLIGHT DIRECTOR LOSES INPUT THE CYC	LIC TRIM WILL NOT RESPOND IN THE PITCH OR ROLL CHANNEL. TRIED TO DISENGAGE AND RE-ENGAGE THE SYSTEM BUT THE SAME PROBLEM	 RETURNS. THE AIRCRAFT REQUIRES MANUAL PEDAL INPUT TO REMAIN IN TRIM. NO EMERGENCY ACTIONS WERE TAKEN OR NEEDED DURING T	1	G	7	2 	4U				H1NE    					 
	20080715		GL  	2008	7	15	2008FA0000357    	1	20080501	G	3222	11907005	STRUT           			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	241CP	516  				201713	360239			AFTER INSPECTION OF AIRCRAFT AFTER A REPORT OF NOSE WHEEL PANT DAMAGE ON LANDING. I FOUND THE UPPER LEFT ARM ON THE NOSE	 STRUT WAS SERIOUSLY CRACKED. THE CRACK RAN FROM THE TOP OF THE ARM ON THE NOSE STRUT WAS SERIOUSLY CRACKED. THE CRACK R	AN FROM THE TOP OF THE ARM. JUST FORWARD OF THE STRUT DATA PLATE, THROUGH THE ENTIRE  ARM  AND STOPPED AT THE BOTTOM WHE	RE A GUSSET WAS WELDED.  THE CRACK CONTINUED TO RUN PARALLEL TO GUSSET FOR ABOUT .5 OF AN INCH. A SMALLER CRACK WAS ALSO	 FOUND ON THE RIGHT ARM STARTING AT THE SAME POINT AS THE LEFT ARM BUT ONLY MEASURED ABOUT .5 OF AN INCH. ALSO FOUND NOS	E WHEEL STOP AND NOSE FORK WAS DAMAGED. POSSIBLE CAUSE COULD BE REPEATED UNREPORTED HARD LANDINGS. WOULD RECOMMENDED ALL	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
	20080715		EA  	2008	7	15	2008FA0000358    	1	20080519	G	2750	60093000123	CONTROL BOX     			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A      	30066	NE  					T/E FLAPS	FAILED          	C				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	03	779AZ	12   				5176				CREW REPORTED FLAP FAILURE DURING APPROACH APPROXIMATELY 8 HOURS AFTER INSTALLATION. RESET SYSTEM AND FLAPS WORKED FINE.	 FLEW AIRCRAFT HOME AND NO DISCREPANCIES. UNABLE TO DUPLICATE PROBLEM UNTIL SEVERAL WEEKS LATER DURING MAINTENANCE RUN. 	FLAPS WOULD IMMEDIATELY FAIL, INTERMITTENTLY. PLACED ELECTRICAL RECORDER  ON SYSTEM WITH BREAKOUT BOX AND FOUND INTERMIT	TENT SIGNAL LOSS ON SIGNAL 2 WHEN INSTALLED ON LEFT WING. SWAPPED UNIT TO RIGHT WING AND FLAPS WOULD CONSISTANTLY FAIL I	NTERMITTENTLY. THIS TIME FOUND SIGNAL LOSS ON RIGHT WING, SIGNAL 1. INSTALLED REPAIRED UNIT, SYSTEM WORKING OK RIGHT NOW	. THIS UNIT HAD LESS THAN 13 HOURS TT SINC REPAIR ON IT. (K)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080715		EA  	2008	7	15	2008FA0000359    	1	20080521	G	2750	600930035	CONTROL HANDLE  			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A1     	30068	NE  					COCKPIT	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	779AZ	3502 				5176	807241			AIRCRAFT HAD BEEN EXPERIENCING MULTIPLE INFLIGHT FLAP FAILURES WHICH WERE NOT DUPLICATED ON THE GROUND. DURING TROUBLESH	OOTING OF THE FLAP SYSTEM, FLAPS WOULD NOT MOVE FROM 45 DEGREES TO 30 DEGREES WHEN SELECTED. NO FAILURE WAS DISPLAYED BY	 THE AIRCRAFT. FLAP HANDLE WAS JOGGLED AND FLAP MOVEMENT WOULD BEGIN. REPLACED FLAP CONTROL HANDLE. (K)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080715		CE  	2008	7	15	2008FA0000360    	1	20080515	G	5720	662121126	STIFFENER       			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					LT MLG WW	MISINSTALLED    	B			X07R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	698QS					5605653				FOUND RT STIFFENER (PN 662121126) INADVERTENTLY INSTALLED IN LT POSITION. WITH LANDING GEAR IN THE STOWED POSITION, THE 	ACTUATOR CONTACTED THE STIFFENER AND CAUSED MINOR CHAFFING. NEITHER THE ACTUATOR NOR THE STIFFENER WERE DEFORMED/ DAMAGE	D. (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20080715		EA  	2008	7	15	2008FA0000361    	1	20080521	G	2750	60093000117	FCU             			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A1     	30068	NE  					T/E FLAPS	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	03	779AZ					5176	807245			AC HAS BEEN EXPERIENCING INTERMITTENT FLAP SYSTEM FAILURES IN DIFFERENT MODES OF FLIGHT, PRIMARILY DURING APPROACH. TROU	BLESHOOTING IAW MM RECOMMENDED REPLACEMENT OF FLAP CONTROL UNIT DUE TO IMMEDIATE ( INTERMITTENT) FAILURES AFTER FLAP MOV	EMENT SELECTION. AFTER INSTALLATION OF THIS UNIT IN AIRPLANE, FLAPS FAILED TAKEOFF CONFIGURATION WARNING SYSTEM CHECK WH	EN UTILIZING LEFT POWER LEVER (THROTTLE LEVER). UNIT NOT RETURNED TO SERVICE. NO FLIGHT TIME PLACED ON UNIT.  THIS PART 	HAD A FRESH INSPECTION TAG FROM VENDOR. (K)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080715		CE  	2008	7	15	2008FA0000362    	1	20080507	G	2910	620701098	HYDRAULIC LINE  			CESSNA	650   	650         	2076802	CE  										HYDRAULIC SYSTEM	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	126MT	3822 				6500044				NOTED HYDR FLUID LEAKING FROM RT WING IN THE MLG AREA. TROUBLESHOOTING REVEALED A GROUND SPOILER HYD LINE. LOCATED ON TH	E REAR FACE OR THE AFT SPAR AT WS 84 (APPROX). HAD BEEN CHAFED THROUGH BY THE AILERON CABLES. DUE TO THE CLOSE PROXIMITY	 OF THE LINE AND CABLES, THIS AREA SHOULD BE CLOSELY INSPECTED TO DETECT ANY CHAFING PROBLEM. (K)				2	L	7	2 	4F				A9NM    					 
	20080715		EU  	2008	7	15	2008FA0000363    	1	20080406	G	6320	350A32030004	GEARBOX         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1A2   	60030	NE  					MAIN ROTOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	111AK	4093 	2110 			3092	4571			HAD A MAIN GEARBOX CHIP EVENT. PERFORMED CHECKS IAW MM TO INCLUDE OIL DAIN, STRAIN AND FLUSH. HAD FIVE SCALE TYPE CHIPS 	THE LARGEST BEING 1.5MM AND SENT IN FOR ANALYSIS. RETURNED AIRCRAFT TO SERVICE.  AT RECEIPT OF ANALYSIS DATA PERFORMED A	 BORESCOPE OF PINION AND BEVEL WHEEL. FOUND FROSTING DAMAGE ON PINION GEAR AND REMOVED AIRCRAFT FROM SERVICE. (K)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
	20080715		CE  	2008	7	15	2008FA0000364    	1	20080509	G	2731		TRIM SWITCH     			CESSNA	206   	P206B       	2073309	CE  	CONT  	O520  	IO520F      	17032	SO  					PILOTS YOKE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	4711F					P2060311	248025R			PILOT REPORTED IN FLIGHT WHEN AUTOPILOT/ELECTRIC TRIM ENABLE, TRIM SERVO "RAN ON", WHEN ELECTRIC TRIM TURNED OFF MANUAL 	TRIM WHEEL OPERABLE AND NO MALFUNCTION OF SYSTEM NOTED, UPON INSPECTION NOTICED SOLDERED CONNECTION ON BASE OF SWITCH BE	NT AND JUMPED BETWEEN WIRE POSTS ON BASE OF SWITCH. RESOLDERED CONNECTION, SEAL WITH HEAT SHRINK AND OPERATED SYSTEM OK.	 (K)			1	H	7	1 	3O	3	O		A4CE    	E5CE				 
	20080715		EA  	2008	7	15	2008FA0000365    	2	20080522	G	8530	SLC36005	CYLINDER        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	21295	681  				17263925				ENGINE WAS OVERHAULED NOV 2001 USING NEW CILINDER ASSEMBLES. BREAK-IN OPERATION PERFORMED WITH MFG SERVICE INSTRUCTION 1	427B AND MINERAL OIL. ENGINE OPERATED NEAR DAILY FLIGHTS AVERAGEING .5 HOUR EACH. REGULAR OIL CHANGES USING 15W50 OIL AN	D ADDITIVE, POST BREAK-IN TIME OF 25 HOURS. OIL SAMPLE RESULTS INDICATED PREMATURE WEAR OF RINGS AND WALLS STARTING WITH	 FIRST SAMPLE AT 111.0 HOURS AND EVERY 30-50 HOURS THERE AFTER. REMOVED CYLINDERS FOR INSPECTION AFTER DISCOVERING VISIB	LE METAL IN SCREEN AT 681 HOURS SINCE OVERHAUL. CYLINDER WALLS ON ALL FOUR ENGINE CYLINDERS WORN/DETERIORATED TO DEGREE 	THAT THE PISTON PIN PLUGS WERE SCRAPING ON RIDGES FROM PISTON RINGS.  NOTABLE ALUMINUM FROM PISTON PIN PLUGS WAS FOUND I	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20080715		CE  	2008	7	15	2008FA0000366    	1	20080524	G	7603		ARM             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					THROTTLE CABLE	BROKEN          	B			O6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	75528					17267783	L153076T			BOLT CONNECTING CARBURETOR THROTTLE ARM TO THROTTLE CABLE FAILED RESULTING IN THROTTLE STICKING OPEN. PILOT PLACED MIXTU	RE CONTROL IN IDLE CUTOFF POSITION AND ATTEMPTED TO GLIDE TO RUNWAY AT AIRPORT. AIRCRAFT IMPACTED POWER LINES SHORT OF R	UNWAY. BOLT WAS NOT RECOVERED. (K)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20080715		CE  	2008	7	15	2008FA0000367    	1	20080522	G	2750	99105863	MOTOR           			CESSNA	208   	208B        	2073701	CE  										TE FLAPS	BURNED          	D				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			NM	04	110WY	295  				208B1020				ON 5/7/08 DEPARTED AT APPROXIMATELY 8:30 LOCAL TIME. FLAPS SET TO 10 DEGREES FOR TAKEOFF. TAKEOFF & CLIMB NORMAL. AFTER 	10 TO 15 MINUTES INTO FLT WITH AUTOPILOT ENGAGED, NOTICED A BURNING ODOR & SAW A SMALL AMOUNT OF SMOKE THAT LASTED FOR A	 SECOND OR TWO. DISENGAGED AUTOPILOT & LOOKED AT CIRCUIT BREAKERS & NOTICED STALL WARNING CIRCUIT BREAKER HAD POPPED. AF	TER RETURNING TO AIRPORT, FOUND SEVERAL CIRCUIT BREAKERS HAD POPPED & FLAPS WERE INOPERATIVE & STUCK AT 10 DEGREES. AVIO	NICS SHOP REPORTED THE FOLLOWING: HIDDEN DAMAGE INSPECTION PERFORMED. BURNED WIRES FOUND IN WIRE BUNDLE RUNNING FROM MAI	N FLAP MOTOR TO CIRCUIT BREAKER PANEL & FROM MAIN FLAP MOTOR TO GROUND BLOCK J66. INSULATION OF ADJACENT WIRES ALONG SAM	1	H	7	1 	3T				A37CE   					 
	20080715		CE  	2008	7	15	2008FA0000368    	1	20080509	G	2430	DOFFO10300J	ALTERNATOR      			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4711F					P2060311	248025R			BODY THRU SCREWS BACKING OUT CAUSING ALTERNATOR HALVES TO START TO SEPARATE, THOUGH NO IMMEDIATE ISSUES WITH AICAFTS CHA	RGING SYSTEM, NOTICED DISCREPANCY UPON VISUAL INSPECTION AFTER LANDING. (K)					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
	20080715		SO  	2008	7	15	2008FA0000369    	2	20080322	G	7414		GEAR            								CONT  	O550  	IO550N      	17042	SO  					MAGNETO	STRIPPED        	G				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			EA	61	2354B					0077	685811			A PRE-TAKEOFF ENGINE RUNUP WAS SATISFACTORY. SHORTLY AFTER LIFTOFF THE AIRCRAFT BEGAN VIBRATING SUBSTANTIALLY. AFTER REA	CHING PATTERN ALITUDE, REDUCED POWER AND SWITCHED TO LT MAGNETO OPERATION AND THE ENGINE RAN SMOOTHLY. SWITCHED TO RT MA	GNETO OPERATION THE ENGINE ESSENTIALLY DIED AND UPON RETURNING TO "LT" THE ENGINE EXPERIENCED AN AFTER FIRE (AKA BACKFIR	E) THEN RAN SMOOTHLY ONCE AGAIN. RETURNED TO THE DEPARTURE AIRPORT AND REMOVED THE ENGINE COWLING. REMOVED THE TIMING PL	UG ON THE RT MAG AND FOUND THE DISTRIBUTOR GEAR WOULD TURN FREELY. REMOVED THE MAGNETO. PARTIAL DISASSEMBLY REVEALED THE	 DISTRIBUTOR GEAR WAS STRIPPED OF NEARLY HALF ITS TEETH. BOTH MAGNETOS HAVE SINCE BEEN REPLACED. EACH MAGNETO HAS A THRE						3	O			E3SO				 
	20080715		CE  	2008	7	15	2008FA0000370    	1	20080507	G	3220		LEG ASSY        			CESSNA	170   	170A        	2072304	CE  	ROTAX 	912   	ROTAX912UL  	 	EU  					NLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	5455C					19489	5645575			NOSE LANDING GEAR LEG BROKEN AT FORWARD WELD ON SHOCK ABSORBER ATTACHMENT BRACKET. EXISTING INTERNAL CRACK. PROBABLE CAU	SE, BAD WELD. (K)					1	H	7	1 	3O	3	O		A799    	EXPE3I				 
	20080718		SO  	2008	7	18	2008FA0000371    	2	20080510	G	8500		ENGINE          			CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300D       	17022	SO  						VAPOR LOCK      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	172BX					17254216	24635D1D			AC WAS BEING FLOWN ON RT FUEL TANK. AFTER RUNNING TANK DRY, PILOT SELECTED RT FUEL TANK AND MOMENTS LATER THE ENG STOPPE	D PRODUCING POWER AND MADE AN EMERGENCY LANDING.  AC FUEL SYS WAS INSPECTED FOR CONTAMINATES AND FAILURES, NONE WERE FOU	ND. POSSIBLE CAUSE IS VAPOR LOCK IN FUEL SYS FROM RUNNING FUEL TANK TRY. TO PREVENT THIS FROM RECURRING, WOULD BE TO SEL	ECT ANOTHER FUEL TANK PRIOR TO RUNNING THE SELECT FUEL TANK DRY. (K)			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
	20080715		WP  	2008	7	15	2008FA0000372    	1	20080514	G	6330	23688	RETAINER        			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540*      	41532	EA  					M/R TRANSMISSION	MISMANUFACTURED 	B			ZYEG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1523T					1740				RETAINER SUSPECTED LOCALLY MADE INSTALLATION WORD "UP" IS NOT STAMPED ON PART BUT ETCHED ON BY HAND. THICKNESS OF RETAIN	ER IS .045, ACTUAL PART THICKNESS OF NEW RETAINER IS .051.  FOUND SHAFTS THAT ARE SHIMMED WITH BAD RETAINERS TO BE SHIMM	ED IMPROPERLY DUE TO RETAINER THICKNESS AS REQURIED BY MFG O/H MANUAL. SHAFTS WERE OUT OF TOLERANCE BY .014 TO .020. (K)				1	G	7	1 	3O	3	O		4H11    	E304				 
	20080715		SO  	2008	7	15	2008FA0000373    	1	20080515	G	3010	488699	TIMER           			PIPER 	PA31T 	PA31T1      	7103126	SO  										WING DE-ICE SYS	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	10	93CN					31T8004029				THESE UNITS WERE BOUGHT NEW FROM MANUFACTURER AND WHEN THEY WERE INSTALLED IN THE AIRCRAFT IT WAS NOTED THAT THE SURFACE	 DEICE BOOTS WERE INFLATED ALL OF THE TIME WHEN THE AIRCRAFT POWER WAS TURNED ON. A SECOND TIMER UNIT WAS PURCHASED AND 	THE SAME PROBLEM EXISTED WHEN IT WAS INSTALLED. UPON TROUBLESHOOTING THE SYSTEM AND VERIFYING CORRECT INSTALLATION AND W	IRING, IT WAS FOUND THAT TWO OF THE WIRES COMING OUT OF THE UNIT WERE SWITCHED DURING MFG AND THE BOXES WERE OPERATING O	PPOSITE AS IS INTENDED.  THERE ARE FOUR WIRES. RED, BLACK, WHITE AND BLUE. THE WHITE AND BLUE WIRES ARE REVERSED. (K)		1	L	7	2 	3T				A8EA    					 
	20080715		SO  	2008	7	15	2008FA0000374    	1	20080515	G	3010	488699	TIMER           			PIPER 	PA31T 	PA31T1      	7103126	SO  										WING DE-ICE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	10	93CN					31T8004029				THESE UNITS WERE BOUGHT NEW FROM MANUFACTURER AND WHEN THEY WERE INSTALLED IN THE AIRCRAFT IT WAS NOTED THAT THE SURFACE	 DEICE BOOTS WERE INFLATED ALL OF THE TIME WHEN THE AIRCRAFT POWER WAS TURNED ON. A SECONDTIMER UNIT WAS PURCHASED AND	 THE SAME PORBLEM EXISTED WHEN IT WAS INSTALLED. UPON TROUBLESHOOTING THE SYSTEM AND VERIFYING CORRECT INSTALLATION AND 	WIRING, IT WAS FOUDN THAT TWO OF THE WIRES COMING OUT OF THE UNIT WERE SWITCHED DURING MFG AND THE BOXES WERE OPERATING 	OPPOSITE AS INTENDED. THERE ARE FOUR WIRES, RED, BLACK, WHITE AND BLUE, THE WHITE AND BLUE WIRES ARE REVERSED.  (K)		1	L	7	2 	3T				A8EA    					 
	20080715		CE  	2008	7	15	2008FA0000377    	1	20080701	G	5730	501102715	SKIN            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	7232R	8914 				BL69				DURING A PREFLIGHT INSPECTION, MAINTENANCE TECH NOTED A 3.75 INCH LONG CRACK IN THE RT WING LOWER WING SKIN JUST FWD OF 	THE IB SECTION OF THE OB FLAP. ADDITIONALLY A SUPPORT/ ANCHOR TAB THAT ATTACHES THE LOWER WING SKIN TO THE IB MOST FLAP 	WELL RIB OF THE OB WING, WITHIN THE FLAP WELL, WAS FOUND CRACKED THROUGH/FAILED. WE BELIEVE THIS TAB FAILURE ALLOWED THE	 SKIN TO VIBRATE GENERATING THE RAPID CRACK GROWTH. THIS CRACK IS DIRECTLY AFT OF THE LOWER AFT WING BOLT. THIS CRACK HA	S JUST APPEARED WITHIN THEPAST (2) HOURS OF FLIGHT TIME.  CAN PINPOINT THIS TIME FRAME SINCE THE 5 YEAR WING BOLTS REMOV	AL AND INSPECTION PROCESS WAS COMPLETED JUST 2 FLIGHT HOURS AGO AND NO WING SKIN CRACKS WERE NOTED/ DOCUMENTED AT THAT T	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20080718		GL  	2008	7	18	2008FA0000378    	1	20080415	G	7931		TRANSMITTER     			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					OIL PRESSURE	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	748CD					0086				FOLLOWING ACTIONS WERE TAKEN AS A RESULT OF A PRECAUTIONARY LANDING, WHERE PILOT REPORTED A LOSS OF OIL PRESSURE.  AT CR	UISE, AT 8000 FT,  OIL PRESSURE ANNUNCIATOR LIGHT ILLUMINATED, OIL PRESSURE GAUGE INDICATED NO OIL PRESSURE.  AFTER LAND	ING, OIL PRESSURE RETURNED TO NORMAL. TECH SUPPORT WAS CONTACTED, RECOMMENDED CHECKING OIL PRESSURE SWITCH CONNECTORS. T	HEY FEED BOTH ANNUNCIATOR AND GAUGE. CONNECTORS WERE CLEANED, CHECKED FOR INTEGRITY AND RECONNECTED. NO PROBLEMS WERE FO	UND. OIL LEVEL WAS FOUND AT APPROX (6) QTS. (1) QUART 20X50 WAS ADDED.  ENGINE STARTUP AND OIL PRESSURE WAS NORMAL, WITH	  READING AT  TOP OF THE GREEN, COLD, DECREASING TO 50 PSI, HOT.   ALL OTHER ENG PARAMETERS APPEAR NORMAL.  SUSPECT A CO	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
	20080715		EA  	2008	7	15	2008FA0000379    	1	20080530	G	5541		SPAR            			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R1340*      	52016	NE  					RUDDER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	3628D					735B				FOUND EXTERNAL CORROSION ON RUDDER MAIN TUBULAR SPAR APPROXIMATELY (2) INCHES ABOVE RUDDER CONTROL HORN. POST WAS SEVERE	LY CORRODED WITH HOLES THRU TUBE. AD 78-08-09 ADDRESSES THIS PROBLEM BUT NOT FOR THIS MODEL AIRCRAFT. (K)					1	Q	7	1 	3R	3	R		1A16    	5E2				 
	20080715		SO  	2008	7	15	2008FA0000380    	2	20080303	G	8520		ENGINE          								CONT  	O520  	IO520CB     	17032	SO  						MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		2400 					502			OH ENGINE AND RETURNED TO SERVICE APROX (2) YEARS AGO, 600 HOURS OPERATION.  ENGINE FAILED WHEN POWER WAS REDUCED ON LAN	DING. THE COUNTERWEIGHT MANAGED TO HOOK ON THE CYLINDER DECK STUD AND DRAG IT INTO THE CASE, GETTING INVOLVED WITH THE R	OTATING COMPONENTS.  MASSIVE DAMAGE TO THE ENTIRE ROTATING MASS.  IT WAS NOTED ON TEARDOWN THAT AT THE CYLINDER DECK STU	DS (NECK STUDS) DO EXTEND THRU THEIR HOLES IN THE CYLINDER PAD APPROX .1875 TO .3125 BELOW THE BOTTOM OF THE HOLE IN THE	 CASTING.  THE LATER CASTINGS HAVE .2500 TO .3125 THICKER MATERIAL CAUSING THE STUDS TO BE EVEN WITH THE BOTTOM OF THE H	OLES, AND TO HAVE SEVERAL MORE THREADS IN THE CASTING.  AFTER EXAMINING THE CASE, NOTED, BASED ON THE DESIGN OF THE STUD						3	O			E5CE				 
	20080718		CE  	2008	7	18	2008FA0000381    	1	20080401	G	5312	12210628	BULKHEAD        			CESSNA	177   	177RG       	2073709	CE  										FUSELAGE	CRACKED         	B			H5GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	7582V	2340 				177RG0873				DURING ROUTINE INSP, FOUND PART CRACKED. CHECKED (2) OTHER AC THAT HAPPENED TO BE IN SHOP, FOUND (1) OF THEM TO HAVE A S	IMILAR CRACK.  THIS SECTION OF BULKHEAD IS  ATTACH STRUCTURE FOR LWR ATTACH ANGLE FOR IB FLAP DRIVE BELLCRANK. IT IS CUR	IOUS THAT THE FACTORY INSTALLED SOME EXTRA REINFORCEMENT STRUCTURE (A BRACKET) IN THIS POSITION IN LT WING.  THERE ARE E	VEN SOME "PILOT DRILL" (PD) HOLES DRILLED AT FACTORY IN RIB AND HEAVY ATTACH ANGLE ON THE AFFECTED RT SIDE. IT WOULD APP	EAR THAT BOTH LT AND RT BELLCRANKS WOULD EXPERIENCE SAME FORE-AFT FORCES BY AIR LOADS ON FLAPS.  SO WHY REINFORCE ONLY O	NE SIDE? IT IS POSSIBLE THAT FACTORY ASSY LINE NEGLECTED TO INSTALL AN INTENDED SIMILAR REINFORCEMENT ON THE RT SIDE?  (	1	H	7	1 	3O				A20CE   					 
	20080715		EU  	2008	7	15	2008FA0000382    	1	20080424	G	7922	1586108	REGULATOR       			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					OIL SYSTEM	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	626CG					258041	P91187			RECEIVED O/H OIL TEMP REGULATOR FROM MFG UNDER THEIR WO 815978-001, DATED 04/22/2008.  WHILE PERFORMING INCOMING PARTS I	NSPECTION ON 04/24/2008, FOUND FUEL INLET PORT SMASHED.  THERE WAS NO DAMAGE TO THE SHIPPING CONTAINER.  PROBABLE CAUSE 	OF DAMAGE WAS MOST LIKELY PRIOR TO PACKING OF UNIT FOR SHIPMENT.  (K)				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
	20080715		WP  	2008	7	15	2008FA0000383    	2	20080523	G	7210	31020474	HOUSING         			MTSBSI	MU2   	MU2B25      	5780409	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					GEARBOX	CRACKED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	15	856JT					306				PILOT REPORTED LOW AND FLUCTUATING OIL PRESSURE FROM LEFT ENGINE IN FLIGHT AND ELECTED TO SHUT THE ENGINE DOWN. AN UNEVE	NTFUL SINGLE ENGINE LANDING WAS MADE.  THE ENGINE OIL BYPASS VALVE WAS FOUND TO BE IN THE "POPPED" CONDITION, THE OIL FI	LTER WAS THEN REMOVED AND FOUND TO BE BLACK IN COLOR WITH THE FORWARD SEALING SURFACE BROKEN IN SEVERAL SMALL PIECES.  T	HE REDUCTION GEAR BOX WAS DISASSEMBLED AND THE OIL PRESSURE PUMP REMOVED.  THE FORWARD HOUSING WAS CRACKED APPROXIMATELY	 (3 INCH) RADIALLY AT FWD DETAIL.  (K)		1	H	7	2 	3T	4	T		A2PC    	E4WE				 
	20080718		GL  	2008	7	18	2008FA0000384    	2	20080519	G	7261	23063413	GEAR            			BELL  	206   	OH58B       	1181503	SW  	ALLSN 	250C  	T63A720     	03002	GL  					AIR/OIL SEPARATR	BROKEN          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	05		600  					AE405555			PILOT REPORTED ENGINE CHIP LIGHTS ON TAKEOFF.  ABORTED MISSION AND RETURNED TO HELIPAD. ENG WAS REMOVED AND SENT FOR INV	ESTIGATION.  ENG RECEIVED FOR REPAIR DUE TO ENG CHIP LIGHTS AND METAL IN OIL.  DISASSEMBLY REVEALED AIR OIL SEPARATOR GE	AR SHAFT HAD BROKEN WHERE STEM MEETS THE BASE.  THIS IS THIRD OCCURRENCE ON THIS PARTICULAR ENG ASSY OF SIMILAR GEAR FAI	LURES.  HAVE SEEN AT LEAST 8 OF THESE FAILURES IN T63 ENGINES SINCE THEY HAVE BEEN RELEASED TO PUBLIC.  (K)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20080715		CE  	2008	7	15	2008FA0000385    	1	20080605	G	3221	66426119	TRUNNION        			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					NLG	CORRODED        	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	640QS	6122 				5605240				(REF CWQR200806) WHILE WORKING AN UNSCHEDULED NOSE GEAR VIBRATION, POPPING, DISCREPANCY.  FOUND BEARING PN MS2464268G TO	 BE ROUGH WHEN TURNING.  UPON FURTHER INSPECTION FOUND CORROSION AND PITTING BETWEEN STEEL BEARINGS AND ALUM NLG TRUNNIO	N ASSY.  NLG TRUNNION SHOULD BE TREATED TO PREVENT DISSIMILAR METAL CORROSION.  FILED SLR NR 363322.  (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20080715		NM  	2008	7	15	2008FA0000387    	1	20080610	G	5340		ATTACH ANGLE    			BOEING	737   	737448      	13844BU	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA									(REF DU4R2008212) DURING SCHEDULED INSPECTION, FOUND CORROSION IN AFT LOWER CARGO COMPARTMENT AT STA 727A ATTACH ANGLE G	BGETWEEN S-27R AND S-26R.  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000388    	1	20080610	G	5310		DOOR FRAME      			BOEING	737   	737448      	13844BU	NM  										FUSELAGE	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				(REF DU4R2008213) DURING SCHEDULED INSPECTION, FOUND 1 INCH LONG CRACK ON FWD CARGO DOOR CUT-OUT AFT FRAME INNER CHORD R	ADIUS.  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000389    	1	20080610	G	5330		SKIN            			BOEING	737   	737448      	13844BU	NM  										BS 887  S19R	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				(REF DU4R2008214) DURING SCHEDULED INSPECTION, FOUND DENT ON LWR RT LOWER AFT FUSELAGE BS 887 S-19R.  (K)						2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000390    	1	20080610	G	5347		CARGO TRACK     			BOEING	737   	737448      	13844BU	NM  										CARGO BAY	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				DURING SCHEDULED INSPECTION, FOUND CORROSION IN THE AFT CARGO COMPARTMENT LT TIE DOWN TRACK LBL 17.20 FROM STA 727B - ST	A 727E.  PARTICULARLY IN FASTENER HOLE UPPER AND LOWER SURFACE. (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000391    	1	20080620	G	5320	141A5505	FLOOR SUPPORT   			BOEING	737   	73783N      	13844HI	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	318TZ					28247				(REF DU4R2008219) DURING SCHEDULED INSPECTION, FOUND CORROSION ON FLOOR SUPPORT CABIN STA 344, BL-0 TO BL-12L.  (K)						2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000392    	1	20080613	G	5320		FLOOR SUPPORT   			BOEING	737   	737448      	13844BU	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				(REF DU4R2008216) DURING SCHEDULED INSPECTION, FOUND CORROSION ON UPPER SURFACE OF FLOOR SUPPORT BEAM BS 328, RBL-16 TO 	RBL-60.  S/O NR 312001, OPS NR 24738.  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000393    	1	20080613	G	5311		FRAME           			BOEING	737   	737448      	13844BU	NM  										FUSELAGE	DAMAGED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				(REF DU4R2008217) DURING SCHEDULED INSPECTION, FOUND DOUBLE-DRILLED HOLE ON MAIN FRAME UPPER CAP AT BS 986.5 AT FLOOR LE	VEL RT.  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000394    	1	20080620	G	5320	141A5410	FLOOR SUPPORT   			BOEING	737   	73783N      	13844HI	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	318TZ					28247				(REF DU4R2008220) DURING SCHEDULED INSPECTION, FOUND CORROSION ON FLOOR SUPPORT CABIN. STA 340, LBL 11.  (K)						2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000395    	1	20080623	G	5230		SKIN            			BOEING	737   	73783N      	13844HI	NM  										AFT CARGO DOOR	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	304TZ					30675				(DU4R2008221) DURING SCHEDULED INSPECTION, FOUND AFT CARGO DOOR EXT SKIN HAS DENT 11 INCHES AFT FROM FWD EDGE 5 INCHS UP	 FROM BOTTOM EDGE WIDTH OF DENT 1.25 INCHES OF DENT .070 INCH W/Y=17 DENT MEASURES WITH DEPTH GUAGE A-1979.  S/O NR 2450	10, OPS NR 26681.  (K)				2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000396    	1	20080623	G	5230		SKIN            			BOEING	737   	73783N      	13844HI	NM  										FWD CARGO DOOR	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	304TZ					30675				(REDF DU4R2008222) DURING SCHEDULED INSPECTION FOUND DENT IN EXT SKIN OF C-1 DOOR 25 INCH DOWN FROM TOP EDGE OF DOOR AND	 22 INCHES AFT FROM FWD EDGE OF DOOR.  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000397    	1	20080624	G	5230		SKIN            			BOEING	737   	73783N      	13844HI	NM  										AFT CARGO DOOR	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	304TZ					30675				(DU4R2008223) DURING SCHEDULED INSPECTION, FOUND DENT IN AFT CARGO DOOR (C-2) EXT. SKIN.  S/O NR 245010, N/R 26678.  (K)						2	L	7	2 	4F			RT	A16WE   					 
	20080718		NM  	2008	7	18	2008FA0000398    	1	20080630	G	5340		NUT CLIP        			BOEING	737   	73783N      	13844HI	NM  										BS 967	CHAFED          	B			DU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	304TZ					30675				(DU4R2008225) DURING SCHEDULED INSP, FOUND AFT CABIN BS 967, RBL 24, TO LBL 49 FLOORBOARD ATTACH POINTS, CLIP NUTS HAVE 	WORN GROOVES/CHAFE MARKS. S/O NR 245010, N/R NR27070 (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080718		NM  	2008	7	18	2008FA0000399    	1	20080630	G	5315		FLOORBEAM       			BOEING	737   	73783N      	13844HI	NM  										BS986	CORRODED        	B			DU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	304TZ					30675				(DU4R2008226) DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN WET AREA ON FLOORBEAM FASTENERS AND FASTENER HOLES AT 	BS 986 FORM RBL45 TO LBL 45.  S/O 245010 , N/R 27072  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000400    	1	20080630	G	5512		SKIN            			BOEING	737   	73783N      	13844HI	NM  										LT HORIZ STAB	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	308TZ					28244				(REF DU4R2008227) DURING SCHEDULED INSPECTION, FOUND OUT OF LIMITS DENT IN LT HORIZ STAB L/E STA 280.  S/O 245008, N/R 2	1578  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000401    	1	20080630	G	5512		SKIN            			BOEING	737   	73783N      	13844HI	NM  										HORIZ STAB	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	308TZ					28244				DURING SCHEDULED INSPECTION, FOUND DENT IN LT L/E OF HORIZ STAB STA 105.  S/O 245008,  N/R 21591.  S/O 245008, N/R 21591	.  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080715		NM  	2008	7	15	2008FA0000402    	1	20080630	G	5315		FLOORBEAM       			BOEING	737   	73783N      	13844HI	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	318TZ					28247				DURING SCHEDULED INSPECTION, FOUND CORROSION ON AFT CABIN FLOORBEAM, BS947, RBL 5 TO LBL5. S/O 245009, N/R 26378 (K)						2	L	7	2 	4F			RT	A16WE   					 
	20080715		EA  	2008	7	15	2008FA0000403    	2	20080616	G	7414	4371	MAGNETO         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OUT OF POSITION 	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	987AP					172S10710				CHECKED THE MAGNETO TIMING AND FOUND THAT BOTH MAGNETOS WERE OFF APPROX 5 DEGREES.  CURRENTLY SET AT APPROX 30 DEGREES B	EFORE TOP DEAD CENTER. MFG SPEC IS 25 DEGREES BTDC. THE AIRCRAFT ENGINE TO MAGNETO TIMING WAS CHECKED WHEN NEW, SHORTLY 	AFTER DELIVERY 4/14/2008- 3.5 HRS TIS AND FOUND OK.  IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICALLY TO THE ADVANCED P	OSITION.  ORANGE FACTORY PUTTY NOTED ON MAGNETO HOLDOWN NUTS. IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICALLY TO THE A	DVANCED POSITION IN 80 HRS TIS. THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING 	ISSUE WITH MFG.  SB SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS, AS IN THIS CASE.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080715		EA  	2008	7	15	2008FA0000404    	2	20080617	G	7414	M3820	DISTRIBUTOR BLK 	SLICK       		CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					MAGNETO	MISREPAIRED     	B			Z08R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07	658PW				08011866	18282098				DURING INTERNAL MAGNETO INSPECTION, FOUND DISTRIBUTOR BLOCK SPOT FACED AREA FOR POLES.  APPEARS TO BE INCORRECTLY SPOT F	ACED.  MATERIAL THAT WAS LEFT BEHIND HAS THE SAME LOFT AS BEARING BOSS AREA ON DISTRIBUTOR BLOCK.  THIS CAUSES THE FINGE	R ON THE DISTRIBUTOR GEAR TO RUB ON THE DISTRIBUTOR BLOCK.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
	20080715		EA  	2008	7	15	2008FA0000405    	2	20080616	G	7414		MAGNETO         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OUT OF POSITION 	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	227BH					172S10662				DURING A PHASE 2 (100 HR) CHECK THE MAGNETO TIMING AND FOUND THE RT MAGNETO ADVANCED TO APPROXIMATELY 27 DEGREES.  MFG S	PECS CALL FOR 25 DEGREES.  LAST CHECK AT 90 HOURS PRIOR, FOUND TO BE OK.  SUSPECT MAGNETO DRIFTING IS OCCURING.  THE MAG	NETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH ENGINE AND MAGNETOS.  SB SB2	-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS, AS IN THIS CASE.  (K)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080715		EA  	2008	7	15	2008FA0000406    	2	20080611	G	7414	4371	MAGNETO         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					POWERPLANT	OUT OF POSITION 	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	712DS	98   				172S10711	L3404451			DURING THE AC FIRST PHASE 2 INSPECTION (100 HR) FOUND THAT BOTH MAGNETOS WERE OFF APPROXIMATELY 5 DEGREES.  CURRENTLY SE	T 30 DEGREES BEFORE TOP DEAD CENTER PLUS (MFG SUM SAYS 25 DEGREES BTDC) THE AIRCRAFT MAGNETO TO ENGINE TIMING WAS CHECKE	D WHEN NEW, SHORTLY AFTER DELIVERY 4/25/2008, 4.3 HRS TIS.  IT APPEARS THE MAGNETOS HAVE DRIFTED TO THE ADVANCED POSITIO	N.  ORANGE PUTTY ON THE MAGNETO HOLD-DOWN STUDS WAS NOTED.  IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICANTLY TO THE AD	VANCED POSITION IN 93 HOURS TIS.  THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOIN	G ISSUE WITH MFG OF ENGINE AND MFG OF MAGNETO SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS AS IN THIS C	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080715		EA  	2008	7	15	2008FA0000407    	2	20080611	G	7414	4371	MAGNETO         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  						OUT OF POSITION 	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	712DS					172S10711	L3404451E			DURING THE AC FIRST PHASE 2 INSP (100 HR) FOUND THAT BOTH MAGNETOS WERE OFF APPROX 5 DEGREES. CURRENTLY SET 30 DEGREES B	EFORE TOP DEAD CENTER PLUS MFG SRM SAYS 25 DEGREES BTDC).  THE AIRCRAFT MAGNETO TO ENGINE TIMING WAS CHECKED WHEN NEW, S	HORTLY AFTER DELIVERY  4/25/2008. 4.3 HOURS TIS.  IT APPEARS THE MAGNETOS HAVE DRIFTED TO THE ADVANCED POSITION. ORANGE 	PUTTY ON THE MAGNETO HOLD-DOWN STUDS WAS NOTED.  IT APPEARS THE MAGNETOS HAVE DRIFTED SIGNIFICANTLY TO THE ADVANCED POSI	TION IN 93 HRS TIS.  THE MAGNETOS DRIFTING TO THE ADVANCED POSITION TO THE ENGINE TIMING HAS BEEN AN ONGOING ISSUE WITH 	ENGINE MFG AND MAGNETO MFG, SB2-08 DOES NOT ADDRESS AN ADVANCED CONDITION OF THE MAGNETOS AS IN THIS CASE.  (K)	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080715		SO  	2008	7	15	2008FA0000408    	1	20080528	G	3246	3080D	WHEEL           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					LT MLG	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	27	959C					278154029				DURING A ROUTINE INSPECTION THE AMT ENCOUNTERED DIFFICULTY WHILE REMOVING THE LT MAIN GEAR WHEEL ASSEMBLY AXLE RETAINING	 NUT.  HE STOPPED AND DEFLATED THE TIRE.  THE WHEEL WAS THEN REMOVED EASILY. FOLLOWING REMOVAL THE WHEEL WAS FOUND TO BE	 SEVERELY CORRODED AND ALL BUT ONE WHEEL-HALF RETAINING BOLT HAD FAILED.  THE LOG BOOK ENTRY INDICATED THAT THE WHEEL HA	D LSAST BEEN DISASSEMBLED 217 HOURS AGO. (K)			1	L	7	2 	3O	3	O		1A10    	1E4				 
	20080715		SO  	2008	7	15	2008FA0000409    	1	20080607	G	2434	32C22491	ALTERNATOR      			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  						DAMAGED         	D				O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			EA	13	30969					3246230	L3047448A			4 SCREWS THAT HOLD THE RECTIFIER PLATE INTO THE BACK CASE OF ALTERNATOR CAME LOOSE AND CONTACTED THE ROTOR, DESTROYED AL	TERNATOR. (K)					1	L	7	1 	3O	3	O		A3SO    	1E4				 
	20080715		EA  	2008	7	15	2008FA0000410    	2	20080527	G	7250	3013411	TURBINE         			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	DAMAGED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	3105E	1026 				T34177	PCE56299			06/20/2008 REPORT: ON 5/27/08 AC UNDER LOAD IN TURN EXPERIENCED ENGINE FAILURE RESULTING IN ACCIDENT.  LOUD BANG! ENGINE	 QUIT.  CT TURBINE TEETH MISSING, NR 2 BEARING DESTROOYED.  1026.1 HOURS ON PMA BLADES PQ0812NE. (K)(NTSB: DFW08CA155)					1	L	7	1 	3T	4	T		A3SW    	E4EA				 
	20080715		CE  	2008	7	15	2008FA0000411    	1	20080612	G	3230		ROD END         			CESSNA	310   	T310Q       	2074244	CE  	LYC   	O360  	IO360A1A    	41514	EA  					LANDING GEAR	BROKEN          	G				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			EA	39	7044Q					T310Q0204				AFTER TAKEOFF, WHEN RETRACTING GEAR, PILOT HEARD LOUD CRACK.  NOSE GEAR WOULD NOT RETRACT.  AIRCRAFT LANDED WITH NOSE GE	AR TRAILING AFT.  NOSE GEAR COLLAPLSED ON LANDING.  INSPECTION REVEALED ROD END UNDER PILOT`S FLOOR THAT CONNECTS NOSE G	EAR RETRACT ROD TO BELLCRANK SEPARATED CAUSING NOSE GEAR TO BECOME DISCONNECTED FROM LANDING GEAR TRANSMISSION.				1	L	7	2 	3O	3	O		3A10    	1E10				 
	20080717		NE  	2008	7	17	2008FA0000412    	2	20080528	G	7510	101910026191	CONTROL ARM     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LT NACELLE	WORN            	B			CWNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	6604L	100  				BB1121				LT ENGINE NACELLE ICE-VANE CONTROL ARM HAD WORN OUT OR DESTROYED BUSHINGS AT ALL 3 ACTUATING CONTROL ARM DRIVE POINTS AN	D LINKS, CAUSING POTENTIAL FOR F.O.D. TO ENGINE.  WHEN ICE VANE IS IN THE RETRACTED POSITION THERE ARE NO HARD STOPS TO 	KEEP IT FROM VIBRATING. (K)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20080715		GL  	2008	7	15	2008FA0000413    	3	20080423	G	6114	05522311	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170E      	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	897LP	570  				172S8897				REPEATED FINDINGS OF CRACKS AT EDGE OF WASHER FOOT PRINT.  ALLOY CHANGE, OR HARDWARE CHANGE MAY HELP. (K)						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
	20080715		EA  	2008	7	15	2008FA0000414    	2	20080701	G	7310	RSA5AD1	INJECTOR        			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	TIO540AK1A  		EA  					FUEL SERVO	CLOGGED         	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	23	101LP	569  				T18208265	L1165861A			PLANE LOST ENGINE POWER, BECAME VERY LEAN, COULD NOT GET FUEL FLOW> 9 GPH. TURNED OUT TO BE ALUMINUM SHAVING FROM ORIGIN	AL MFG OF FUEL SERVO.  CLOGGED MIXTURE HOLE INSIDE FUEL SERVO.  THIS WAS A DEFECT FROM TIME OF MANUFACTURE OF FUEL SERVO	.  EMERGENCY LANDING.  (K)				1	H	7	1 	3O	3	O	NT	3A13    					 
	20080718			2008	7	18	2008FA0000415    	2	20080505	G	7414	S6LSC204T	MAGNETO         			BEECH 	58    	58          	1152740	CE  										ENGINE	FAILED          	B			NW4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	142DR	4    				TH1458				SMOKE WAS REPORTED IN COCKPIT.  UPON INVESTIGATION, FOUND PIN HOLE CORRODED IN METAL LINE CLOSE TO AIR CONDITIONER BLOWE	R MOTOR. ALCOHOL SOAKED INSULATION NEAR FRONT BULKHEAD.  BURNED SOME INSULATION AND AIR CONDITION FILTER HAD HOLE BURNED	 IT ALSO.  WAS UNABLE TO FIND LEAK WITHOUT LINE REMOVAL AND PRESSURE TEST.  CONTACT POINT PN 10-382585 WAS FOUND IN MAGN	ETO.  POINT CONTACT SURFACE WAS DEBONDED FROM BASE.  RESULT WAS FAILED MAGNETO.  FOR INFO ONLY - TO SEE IF MORE BREAKER 	POINTS SHOW SAME TYPE OF FAILURE MAY BE MFG PROCESS. (K)		1	L	7	2 	3O				3A16    					 
	20080715		SO  	2008	7	15	2008FA0000416    	1	20080609	G	5720	494718	TAPE            			PIPER 	PA28  	PA28161     	7102803	SO  										WING	PEELING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	8369A					288116198				STUDENT PILOT DECLARED AN EMERGENCY AS HE THOUGHT NOISE HE WAS HEARING WAS HIS ENGINE COMING APART.  AFTER SAFELY LANDIN	G IT WAS FOUND THAT THE NOISE WAS THE ANTI-SLIP WINGWALK MATERIAL SLAPPING THE WING, IN THE SLIP STREAM.  WIND GOT UNDER	 THE MATERIAL AND LIFTED UP A SECTION OF IT, PEELING IT BACK ENOUGH TO MAKE THE "SLAPPING- BANGING" NOISE HE HEARD.  REM	OVED THE OLD WING WALK MATERIAL AND INSTALLED NEW PIECE.  (K)			1	L	7	1 	3O				2A13    					 
	20080715		SO  	2008	7	15	2008FA0000418    	1	20080628	G	3246		WHEEL           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					RT MLG	BROKEN          	D			PP4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	959C	217  				278154029				DIFFICULTY WAS ENCOUNTERED WHILE AN AMT WAS REMOVING THE RETAINING NUT FROM THE AXLE ON THE RT MAIN GEAR OF AC.  HE STOP	PED  AND DEFLATED THE TIRE. THE WHEEL ASSEMBLY WAS THEN REMOVED WITHOUT RESISTANCE.  AFTER REMOVAL ALL BUT ONE OF THE AS	SEMBLY RETAINING BOLTS WERE FOUND BROKEN AND THE WHEEL HALVES WERE ALSO BROKEN.  CORROSION CAUSED THE PROBLEM.  THE WHEE	L HAD ACCUMULATED 217 HOURS SINCE IT WAS LAST DISASSEMBLED AND INSPECTED.  TT ON THE WHEEL IS UNKNOWN.  THE ENTIRE WHEEL	 ASSEMBLY WAS REPLACED.  (K)		1	L	7	2 	3O	3	O		1A10    	1E4				 
	20080715		GL  	2008	7	15	2008FA0000419    	1	20080618	G	5210	DA4522100002	DOOR            			DIAMON	DA40  	DA40        	2990002	GL  										REAR PAX DOOR	DEPARTED        	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			WP	28	686US	615  				40640				ON TAKE-OFF ROLL AT VR, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)						1	L	7	1 	3O			NT	A47CE   					 
	20080715		GL  	2008	7	15	2008FA0000420    	1	20080618	G	5344		HINGE           			DIAMON	DA40  	DA40        	2990002	GL  										DOOR	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	686US					40640				FOUND CRACKS IN AFT DOOR HINGE.  (K)						1	L	7	1 	3O			NT	A47CE   					 
	20080715		GL  	2008	7	15	2008FA0000421    	1	20080618	G	5210	DA4522100002	DOOR            			DIAMON	DA40  	DA40        	2990002	GL  										REAR PAX DOOR	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			WP	28	605US	225  				40675				WHILE TAXIING INOT TAKEOFF POSITION ON RUNWAY, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)						1	L	7	1 	3O			NT	A47CE   					 
	20080715		GL  	2008	7	15	2008FA0000422    	1	20080616	G	5210	DA4522100002	DOOR            			DIAMON	DA40  	DA40        	2990002	GL  										AFT PAX DOOR	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			WP	28	605US	536  				40675				ON TAKEOFF CLIMBOUT, AFT PASSENGER DOOR DEPARTED AIRFRAME.						1	L	7	1 	3O			NT	A47CE   					 
	20080715		GL  	2008	7	15	2008FA0000424    	1	20080616	G	5210	DA4522100002	DOOR            			DIAMON	DA40  	DA40        	2990002	GL  										REAR PASSENGER	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			WP	28	605US					40675				ON TAKEOFF CLIMBOUT, AFT PASSENGER DOOR DEPARTED AIRFRAME.  (K)						1	L	7	1 	3O			NT	A47CE   					 
	20080715		GL  	2008	7	15	2008FA0000426    	1	20080618	G	5344		HINGE           			DIAMON	DA40  	DA40        	2990002	GL  										DOOR	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	28	686US					40640				FOUND CRACKS IN AFT DOOR HINGE.  (K)						1	L	7	1 	3O			NT	A47CE   					 
	20080717		NM  	2008	7	17	2008FA0000427    	1	20080601	G	2751	18195816	TRANSMITTER     			BOEING	767   	767241      	1385115	NM  	GE    	CF6   	CF680C2*    	 	GL  					FLAP POSITION	FAULTY          	W			TAMF	A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	23	770QT					23802				LT FLAP DID NOT MOVE FROM 1 TO UP POSITION. FLIGHT RETURNED TO DEPARTURE.  REMOVED AND REPLACED PROXIMITY SENSORS S282 A	ND S283 IAW SWPM 20-30-12 AND AMM 27-88-01, BITE TEST PSEU WAS PERFORMED AND IT WAS FOUND NORMAL IAW FIM 32-09-03, FIG 1	03. FLAP POSITION TRANSMITTER NR 5 WAS REMOVED AND REPLACED IAW MM 27-51-45, PG 201-222, OPS CHECK NORMAL, OVERWEIGHT LA	NDING INSPECTION WAS ACCOMPLISHED IAW MM 05-51-35 PHASE I, OPTION A, PG 201-203, NO DAMAGES WERE FOUND.  (K)			2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
	20080718			2008	7	18	2008FA0000428    	4	20080610	G	3420		LIGHT           			BOEING	767   	767241      	1385115	NM  	GE    	CF6   	CF680C2*    	 	GL  					ALTITUDE INDICAT	ILLUMINATED     	W			TAMF	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	23	770QT					23802				CABIN ALT AND CABIN ALTITUDE LIGHTS ILLUM, EICAS MSG CABIN ALTITUDE WAS DISPLAYED.  UNABLE TO RESTORE CABIN PRESS USING 	MANUAL MODE. AIRPLANE RETURNED TO DEPARTURE. IAW FIM 21-31-00, FIG 103 BLOCKS 1,2,22,23,23A, 24, 44, PLN U3 IN CONNECTOR	 D2712A WAS REPAIRED. REF WDM 21-31-11/21-31-21.  TEST WITH AIRCRAFT PRESSURIZED ON GROUND IS SATISFACTORY.  (K)				2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
	20080717		CE  	2008	7	17	2008FA0000429    	1	20080605	G	3222	66420003	PISTON          			CESSNA	500   	560CESSNA   	2076750	CE  										NLG	LOOSE           	B			CWQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	351QS	1556 				5600451				( REF CWQR200801)  DURING A1-5 PHASE INSPECTION, FOUND EXCESSIVE PLAY INT HE NOSE GEAR FWD AND AFT PLAY CHECK.  AFTER FU	RTHER INSPECTION , FOUND THE NOSE GEAR FORK LOOSE ON THE PISTON. THEN THE SAFETY BOLT WAS REMOVED THE FORK FELL FROM THE	 PISTON.  THIS SHOULD BE AN INTERFERENCE FIT.  THIS IS A LOW TIME AC AND APPEARS TO BE A MFG PROBLEM.  FILED SCR NR 3632	22 WITH MFG. (K)			2	L	7	2 	4F			RT	A22CE   					 
	20080717		EA  	2008	7	17	2008FA0000430    	1	20080625	G	3230	7455025	CONTROL PANEL   			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	30015	NE  					MLG	MALFUNCTIONED   	B			RO3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	614BA	1176 				5614				LANDING GEAR HANDLE DIFFICULT TO ACTUATE TO UP POSITION.  REQUIRED MULTIPLE ATTEMPTS TO ACTUATE GEAR HANDLE.  FOUND LIGH	TED COVER PANEL LOOSE ON GEAR HANDLE ASSEMBLY.  REMOVED LIGHT PANEL TO INVESTIGATE.  FOUND ONE SCREW FROM BACKSIDE OF PA	NEL HAD FALLEN OUT AND WAS INTERFERING WITH GEAR UP RELEASE MECHANISM.  REINSTALLED SCREW AND TIGHTENED ALL OTHERS .  RE	INSTALLED LIGHT PANEL. PREFORMED MULTIPLE GEAR SWINGS, NO FAULTS NOTED.  (K)			2	L	7	2 	4F	4	F	RT	A21EA   					 
	20080718		NM  	2008	7	18	2008FA0000431    	1	20080630	G	5320	715K9004507	ANGLE           			BOEING	717   	717200      	1383700	NM  										BS 26	CRACKED         	A			MWEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	970ME					65171				RT UPPER BUCKET, FWD OB Z-FRAME IS CRACKED AT STA 26 APPROXIMATELY 1 INCH LONG.  FABRICATED AND INSTALLED ANGLE.  (K)						2	L	7	2 	4F			TR	A6WE    					 
	20080717		CE  	2008	7	17	2008FA0000432    	1	20080602	G	3260	602EN166B	DOWNLOCK SWITCH 			CESSNA	501   	551         	2076605	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT MAIN GEAR	INOPERATIVE     	B			UPWR	O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			GL	03	502CL					5510002				RT MAIN GEAR GREEN INDICATOR DID NOT ILLUMINATE WHEN GEAR EXTENDED GOING INTO LAND.  CYCLED GEAR AND GREEN INDICATOR LIG	HT REMAINED OUT.  AC LANDED WITHOUT INCIDENT.  RT MAIN GEAR DOWNLOCK SWITCH FOUND TO BE FAULTY.  (K)					1	L	7	2 	4F	4	F		A27CE   	E1NE				 
	20080717		EA  	2008	7	17	2008FA0000433    	1	20080521	G	2751	60093000123	ASYMMETRY SWITCH			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CE	21	779AZ					5176				FLAPS FAIL FOUR DEGREES AFTER SELECTION.  USING BREAKOUT BOX, SELECTED THIS BDU AND FLAPS WOULD CONSISTENTLY FAIL. SELEC	TED OTHER SIDE BDU AND FLAPS WOULD OPERATE NORMALLY.  UNIT ALSO RATTLES ON BENCH WHEN CHECKING DRAG TORQUE (UNLOCKED).  	(K)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080717			2008	7	17	2008FA0000434    	1	20080605	G	2560		RELEASE MECH    																	SEAT BELT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25										SEAT BELT WILL RELEASE WITHOUT PULLING ON THE RELEASE BUCKLE.  DURING FLIGHT THE SEAT BELT CAME UNDONE WITHOUT ANYONE PH	YSICALLY UNLATCHING THE BELT.  CAUSE WAS DUE TO DEFECTIVE LATCH MECHANISM.  ALL BELTS WITH CERTAIN BATCH NUMBERS ARE DEF	ECTIVE.  (1-954/784-3178 MFG) (K)																	 
	20080717		NM  	2008	7	17	2008FA0000435    	1	20080627	G	3213	656174010	CYLINDER        	BOEING      		BOEING	737   	7373B7      	1384580	NM  										MLG	CRACKED         	B				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			WP	07	514AU				XC92439	23700				AFTER AIRCRAFT TOW, FLUID WAS OBSERVED LEAKING FROM .5 INCH CRACK (APPROXIMATE) IN THE OUTER CYLINDER OF THE LT MLG SHOC	K STRUT.  THE CRACK IS LOCATED APPROXIMATELY 26 INCHES BELOW THE SHOCK STRUT AIR VALVE.  (K)					2	L	7	2 	4F			RT	A16WE   					 
	20080717		SO  	2008	7	17	2008FA0000436    	2	20080506	G	8530	SA52006A1	CYLINDER        			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520BA     	17032	SO  					NR 4	CRACKED         	B			BJFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	2024W					D8078	241723R			CRACK VISIBLE AT NR 4 CYLINDER. CRACK APPEARS TO START AT CASTING ANOMALY, CONTINUES TO EDGE OF FINS, AND IS VISIBLE AT 	THE FIRST FOUR COOLING FINS. ALSO VERIFIED, THROUGH USE OF EDDY CURRENT, THAT THE CRACK CONTINUES TO THE SPARK PLUG HOLE	. ALL OTHER CYLINDERS HAVE SIMILAR CASTING ANOMALIES WITH INDICATIONS OF DISCONTINUITIES FOUND WITH EDDY CURRENT EQUIPME	NT. THIS FACILITIES OPINION IS THAT POOR CASTING TECHNIQUES BY THE MFG LEFT STRESS POINTS FOR THE FORMATION AND CONTINUA	TION OF CRACKS, AND MORE THAN LIKELY, ANY CYLINDER NOT YET CRACKED, PROBABLY WILL. (K)		1	L	7	1 	3O	3	O		3A15    	E5CE				 
	20080717			2008	7	17	2008FA0000437    	4	20080618	G	2211	31B641	TRIM SWITCH     			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					CONTROL WHEEL	FAILED          	B			QPID	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	362MC				3188E	LJ760				AFTER INSTALLATION OF NEW MFG AUTOPILOT SYS, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT. COMPUTER WAS	 RETURNED TO MFG AND REINSTALLED AFTER REPAIR.  TRIM CIRCUITRY FAILED AGAIN AND RETURNED TO MFG. MFG TECH SUPPORT ADVISE	D REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAILURE. SWITCHES IN ASSY FAILED ALLOW	ING BOTH UP & DOWN COMMANDS AT THE SAME TIME. TRIM SWITCH ASSY PROVIDED BY MFG, WAS REPLACED & COMPUTER REPAIRED & REINS	TALLED.  TRIM CIRCUITRY FAILED AGAIN AFTER 3 HOURS OF FLT.  COMPUTER REPAIRED & REINSTALLED. TRIM CIRCUITRY FAILED ON IN	ITIAL CHECKOUT.  COMPUTER REMOVED FOR REPAIR & TRIM SWITCH CONFIRMED TO BE CAUSING FAILURE AGAIN. TRIM UP SWITCH STUCK I	1	L	7	2 	3T	4	T		3A20    	E4EA				 
	20080717		CE  	2008	7	17	2008FA0000438    	1	20080630	G	2910	605700311	HOSE            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					HYD SYSTEM	FAILED          	E			JBGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	260AN	5025 				124	PCECA0083			PILOT REPORTED A LOSS OF HYDRAULICS DURING FLIGHT AT CRUISE FL400.  INSPECTION REVEALED THAT THE RT ENGINE DRIVEN HYDRAU	LIC PUMP, PRESSUE SIDE HYDRAULIC LINE WAS LEAKING, AND ALLOWED THE AIRCRAFT`S HYDRAULIC SYSTEM FLUID TO BE DEPLETED.  FU	RTHER INSPECTION REVEALED THAT THE LINE HAD FAILED INTERNALLY AND WHEN PRESSURE WAS APPLIED THE HOSE WOULD SWELL AND BEG	IN TO LEAK.  THE PROBABLE CAUSE OF THE FAIURE IS AGE AND POSSIBLE EMBRITTLEMENT OF THE HOSE.  TO POSSIBLY PREVENT RECURR	ENCE OF SUCH FAILURES AT TIME INTERVAL FOR REPLACEMENT OF AGEING TEFLON HOSES MAY BE NEEDED.  (K)		2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
	20080717		GL  	2008	7	17	2008FA0000439    	1	20080701	G	2430		BEARING CAP     			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ALTERNATOR CASE	CRACKED         	B			YD5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	391CP				1042440	3072	691753	FP6720B		PILOT REPORTE TO HAVE AN ALTERNATOR NR 1 FAILURE DURING GROUND PRE-FLIGHT RUN-UP.  AC WAS BROUGHT IN FOR MAINTENANCE TO 	TROUBLESHOOT ALTERNATOR ISSUE. ALTERNATOR BEARING END CAP WHICH IS PART OF THE ALTERNATOR CASE COMPLETED CRACKED OFF AND	 WAS LYING ON THE ENGINE BAFFLING.  AC WAS FURTHER INSPECTED WITH NO OTHER DISCREPANCIES FOUND. ALTERNATOR WAS REPLACED 	WITH NEW.  GROUND AND FLIGHT TESTS CHECK GOOD. (K)			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
	20080717		SW  	2008	7	17	2008FA0000440    	1	20080610	G	6720	206011725001	ROD             			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					T/R PITCH	CHAFED          	B			ULXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	600W					51250				DURING AN INSPECTION OF THE TAIL ROTOR PITCH CONTROL TUBE SLEEVES, WE DISCOVERED THAT BELLCRANK PN 206001763001 HAD BEEN	 CHAFED INTO BY THE RIVET SECURING THE ROD END OF ROD ASSEMBLY PN 206011725001. THIS WEAR OCCURS WHEN LEVER ASSEMBLY PN 	206011722105 PIVOT DURING CONTROL MOVEMENTS, CHANGING THE PLANE OF THE ROD.  THE MM DOES NOT TELL YOU WHICH WAY TO INSTA	LL THE ROD, HOWEVER ALL OF THE ILLUSTRATIONS SHOW THE RIVETED END OF THE ROD TO BE CONNECTED TO THE BELLCRANK.  PLEASE S	EE BHT 206L SERIES IPB, FIG 64-1 AND FIG 67-12 AND BHT 206L MM, PARA 67-63, FIG 67-17 DETAIL D. PARA 64-20 AND FIG 64-14	.  THIS CAN BE CURED BY INSTALLING THE ROD WITH THE ADJUSTABLE END CONNECTING TO THE BELLCRANK AND THE RIVETED END CONNE	1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20080717		GL  	2008	7	17	2008FA0000441    	2	20080604	G	7230	23009670	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					COMPRESSOR	FAILED          	B				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	05	3WV				CAC45603	53713	CAE847787			PILOT REPORTED ENGINE CHIP LIGHT PRECAUTIONARY LANDING MADE TO INVESTIGATE. A CONSIDERABLE AMOUNT OF FERROUS MATERIAL WA	S ON THE TOP AND BOTTOM CHIP DETECTORS.  NO PENALTY RUNS WERE PERFORMED. AIRCRAFT WAS PLACED ONTO A TRAILER AND MOVED BA	CK TO BASE WHERE THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR INVESTIGATION.  THE DISMANTLE AND INVESTIGA	TION REVEALED THE NR 2 BEARING THAT SUPPORTS THE REAR OF THE IMPELLER HAD FAILED. THE BALL BEARING KEEPER HAD FRACTURED 	COMPLETELY ACROSS THE SURFACE. AT LEAST ONE OF THE BALLS HAD SPALLED AND ALSO THE OUTER RACE HAD SEVERAL AREAS OF SPALLI	NG.  THE FAILED BEARING WAS REPLACED, THE REMAINDER OF THE ENGINE OIL SYSTEM WAS FLUSHED WITH NO DISCREPANCIES NOTED.  E	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20080717			2008	7	17	2008FA0000442    	1	20080701	G	3610	AS18954175	COUPLING        								CFMINT	CFM56 	CFM567B26US 	 	NE  					ENGINE DUCT	MISSING         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	33							894464			DURING GROUND RUN AFTER INSTALLATION, HOT AIR ESCAPED FROM THE NOSE COWL ANTI-ICE DUCT AT THE 12 O`CLOCK POSITION CAUSIN	G THERMAL DAMAGE TO THE C-DUCT THERMAL BLANKETS AND TRUST LINK TEFLON WASHERS.  INVESTIGATION FOUND DUCT COUPLING PN AS1	895-4-175 MISSING.  ENGINE WAS RELEASED FOLLOWING MAINTENANCE TO RECTIFY HIGH OIL PRESSURE INDICATIONS IN FEB 2008.  (K)									4	F			E00055EN				 
	20080717		EA  	2008	7	17	2008FA0000443    	2	20080617	G	8530		GUIDE           			CESSNA	210   	T210N       	2073456	CE  	CONT  	O550  	IO550P      	17216	EA  					EXHAUST VALVE	OUT OF TOLERANCE	C			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6621A					21063559				AFTER NUMEROUS ATTEMPTS TO TROUBLESHOOT FREQUENT ENGINE MISFIRES OCCURRING PRIMARILY IN THE INITIAL CLIMB STAGES OF FLIG	HT, THE ENGINE VALVE TRAIN WAS INSPECTED FOR STICKING VALVES.  DIMENSIONAL INSPECTIONS OF THE EXHAUST VALVE GUIDES IN AL	L 6 CYLINDERS REVEALED THAT THE EXHAUST VALVE GUIDES WERE BELOW THE MINIMUM ACCEPTABLE DIAMETERS AS PUBLISHED IN THE APP	LICABLE O/H MANUAL.  IT IS BELIEVED THAT THE EXCESS MATERIAL EXISTS BECAUSE THE GUIDES WERE NOT MEASURED OR REAMED DURIN	G THEMFG ASSY PROCESS.  CORRECTIVE ACTION NOT AVAILABLE AT THIS TIME.  (K)		1	H	7	1 	3O	3	O		3A21    	E3SO				 
	20080717			2008	7	17	2008FA0000444    	4	20080609	G	6113		BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					PROP SPINNER	CRACKED         	B			OMKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	537SP					172S8393				DURING A 100 HR INSPECTION, PROPELLER SPINNER FWD BULKHEAD WAS FOUND TO BE CRACKED FROM A PROP BOLT HOLE OUT TOWARD THE 	OUTER EDGE OF THE BULKHEAD, APPROX 1.5 INCH LONG. THE PROP BOLTS AND THE BULKHEAD WERE REMOVED FRO THE AIRCRAFT.  CLOSER	 INSPECTION SHOWED THE CRACK ORIGINATED FROM THE OUTER APEX OF THE WASHER MARK, NOT THE BOLT HOLE ITSELF.  ALSO, ALL BOL	T HOLES WERE FOUND TO BE CRACKED IN THE SAME LOCATION (OUTER APEX OF WASHER IMPRESSION), RANGING FROM .2500 TO 1.0 IN LE	NGTH.  THE MM HAS A NOTE THAT SAYS, "THE MOUNTING BOLT HOLES IN THE FORWARD BULKHEAD MAY BE UNDERSIZED DUE TO THE ORIGIN	AL TORQUING OF THE MOUNTING BOLTS".  IT IS PLAIN TO SEE THIS CRUSHES THE ALUMINUM, CASUING STRESS CONCENTRATIONS AROUND 	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080717		CE  	2008	7	17	2008FA0000445    	1	20080611	G	5210	1014300329	PIN             			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6*        	52043	EA  					PAX DOOR	MISSING         	B			XA14	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	10TX	3132 				FL1				UPPER AFT ENTRANCE DOOR BAYONET SHIFTED OB .7500 INCH CAUSING AC TO DEPRESSURIZE.  THIS WAS CAUSED BY A PIN (PN 101-4300	32-9) FALLING OUT OF PLATE (101-4300323) CAUSING ROLLER (PN 50-430037-7) TO FALL OUT.  THIS CAUSED ROD (PN 50-430016-11)	 WITH BOLT (PN 50-430177-5), (ASSY CALLED A DOOR BAYONET), TO SHIFT OUTBOARD .7500 INCH THROUGH AFT DOOR FRAME (PN 50-43	0032-3 INSTALLED 180 DEGREE OUT.  THE PINS THAT HOLD THE ROLLERS IN PLACE ARE STAKED.  IT LOOKS AS THOUGH OVER TIME THAT	 THE PIN WORE THE STAKES SMOOTH AND THUS ALLOWING PIN AND ROLLER TO FALL OUT..  STAKED PINS SHOULD BE CHANGED TO COTTER 	KEYED TYPE PINS TO KEEP THIS FROM HAPPENING ON OTHER AC.  CHECK MFG AND THESE HAVE THE COTTER PIN TYPE PINS.  (K)	2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
	20080717			2008	7	17	2008FA0000446    	1	20080109	G	3500	80130700	CYLINDER        																		OUT OF TOLERANCE	B			AY54	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35	GEZJO									OXYGEN CYLINDER (PN 801307-00, SN ST26121) ARRIVED AT WORKSHOP ON 9TH JAN, 2008, REMOVED OFF OF G-EZJO FOR HAVING LOW CO	NTENTS PRESSURE.  ON CLOSE INSPECTION, IT WAS DISCOVERED THAT THE CYLINDER NECK HAD BEEN MARKED WITH HIGH STRESS STAMPS.	  CYLINDER LAST OVERHAULED BY AVOX.  IN THE RIN STAMP, THE NUMBER 1 CLEARLY SHOWS THAT THE INCORRECT STAMPS HAVE BEEN US	ED. (K)																 
	20080717		GL  	2008	7	17	2008FA0000447    	2	20080529	G	7250	23073853	TURBINE WHEEL   								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05		1036 					CAT34953			TURBINE ASSY RECEIVED FOR REPAIR DUE TO METAL IN OIL.  UPON DISASSEMBLY, IT WAS NOTED THAT THE 1ST STAGE TURBINE WHEEL B	LADES WERE MISSING PIECES OF BLADE MATERIAL.  THE APPARENT IMBALANCE OF THE GP ROTOR ASSY PRODUCED BY THE MISSING BLADE 	PIECES CAUSED THE GP STATOR SEAL TO FRACTURE.  ONE PORTION OF THE STATOR SEAL BEGAN TO ROTATE WITH THE NR 8 BEARING OUTE	R RACE.  THE DOWNSTREAM PORTION OF THE STATOR SEAL BELOW THE FRACTURE REMAINED STATIONARY AND THE GRINDING BETWEEN THE S	TATIONERY PORTION OF THE SEAL AND THE ROTATING PORTION APPEARS TO BE THE SOURCE OF THE METAL.  THE TURBINE WHEEL BLADE T	IPS APPEAR TO HAVE FAILED DUE TO HOT - CORROSION SULFIDATION AS DEFINED IN MFG CSL-1210.  SOME DOWNSTREAM PORTIONS OF TH						3	U			E4CE				 
	20080717		NE  	2008	7	17	2008FA0000448    	2	20080618	G	7250	1975M56G03	NOZZLE          			BOEING	777   	777224      	1385225	NM  	GE    	GE90  	GE9092B     	30036	NE  					ENGINE	FAILED          	B			QEMY	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35	78008	39277	17271			29478	900240			ENGINE SUFFERED AN OVERTEMP AND HPC/HPT ROTOR VIBRATION EXCCEEDANCE.  THE CUSTOMER REPORTED METAL PARTICLES IN THE EXHAU	ST.  DURING ENGINE MODULE DISASSEMBLY AT MFG, IT WAS NOTED THAT THE HPT STAGE 2 NOZZLE ASSY EXHIBITED SIGNIFICANT HARDWA	RE DAMAGE TO THE NOZZLE SEGMENTS, STAGE 1 AND STAGE 2 SHROUDS.  (K)				2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN				 
	20080718		SO  	2008	7	18	2008FA0000449    	1	20080701	G	5340	7955300	FITTING         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					FUSELG TO WNDSHD	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	602FT					2841196				STEEL FITTINGS (PN 79553-00) LT AND (PN 79553-01(RT) WERE FOUND WITH SEVERE CORROSION DURING LT AND RT WINDSHIELD REMOVA	L, THOSE FITTINGS CARRY STRUCTURAL LOADS AND LEFT UNCORRECTED COULD JEOPARDIZE THE INTEGRITY OF THE UPPER FUSELAGE SECTI	ON, PROBABLE CAUSE COULD BE DISSIMILAR METAL CORROSION BETWEEN STEEL AND ALUMINUM AND A FOAM INSTALLED AT FACTORY WHICH 	KEEP MOISTURE IN, FOUND SAME PROBLEM IN OTHER AC.  (K)			1	L	7	1 	3O	3	O		2A13    	E274				 
	20080717		SO  	2008	7	17	2008FA0000450    	1	20080701	G	5340	7955301	FITTING         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					FUSLG TO WNDSHLD	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	602FT					2841196				STEEL FITTING FOUND WITH SEVERE CORROSION DURING LT AND RT WINDSHIELD REMOVAL, THOSE FITTING CARRY STRUCTURAL LOADS AND 	LEFT UNCORRECTED COULD JEOPARDIZE THE INTEGRITY OF THE UPPER FUSELAGE SECTION, PROBABLE CAUSE COULD BE DISSIMILAR METAL 	CORROSION BETWEEN STEEL AND ALUMINUM AND A FOAM INSTALLED AT FACTORY WHICH KEEP MOISTURE IN, I HAVE FOUND THE SAME PROBL	EM IN OTHER AC.  (K)			1	L	7	1 	3O	3	O		2A13    	E274				 
	20080718		GL  	2008	7	18	2008FA0000451    	1	20080609	G	7810		ELBOW           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					RT EXHAUST	MISINSTALLED    	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	04	266SR					2626				WHILE ACCOMPLISHING SERVICE ADVISORY 08-03 IT WAS DISCOVERED THAT RT SIDE EXHAUST ELBOW WHICH IS INSERTED BETWEEN WASTEG	ATE OUTLET FITTING AND TAILPIPE WAS ORIGINALLY INSTALLED BACKWARDS A THE FACTORY. THIS INCORRECT INSTALLATION RESULTED I	N ELBOW HAVING ONLY A .1875 INCH ENGAGEMENT WITH WASTEGATE FITTING AND A 2.2500 INCH ENGAGEMENT IN TAILPIPE.  THE .3750 	INCH ENGAGEMENT COULD HAVE RESULTED IN SEPARATION OF JOINT.  THE 2.2500 INCH ENGAGEMENT CAUSED A 1 INCH OBSTRUCTION IN E	XHAUST GAS PATH.  (K)		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
	20080717		EU  	2008	7	17	2008FA0000452    	1	20080610	G	3411		PITOT TUBE      			AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  						OBSTRUCTED      	D				C				ABORTED TAKEOFF         				P			NO WARNING INDICATION     			TO	TAKEOFF        	1			EA	21	820FX					248				ON TAKEOFF ROLL THE F/O AIRSPEED INDICATOR REMAINED AT ZERO.  THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE G	ATE.  MAINTENANCE FOUND FOD (SPIDER) IN THE PITOT TUBE.  THE TUBE WAS CLEARED AND THE SYSTEM CHECKED GOOD.  THE AIRCRAFT	 WAS RETURNED TO SERVICE.  (K)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
	20080717		SO  	2008	7	17	2008FA0000453    	1	20080510	G	3220		BUNGEE          			PIPER 	PA28  	PA28R201T   	7102813	SO  										LT NOSE WHEEL	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	9581C					28R7803267				THE PILOT SLOWED FOR LANDING AND DEPLOYED THE GEAR. A SAFE CONDITION WAS INDICATED FOR THE MAINS, BUT NOT  FOR THE NOSE.	 THE GEAR WAS CYCLED; HOWEVER AGAIN, NO SAFE NOSE INDICATION. AN EMERGENCY GEAR DEPLOYMENT WAS ATTEMPTED BUT STILL, NO G	REEN NOSE LIGHT.  THE PILOT ASSUMED THAT DUE TO PREVIOUS PROBLEMS WITH THE LANDING GEAR INDICATOR LIGHTS THAT THE NOSE G	EAR HAD PROBABLY DEPLOYED AND CONTINUED THE LANDING. IMMEDIATELY AFTER TOUCHDOWN, THE NOSE LANDING GEAR COLLAPSED.  POS 	INCIDENT INVESTIGATION REVEALED THE LT NOSE WHEEL BUNGEE ASSY; PN 76425-03 HAD BROKEN AND WEDGE IN THE NOSE LANDING GEAR	 PREVENTING EXTENSION. THE FAILURE APPEARS TO HAVE OCCURRED WHEN THE GEAR WAS IN THE RETRACTED POSITION.  (K)	1	L	7	1 	3O				2A13    					 
	20080718		CE  	2008	7	18	2008FA0000454    	1	20080630	G	5510	45A21085003	BRACKET         			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HORIZONTAL STAB	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	184AR	4512 				RK34				HORIZ STAB IB RIBS LT AND RT ROLLER BRACKETS FOUND CRACKED. REPLACED PN 45A21085-003 LT FWD BRACKET.  PN 45A21086-003 LT	 AFT BRACKET, PN 45A21085-004 RT FWD.  BRACKET PN 45A21086-004 RT AFT BRACKET WITH IMPROVED PN 128-620021-0001 (LT) AND 	PN 128-620021-0002 (RT) BRACKETS IAW MFG COMMUNIQU NR 83.  REPLACED PN 45A21146-005 RIB (LT) AND PN 45A21146-006 RIB  	(RT) WITH IMPROVED PN 128-620022-0001 (LT) AND PN 128-620022-0002 (RT) RIBS IAW MFG COMMUNIQU NR 83. INSPECTION NEWLY I	NCORPORATED INTO MM 5-20-02 INSP GUIDE AND SECTION 55-30-00.  (K)		2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
	20080718		CE  	2008	7	18	2008FA0000455    	1	20080626	G	2435	M835366026L	RELAY           			RAYTHN	390   	390         	7150030	CE  										STARTER GEN	STUCK           	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	404JM	444  				RB167				INVESTIGATED PILOT REPORT OF RT ENG STARTER/GEN NOT DISENGAGING FROM START FUNCTION AFTER ENG START. FOUND 80K5 RT ENG S	TART LATCH RELAY STUCK IN START FUNCTION.  RT STARTER/GEN TERMINAL COVER AND COOLING AIR INLET DUCT SHOW SIGNS OF OVERHE	ATING. INSPECTED STARTER/GEN, REPLACED 80K5 RELAY, STARTER/GEN FUNCTIONS NORMAL. HAVE REPLACED NUMEROUS 80K3 AND 80K5 ST	ART LATCH RELAYS IN 390 SERIES AC THAT HAVE FAILED WITH SHORT TIS. RECOMMEND MFG INVESTIGATE WHETHER THIS IS A RELAY QC 	OR DESIGN/INSTALLATION ISSUE.  (K)		1	L	7	2 	3F			RT	A00010WI					 
	20080718		CE  	2008	7	18	2008FA0000456    	1	20080626	G	3020	5188001	VALVE           			RAYTHN	390   	390         	7150030	CE  										ANTI ICE SYSTEM	STUCK           	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	404JM					RB167				REPLACED FAILED RT ENGINE ANTI-ICE VALVE WITH 0 TSOH VALVE ASSY SUPPLIED BY HBC/RAPID; O/H BY MFG, WO R73432, DATED 5/22	/2008.  VALVE ASSY FAILED IN STUCK IN OPEN POSITION, WHEN INITIALLY TESTED FOLLOWING INSTALLATION.  REPLACED VALVE WITH 	ANOTHER RAPID-SUPPLIED VALVE ASSY, OPERATIONS NORMAL. RECOMMEND MFG INVESTIGATE WHETHER THIS IS A QC ISSUE OR IF VALVE A	SSY SUBJECTED TO HIDDEN INTERNAL DAMAGE DUE TO ROUGH HANDLING DURING SHIPPING.  (K)			1	L	7	2 	3F			RT	A00010WI					 
	20080718		SO  	2008	7	18	2008FA0000457    	2	20080710	G	7414	07010003	MAGNETO         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					LEFT	BURNED          	D			GICR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	662AJ					1632				DURING ROUTINE MAINT, THE LT MAGNETO WAS DISCOVERED OUT OF TIME TO ENGINE.  WAS UNABLE TO RE-TIME MAG WITHOUT RE-STABBIN	G.  WHEN REMOVED, OPENED COVER AND FOUND INTERNAL PLASTIC COMPONENTS BURNED WITH SIGNIFICANT AMOUNT OF LOOSE (BURNED) PL	ASTIC PARTS LOOSE WITHIN MAGNETO.  THIS MAGNETO WAS SUPPLIED WITH NEW ENGINE 261.3 HOURS AGO, OTHER THAN MAG TO ENGINE T	IMING BEING OFF, THERE WAS NO INDICATION (OPERATIONALLY) OF A PROBLEM.  THIS IS FIRST TIME HAVE SEEN THIS KIND OF DAMAGE	 TO MAGNETO AND HAVE IT STILL OPERATE.  PERFORM 500 HR INTERNAL INSP OF MAGS AND BEING HALF WAY THERE, IT THEORETICALLY 	WOULD NOT HAVE BEEN DISCOVERED UNTIL 500 HOUR MARK OR TOTAL FAILURE OF MAGNETO.  (K)	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
	20080718		CE  	2008	7	18	2008FA0000458    	1	20080702	G	3230	50452112	FORK            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	FRACTURED       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	60PP					340A0073				LANDING GEAR DOWN ACTUATION ON 7/2/2008 PRODUCED AN INDICATED UNSAFE NOSE LANDING GEAR LIGHT.  AN ATTEMPT TO ACTUATE MAN	UAL EXTENSION OF THE LANDING GEAR PROVED UNSUCCESSFUL SINCE THE NOSE LANDING GEAR DID NOT EXTEND TO A DOWN AND LOCKED PO	SITION.  SUBSEQUENT DAMAGE RESULTED TO THE AIRCRAFT WHEN THE NOSE LANDING GAR COLLAPSED UPON LANDING.  AN INSPECTION OF 	THE AC REVEALED THAT NLG LINKAGE "ADJUSTING FORK" FRACTURED THEREBY DISABLING THE EXTENSION OF THE NLG FROM EXTENDING TO	 A DOWN AND LOCKED POSITION.  EVIDENCE SUGGESTS THAT THE FRACTURE WAS PROGRESSIVE IN NATURE DUE TO INDICATIONS THAT A DE	GRADATION TO THE STRUCTURE OF THIS COMPONENT EXISTED PRIOR TO FAILURE OF THIS COMPONENT. (K)	1	L	7	2 	3O	3	O		3A25    	E8CE				 
	20080718		SW  	2008	7	18	2008FA0000459    	1	20080701	G	2400	102149	METER           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  						MALFUNCTIONED   	C			DDZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	6BU	7003 				4034	CAE270422			AC MAINT HOBBS METER FOUND RUNNING SLOW.  THIS PROBLEM CAUSES THE ACTUAL TT OF THE AC TO BE INCORRECT.  THIS PROBLEM CAU	SED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM.  PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND WO	RN OUT.  RECOMMENDATION TO PREVENT THIS PROBLEM: MAINT HOBBS METER, TO BE CHECKED BY PILOTS CLOCK WEEKLY TO MAKE SURE ME	TER IS RUNNING PROPERLY. (K)			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20080718		SW  	2008	7	18	2008FA0000460    	1	20080701	G	2400	102149	METER           			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  						MALFUNCTIONED   	B			DDZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	75TV	7845 				52095	CAE895710			AC MAINT HOBBS METER FOUND RUNNING SLOW.  THIS PROBLEM CAUSES THE  ACTUAL TT OF THE AC TO BE INCORRECT.  THIS PROBLEM CA	USED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM.  PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND W	ORN OUT.  RECOMMENDATION TO PREVENT THIS PROBLEM; MAINT, HOBBS METER TO BE CHECKED BY PILOTS CLOCK WEEKLY TO MAKE SURE M	ETER IS RUNNING PROPERLY.			1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
	20080718		NM  	2008	7	18	2008FA0000461    	1	20080703	G	5315		FLOORBEAM       			BOEING	737   	73783N      	13844HI	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS294	CORRODED        	B			DU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	304TZ					30675				DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AROUND FASTENERS AT BS 294 FROM RBL-2 TO R	BL 43.  SO NR 245010  NR 27077. (K)					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
	20080718		NM  	2008	7	18	2008FA0000462    	1	20080704	G	5315		FLOORBEAM       			BOEING	737   	73783N      	13844HI	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 328, RBL26	CORRODED        	B			DU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	304TZ					30675				DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AT BS 328, RBL 26 AFT SIDE OF BEAM FOUND T	O BE BEYOND LIMITS.  (K)					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
	20080718		NM  	2008	7	18	2008FA0000463    	1	20080703	G	5315		FLOORBEAM       			BOEING	737   	73783N      	13844HI	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS328	CORRODED        	B			DU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	304TZ					30675				DURING SCHEDULED INSP, FOUND CORROSION IN PAX CABIN FWD WET AREA ON FLOORBEAM AT BS 328 FROM RBL 13 TO RBL 50.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
	20080718		NM  	2008	7	18	2008FA0000464    	1	20080707	G	5315		FLOORBEAM       			BOEING	737   	73783N      	13844HI	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS 344	CHAFED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	304TZ					30675				DURING SCHEDULED INSP, FOUND CLIP NUTS CHAFING FLOORBEAM IN FWD CABIN BS 344, LBL 0 TO LBL 55.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
	20080718		NM  	2008	7	18	2008FA0000465    	1	20080707	G	5315		FLOORBEAM       			BOEING	737   	73783N      	13844HI	NM  	GE    	CFM56 	CFM56*      	13802	NE  					BS344, LBL10	CORRODED        	B			DU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	304TZ					30675				DURING SCHEDULED INS, FUND FWD CABIN BS 344, LBL10, FLOORBEAM CORRODED.  (K)  SO 245010, NR27110						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
	20080718			2008	7	18	2008FA0000466    	4	20080711	G	3460	4052500927	COMPUTER        			BOEING	767   	767*        	       	NM  										FMC	FAILED          	W			ANCF	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	23	421AV					25421				AIR TURNBACK DUE PILOT REPORT 4273256-1; EICAS MSG L FMC FAIL DISPLAYED.  FIM 34-61-00 FOLLOWED L FMC PWR RESET ALL INDI	CATIONS NORMAL. PLS MONITOR FURTHER.  AS A PREVENTIVE ACTION DURING OVERNIGHT; IAW AMM 34-61-01/401 WAS REMOVED AND REPL	ACED THE FLIGHT MANAGEMENT COMPUTER.  (K)				2	L	7	2 	4F			RT	A1NM    					 
	20080718		GL  	2008	7	18	2008FA0000467    	1	20080512	G	6100		SNAP RING       			NAMER 	T6    	AT6F        	6400420	GL  						HAMSTD	23D	23D40       	NE  	PROP GOVERNOR	MISSING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	767WB					12142537				PROPELLER WAS INSTALLED IMPROPERLY.  SNAP RING THAT HOLDS ON PROP NUT AND CRANKSHAFT EXTENSION WAS NOT INSTALLED.  THIS 	ALLOWED CRANKSHAFT EXT TO UNSCREW AND LET PROP GOVERNOR PRESSURE OF 180 LBS TO BE PUT ON ENGINE AND PROPELLER.  THIS CAU	SED PROPELLER AND ENG TO LEAK OIL.  (K)				1	L	7	1 	3R				A2575   		6	C	P719	 
	20080718		CE  	2008	7	18	2008FA0000468    	1	20080701	G	5344	NAS405	HINGE           			BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720A1B    	41546	EA  					CABIN DOOR	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	44MA					LD412	L15595YA			(2) OF THE HINGE LINKS HAD CRACKED OFF ON ONE END.  UPON DISASSEMBLY IT WAS DETERMINED THAT A CRACK HAD FORMED LENGTHWIS	E BETWEEN THE FASTENERS AND THE HINGE LINKS.  POSSIBLE CAUSE MAY HAVE BEEN FATIGUE. (K)					1	L	7	2 	3O	3	O		3A20    	1E15				 
	20080721		GL  	2008	7	21	2008FA0000469    	1	20080616	G	5340		MOUNT           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ALTERNATOR	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	710CD	849  			100575	0013	685689			STANDBY ALTERNATOR MOUNTING FLANGE CRACKED IN (2) PLACES.  OIL GALLING AT MOUNT FLANGE WHERE CRACKS WERE NOTED.  (K)						1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
	20080721		SW  	2008	7	21	2008FA0000470    	1	20080701	G	5343	ED12758	CLEVIS          			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  					RT MLG ACTUATOR	BROKEN          	B			BOER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	122AV					11235				WHEN FLYING IN TO LAND, LANDING GEAR WAS SELECTED DOWN, RT MLG CAME DOWN ABOUT A FOOT AND STOPPED ON (2) ATTEMPTS, UPON 	(3RD) ATTEMPT GEAR CAME DOWN AND INDICATED LOCKED.  AC WAS BROUGHT INTO OUR SHOP AND WHEN THE RT MLG WAS INSPECTED, IT W	AS FOUND THAT CLEVIS ASSY FROM UPPER STRUT HSG TO MAIN ACTUATOR HAD BROKEN IN (2) PIECES, (1) PART STILL ATTACHED TO ACT	UATOR AND THE OTHER WAS STILL IN THE UPPER STRUT ASSY. AN OEM SL REQUIRING THAT THE CLEVIS BE REMOVED EA 500 HR AND INSP	ECTED BY A LEVEL II INSPECTOR.  THIS CLEVIS HAD 274 HR ON IT SINCE THAT INSPECTION, WHERE IT WAS FOUND AIRWORTHY.  ON TH	ESE AC THERE IS A MAIN ACTUATOR AND AN AUXILLIARY ONE WITH ITS OWN CLEVIS MOUNTING ALSO.  LANDING GEAR CAME DOWN AND LOC	1	H	7	2 	3T	4	T		2A4     	E4WE				 
	20080721		NM  	2008	7	21	2008FA0000471    	1	20080601	G	7700	PT25	SENSOR          			BOEING	777   	7772Q8      	1385238	NM  	GE    	GE90  	GE9094B     	30045	NE  					RT ENGINE	FAILED          	W			ASMF	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	23	745AM	10004				32718	900475			AC RETURNED TO DEPARTURE DUT TO RT ENGINE STALLED.  MAINT PERFORMED FIM 75-21 TASK 822 AND STALL INSPECTION IN 1ST, 5TH 	AND 9TH HPC STAGES.  NO DAMAGES WERE DETECTED IAW MM 71-00-00.  RT PT25 SENSOR WAS REPLACED IAW MM 73-21-63, TESTED CORR	ECT.  THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO AIRCRAFT LANDED WITH 211, 400 KGS AND MAXIMUM LANDING WEIGHT IS	 213 KGS. (K)			2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN				 
	20080721		NE  	2008	7	21	2008FA0000472    	2	20080606	G	7200		ENGINE          			BOEING	777   	7772Q8      	1385238	NM  	GE    	GE90  	GE9094B     	30045	NE  					RIGHT	FAILED          	W			ASMF	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	23	745AM	10838				32718				DURING TRANSIT CHECK, THE RT ENGINE WAS DETECTED WITH DAMAGES.  MAINT PERFORMED BOROSCOPIC INSPECTION, DETECTING DAMAGES	 OUT OF LIMITS, SO RT ENGINE WAS REPLACED AND TESTED IAW MM 71-00-02 AND 71-00-00, ALL CORRECT.  (K)					2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN				 
	20080721		NE  	2008	7	21	2008FA0000473    	2	20080619	G	7200		ENGINE          			DOUG  	DC9   	DC987       	3022087	WP  	PWA   	JT8   	JT8D219     	52053	NE  					RIGHT	VIBRATION       	W			ASMF	O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	23	205AM					49405				CAPTAIN REPORTED STRONG VIBRATION IN RT ENGINE WITH EPR`S BETWEEN 1.7 AND 1.75.  TECHS VERIFIED THE RT ENGINE CONDITION 	AND PERFORMED OPERATIONAL TEST IAW AMM 71-00-01 FOUND ALL CORRECT.  VIBRATION WAS WITHIN LIMITS (0.4 UNITS INDICATED). (	K)				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
	20080725		NM  	2008	7	25	2008FA0000474    	1	20080709	G	5230		SKIN            			BOEING	737   	737448      	13844BU	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CARGO DOOR	DENTED          	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				DURING SCHEDULED INSPECTION, FOUND NUMEROUS DENT ON AFT CARGO EXT DOOR SKIN.  S/O 312001, OPS 24422.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
	20080728		NM  	2008	7	28	2008FA0000475    	1	20080627	G	5315		FLOORBEAM       			BOEING	737   	737448      	13844BU	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					BS 986	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				DURING SCHEDULED INSPECTION, FOUND CORROSION ON UNDERSIDE OF "T" CAP REPLACEMENT 986.5 AROUND ATTACH HOLES BL 29R TO BL 	29L, NUMEROUS HOLES. (K)					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
	20080725		WP  	2008	7	25	2008FA0000476    	1	20080617	G	3245	95502677	WHEEL           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D*       	 	NE  					NLG	LOOSE           	W			ANCF	C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			SO	23	160BS	1211 				53463				REJECTED TAKEOFF, DURING T/O ROLL, THERE WAS AND ABNORMAL AND ABRUPT VIBRATION IN THE NOSE SECTION.  IAW AMM 32-21-04, P	AGE 201/210 WAS CHECKED TORQUE LINKS ASSY BY LOOSE AND ADJUSTMENT ALSO WERE CHECK BOTH NOSE WHEELS, IAW AMM 32-40-02 PAG	E 201, PRESS IN BOTH WHEELS 150 PSI IAW AMM 12-16-01 AND IAW AMM 32-22-01, PAGE 201 WERE CHECK BOTH DOORS AND LINKAGE.  	(K)			2	L	7	2 	4F	4	F	RT	A6WE    	E2EA				 
	20080725		NM  	2008	7	25	2008FA0000477    	1	20080602	G	2130	1305027	SELECTOR        			BOEING	767   	767284      	1385184	NM  										CABIN PRESSURE	INOPERATIVE     	W			ANCF	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	23	988AN					24742				AIR TURN BACK, CABIN ALT, CABIN ALTITUDE LIGHT EICAS MSG DISPLAYED OPERATIONAL AND MANUAL MODE RESTORED CABIN PRESS CABI	N AUTO INOP 1 AND 2.  IAW AMM 21-31-01/401.  CABIN PRESSURE SELECTOR WAS REPLACED AND WAS ACCOMPLISHED CABIN PRESSURE CO	NTROL SYS, OPS TEST IAW TASK 21-31-00-705-001.  TEST SATISFACTORY.  (K)				2	L	7	2 	4F			RT	A1NM    					 
	20080725		NM  	2008	7	25	2008FA0000478    	1	20080618	G	5610		WINDOW          			BOEING	767   	767259      	1385136	NM  										COCKPIT	LEAKING         	W			ANCF	C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			SO	23	985AN					24618				REJECTED TAKEOFF, VERY STRONG NOISE AT 2R WINDOW DURING ROLL.  IT WAS APPLY SEALANT IN THE FINISH AROUND THE WINDOW EDGE	 IAW AMM 56-11-00 PAGE 801, DID THE WINDOW TEST IAW AMM 56-11-02, PAGE 601, TEST OK.  (K)					2	L	7	2 	4F			RT	A1NM    					 
	20080725		NM  	2008	7	25	2008FA0000479    	1	20080617	G	2750		FLAP SYSTEM     			BOEING	767   	767283ER    	1385149	NM  										TE FLAPS	MALFUNCTIONED   	W			ANCF	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SO	23	728CG					24728				EMERGENCY LANDING, EICAS MSG TE FLAP DISAGREE DISPLAYED, TRAILING EDGE LIGHT ILLUMINATED WHEN ANY TE FLAP POSITION SELEC	TED.  FLAP FAIL TO MOVE SELECTED POSITION.  IAW FIM 27-51-00, FIG 105, BLOCKS 1,21,22,23,43 WAS ACCOMPLISHED AND IAW FIM	 27-51-00, FIG 104 BLOCK 1 TO 4 IT IS OK, FSEU BITE WAS ACCOMPLISHED.  (K)				2	L	7	2 	4F			RT	A1NM    					 
	20080725		CE  	2008	7	25	2008FA0000480    	1	20080415	G	3233	2317100016	ACTUATOR        			LEAR  	60    	60LEAR      	5170707	CE  										NLG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14						50038				THE NLG ACTUATOR HAD IMPACT MARKS FROM THE LOCKING BALLS IN THE LOCKING CHANNEL. THESE IMPACT MARKS ALSO PUSHED PISTON M	ATERIAL OUT OF THE CHANNEL CAUSING INTERFERENCE WITH THE LOCKING SLEEVE.  THIS INTERFERENCE CREATED METAL SHAVINGS THAT 	INTERFEERED WITH THE DOWN LOCK MECHANISM.  (K)				2	L	7	2 	4F			RT	A10CE   					 
	20080725		EU  	2008	7	25	2008FA0000481    	1	20080702	G	2697	0292697390	CONNECTOR       			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					FIRE DETECTION	CONTAMINATED    	B			QMLR	A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			NM	03	902CF	3746 				3630	22351			DURING CRUISE FLIGHT, THE ENGINE FIRE LIGHT ILLUMINATED.  DURING THE DESCENT FOR A PRECAUTIONARY LANDING, THERE WAS NO S	MOKE TRAILING THE AC AND THE ENGINE FIRE LIGHT EXTINGUISHED AND ILLUMINATED SEVERAL TIMES.  AFTER SECURING THE AC UPON L	ANDING, THE PILOT INSPECTED THE ENGINE AREA AND NO FIRE DAMAGE WAS NOTED. THE MAINTENANCE STAFF CAME OUT AND FOUND MOIST	URE IN THE CONNECTOR PLUG ON THE FIRE DETECTION SYSTEM.  AFTER CLEANING AND INSPECTING THE SYSTEM, THE PILOT PERFORMED A	 CHECK FLIGHT AND THE AC WAS RETURNED TO SERVICE.  (K)		1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20080725		EU  	2008	7	25	2008FA0000482    	1	20080706	G	2150	060018	BELT            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					AIR CONDITIONER	BROKEN          	B			QMLR	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			NM	03	152AC					3574				IMMEDIATELY AFTER TAKEOFF AND LEVELING FOR CRUISE, THE AIR CONDITIONER WAS TURNED ON.  WITHIN A SHORT TIME A STRONG ACRI	D SMELL WAS PRESENT IN THE AIRCRAFT.  THE SOURCE OF THE SMELL WAS UNKNOWN IN FLIGHT. THE AIRCRAFT WAS IMMEDIATELY LANDED	 NEXT TO A HARD-SURFACE ROAD JUST SOUTH OF THE HOSPITAL IN A SOY BEAN FIELD.  THE SKIDS WERE DIRECTLY BETWEEN THE ROWS A	ND NO DAMAGE WAS DONE TO THE FIELD BY THE AIRCRAFT.  AN AMBULANCE WAS IMMEDIATELY DISPATCHED TO THE SCENE AND THE PATIEN	T TRANSFERRED TO THE AMBULANCE FOR TRANSPORT.  THE DUTY MECHANIC WAS IMMEDIATELY CALLED.  THE MECHANIC INSPECTED THE AIR	CRAFT, DETERMINED THE CAUSE OF THE ACRID SMELL AS THE AIR CONDITIONER BELT. THE MECHANIC THEN INSPECTED THE AIR CONDITIO	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20080725		EU  	2008	7	25	2008FA0000483    	1	20080704	G	2150	060018	BELT            			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					AIR CONDITIONER	BROKEN          	B			QMLR	A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			NM	03	105LN					3249				GROUND CREW NOTICED THE SMELL OF FUEL AND VAPOR COMING FROM AIRCRAFT AFTER LIFTING FROM SCENE.  PIC NOTIFIED OF THE CIRC	UMSTANCES.  PIC MADE A PRECAUTIONARY LANDING WITH PATIENT ON BOARD. PIC DETERMINED THAT THE VAPOR WAS COMING FROM THE AI	R CONDITIONER, AND NO FUEL LEAK.  (K)				1	G	7	1 	3U	3	U		H9EU    	E34NE				 
	20080725		CE  	2008	7	25	2008FA0000484    	1	20080516	G	2497		WIRE            			CESSNA	208   	208B        	2073701	CE  										STARTER GEN	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21						208B0989				ON (2) RECENT OCCASIONS (2) AIRCRAFT HAVE HAD IDENTICAL DISCREPANCIES WITH THE STARTER ENERGIZED (SE) CIRCUIT. DURING A 	NORMAL START THE SE ANNUNCIATOR DID NOT EXTINGUISH NORMALLY/AUTOMATICALLY AS THE ENGINE NG INCREASES.  THE ANNUNCIATOR S	TAYS ON UNTIL THE PILOT MOVES THE STAT SWITCH TO "OFF" AT WHICH TIME THE LIGHT GOES OUT AND THE GENERATOR COMES ON-LINE.	  TROUBLESHOOTING IN BOTH OF THESE CASES REVEALED HIGH RESISTANCE IN THE SPEED SENSOR CIRCUIT.  FURTHER INSPECTION REVEA	LED THAT THIS WAS DUE TO POOR WORKMANSHIP (CRIMPED AND POORLY SOLDERED) ON THE WIRE CONNECTIONS INSIDE THE STARTER/GEN (	S/G CONNECTOR.  WIRE WAS PINCHED BETWEEN CONNECTOR AND CASE.  IN BOTH CASES THE S/G HAD BEEN RECENTLY OVERHAULED.  (K)	1	H	7	1 	3T				A37CE   					 
	20080725		NE  	2008	7	25	2008FA0000485    	2	20080709	G	7320	256072	FLOW DIVIDER    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NR 1 ENGINE FUEL	FAILED          	B			B3OR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	03	6001L					5500169	71709			DURING CLIMB OUT AFTER TAKEOFF, NR 1 ENGINE COULD ONLY PRODUCE 85 PERCENT N1.  WHILE RETURNING TO BASE , ENGINE SHUT ITS	ELF DOWN ON 2 MILE FINAL.  TROUBLESHOOTING FOUND THAT FUEL FLOW DIVIDER HAD MALFUNCTIONED.  FUEL FLOW DIVIDER WAS REMOVE	D FROM SERVICE, AND REPLACED WITH AN OVERHAULED UNIT.  AIRCRAFT WAS RETURNED TO SERVICE.  (K)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20080725			2008	7	25	2008FA0000486    	4	20080618	G	2200		TRIM SWITCH     			BEECH 	90    	C90         	1152913	CE  										AUTO PILOT	FAILED          	B			QPIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	362MC				3188E	LJ760				AFTER INSTALLATION OF NEW AUTOPILOT SYSTEM, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT, 10/02/2007.  	COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR.  TRIM CIRCUITRY FAILED AGAIN AND WAS RETURNED TO MFG ON 1/18/	2008.  TECH SUPPORT ADVISED REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAILURE.  MI	CRO SWITCHES IN ASSY FAILED ALLOWING BOTH UP AND DOWN COMMANDS AT THE SAME TIME.  TRIM SWITCH ASSY PROVIDED WAS REPLACED	 AND COMPUTER REPAIRED AND REINSTALLED.  TRIM CIRCUITRY FAILED AGAIN AFTER (3) HOURS OF FLIGHT.  COMPUTER WAS REPAIRED A	ND REINSTALLED ON 2/17/2008.  TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT.  COMPUTER WAS REMOVED FOR REPAIR AND THE TRIM S	1	L	7	2 	3T				3A20    					 
	20080725			2008	7	25	2008FA0000487    	3	20080717	G	6110	D5258	BULKHEAD        			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					PROP MOUNT	CRACKED         	B			CNZ2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	500JL	1279 				CE1603				PROPELLER SPINNER BULKHEAD CRACKING BETWEEN ATTACH BOLT HOLES IN (2) PLACES.  CRACK COULD BE INDUCED FROM VIBRATION. INS	PECT VISUALLY EVERY PRE-FLIGHT.  A BETTER HEAT TREATING PROCESS MAY STRENGTHEN THE BULKHEAD AND REDUCE THE CRACKING FROM	 VIBRATION.  (K)				1	L	7	1 	3O	3	O		3A15    	E5CE				 
	20080725		EA  	2008	7	25	2008FA0000488    	2	20080423	G	7210	3028266	HOUSING         								PWA   	PT6   	PT6A27      	52043	EA  					RGB	BROKEN          	B			UTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19							PCE41761			ABOUT 12 INCHES OF THE RGB FRONT HOUSING SPLINES WERE FOUND BROKEN OFF DUE TO FATIGUE CRACK.  (K)											4	T			E4EA				 
	20080725		CE  	2008	7	25	2008FA0000489    	1	20080620	G	5410	109910029165	INLET           			BEECH 	90    	C90A        	1152911	CE  										LWR AFT COWLINGS	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	5115H	901  				LJ1705				LT AND RT WELD ASSY CRACKED ALONG A WELDED SEAM.  THE CRACKS ARE APPROXIMATELY 12 INCHES LONG.  THESE WELD ASSY ARE A PO	RTION OF THE ENGINE INLET.  A PORTION OF THE INLET AIR IS USED FOR THE OIL COOLER AND SOME AIR IS BYPASSED AND EXITS FRO	M THE LOWER PORTION OF THE COWLING.  THE CRACK IN THE WELD ASSY HAPPENED AT THE UPPER WELDED SEAMS IN THE BYPASS PORTION	 OF THE DUCT.  THE CRACKS POSED NO POTENTIAL PROBLEM OF BEING INGESTED INTO THE ENGINE.  WE HAVE COMMUNICATED THIS ISSUE	 WITH THE MFG OF THE AC. WE DO NOT KNOW OR WANT TO SPECULATE AT THIS TIME WHAT CAUSED THE PROBLEM OR ARE THERE ANY RECOM	MENDATIONS TO PREVENT IT FROM HAPPENING AGAIN. OUR ONLY RECOMMENDATION IS TO INSPECT THIS AREA IN BOTH LT AND RT COWLING	1	L	7	2 	3T			RT	3A20    					 
	20080728		NE  	2008	7	28	2008FA0000490    	2	20080622	G	7200		ACOUSTIC LINER  			DOUG  	DC9   	DC987       	3022087	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LEFT	DAMAGED         	W			ASMF	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	23	216AM	45271	7361 			49586				AC RETURNED TO PLATFORM, DURING ENGINE ACCELERATION UP TO 1.4 EPR, STRONG NOISE IN THE RT ENG WAS HEARD.  MAINT PERFORME	D AN INSPECTION AND DETECTED ACOUSTIC LINER DELAMINATION OF THE DIFFUSER OUTER FAN DUCT, BUT WITHIN LIMITS TO OPERATE TE	N HOURS IAW MM 72-00-00.  AC, DURING OVERNIGHT CHECK, THE RT ENG WAS REPLACED AND TESTED IAW MM 71-00-02 AND MPCM 71-00-	01, ALL CORRECT.  (K)			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
	20080728		GL  	2008	7	28	2008FA0000491    	2	20080709	G	7230	66032	BLADE           			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					IP ROTOR BLADE	DEPARTED        	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	678RF	1040 				5250537	2091			DURING ROUTINE INSP, FOUND DAMAGE TO THE 1ST STAGE STATOR ASSY, UPON FURTHER INSPECTION, FOUND 1 BLADE HAD FAILED AND DE	PART THE LP ROTOR ASSY CAUSING DAMAGE TO THE REST OF THE ENGINE DOWN STREAM.  (K)					1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
	20080725		GL  	2008	7	25	2008FA0000492    	1	20080630	G	2421		FAN             			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ALTERNATOR	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	PROMZ					3041	691724	FP6763		ALTERNATOR NR 2 (BELT DRIVEN ALTERNATOR) COOLING FAN DEVELOPED CRACK AT FAN BLADE RADIUS.  CRACK ELONGATED UNTIL FAN SEP	ARATED FROM ALTERNATOR.  (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
	20080728		GL  	2008	7	28	2008FA0000493    	1	20080623	G	5397		WIRE            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ALT AIR DOOR	FATIGUED        	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	683SR					2766	691392			WIRES THAT CONNECT TO THE ALTERNATE AIR DOOR (WHICH ARE SOLDERED TO THE SWITCH) FOR THE TORNADO ALLEY TURBO SYSTEM ARE B	ECOMING FATIGUED AND SOLDER IS BREAKING AT SWITCH.  IF THE ALTERNATE AIR WAS TO OPEN AND THESE WIRES WERE BROKEN, IT WOU	LD NOT GIVE THE PILOT AN INDICATION THAT THE ALTERNATE AIR DOOR WAS OPEN.  (K)				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
	20080725		SO  	2008	7	25	2008FA0000494    	1	20080715	G	2170	234018623	WATER SEPARATOR 			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  						DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	21	595PE		141  			1373				BOTH UNITS O/H AT MFG.  WHEN CHANGING SOCK, FOUND RUST STAINS ON SOCK.  REMOVED AND FOUND RETAINING CHAIN PN 834639 RUST	ED.  CHAIN WAS WRONG MATERIAL (METAL) AND INCORRECT LENGTH (9.5 INCHES).  REPLACEMENT UNIT WAS SS WITH A TOTAL LENGTH OF	 (6 INCHES).  ALSO ON UNIT 67-272 (1) OF (8) INTERNAL RETAINING SCREWS WAS FOUND NOT SEATED AND IN CONTACT WITH PART GAS	KET.  ALSO FOUND INSIDE SAME UNIT WAS A PIECE OF MASKING TAPE (2 INCHES X 6 INCHES) WITH SN OF UNIT WRITTEN WITH A RED M	ARKER STILL AFFIXED TO INNER COATING OF AFT SECTION.  WO NR TTT91055 (SN 49-945) DATED SEPT 28, 2006. AND CLJ14812 (SN 6	7-272) DATED SEPT 24, 2007.  (K)	2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
	20080728		EU  	2008	7	28	2008FA0000495    	1	20080525	G	2800		FUEL SYS        			RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540*    		EA  						MALFUNCTIONED   	D				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			NE	05	22MW					131				APPROX 9 GALLONS OF FUEL IN CENTER TANK BECAME INACCESSIBLE DURING FLT, PRECAUTIONARY LANDING.    AFTER DEPARTING USING 	CENTER TANK FUEL FOR A 120 MILE FERRY FLIGHT, SWITCHED TO  THE WING TANKS FOR THE PREPONDERANCE OF THE TRIP. NEARING THE	 DESTINATION  WITH THE WING TANKS ALMOST DRY, SELECTED THE FUSELAGE TANK FOR THE REMAINDER OF THE FLIGHT.  THE FUEL FLOW	 METER INDICATED THAT AIR, RATHER THAN FUEL , WAS BEING DRAWN INTO THE SERVO.  THE ENGINE STOPPED.  RESELECTED THE WING 	TANKS; THE ENGINE RESTARTED. ATTEMPTED 4 MORE TIMES TO SOURCE FUEL FROM THE FUSELAGE; EACH TIME, THE ENGINE STOPPED.  MA	DE A PRECAUTIONARY LANDING. MECH DECOWLED ACFT AND CONFIRMED THAT FUEL COULD BE SOURCED INTO THE SERVO FROM EITHER THE W	1	M	7	1 	3O	3	O	NC	EA67U   	1E4				 
	20080725			2008	7	25	2008FA0000496    	4	20080618	G	2200	30B641	TRIM SWITCH     	CENTURY     		AMTR  	SUKHOI	SU26MX      	1152913	GL  	PWA   	PT6   	PT6A21      	52043	EA  					CONTROL COLLUMN	INOPERATIVE     	B			QPID	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	362MC				3188E	LJ760				AFTER INSTALLATION OF NEW AUTOPILOT SYSTEM, AUTOPILOT COMPUTER TRIM CIRCUITRY FAILED ON INITIAL CHECK OUT, OCT 02, 2007.	  COMPUTER WAS RETURNED TO MFG AND REINSTALLED AFTER REPAIR.  TRIM CIRCUITRY FAILED AGAIN AND WAS RETURNED TO MFG ON JAN	 18, 2008.  MFG TECH SUPPORT ADVISED REPLACEMENT OF SUSPECTED BAD TRIM SWITCH ASSY AT THIS TIME AS CAUSE OF REPEATED FAI	LURE. MICRO SWITCHES IN ASSY FAILED ALLOWING BOTH UP AND DOWN COMMANDS AT THE SAME TIME.  TRIM SWITCH ASSY PROVIDED BY M	FG WAS REPLACED AND COMPUTER REPAIRED AND REINSTALLED ON FEB 17, 2008.  TRIM CIRCUITRY FAILED ON INITIAL CHECKOUT.  COMP	UTER WAS REMOVED FOR REPAIR AND THE TRIM SWITCH WAS CONFIRMED TO BE CAUSING THE FAILURE AGAIN.  THE TRIM UP MICRO SWITCH	1	M	7	1 	3R	4	T	NC	EXPA1M71	E4EA				 
	20080728		NM  	2008	7	28	2008FA0000497    	1	20080620	G	2701		BOOT            			ADAMAC	A500  	A500        	05614IQ	NM  	CONT  	O550  	TSIO550E    	17043	SO  					CONTROL COLLUMN	MISINSTALLED    	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	27	896MH					0008				AT LOCATION WHERE CONTROL "STICK" PASSES THROUGH L/R SIDE ARM REST, THE BOOT SURROUNDING BASE OF STICK LIES OPEN TO CONT	ROL MECHANISMS. WHERE THE STICK ENTERS THE COCKPIT, THE LEATHER BOOT THAT IS DESIGNED TO COVER THE AREA BENEATH THE STIC	K, IS PARTIALLY OPEN.  THIS ALLOWS FOREIGN OBJECTS, PLACED ALONG THIS AREA, TO FALL DOWN INTO WHERE CONTROLS COULD BECOM	E JAMMED.  THIS HAS ALREADY OCCURRED, RESULTING IN LOSS OF VERTICAL CONTROL. MFG NEEDS TO ISSUE AN IMMEDIATE AD AND ISSU	E REMEDY FOR THIS SAFETY OF FLIGHT ISSUE.  (K)		1	L	7	2 	3O	3	O	RT	A00009DE	E5SO				 
	20080725		CE  	2008	7	25	2008FA0000498    	1	20080711	G	5510	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	66970					15281696				WHILE CONDUCTING A 100 HOUR INSPECTION ON THE AIRCRAFT, COMPLYING WITH AD80-11-04 (NUTPLATE INSPECTION).  UPON INSPECTIO	N, IT WAS FOUND THAT NOT ONLY WAS THERE A CRACKED NUTPLATE, BUT THERE IS ALSO A (1 INCH) CRACK IN THE WELDED BRACKET- TH	E PART THAT THE NUTPLATES MOUNT TO.  IT CAN BE SEEN IN MFG ILLUSTRATED PARTS CATALOG, FIGURE 18, ITEM NR 10.  UPON REMOV	ING THE BRACKET FROM THE AIRCRAFT, ALSO DISCOVERED THAT A LARGE PORTION OF THE STEEL BRACKET HAD BEEN RUSTED; PARTICULAR	LY IN THE WELDED AREAS.  BECAUSE MFG NO LONGER MAKES THIS PART, ACQUIRED A SERVICEABLE PART, INSPECTED THE WELDS, TREATE	D THE CORROSION, AND INSTALLED IT ON THE AIRCRAFT.  (K)	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
	20080725		CE  	2008	7	25	2008FA0000499    	1	20080716	G	2750	98600581	CONTROL CABLE   			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					FLAPS	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	2423S					21061275				ORDERED NEW MFG FLAP FOLLOW UP CABLE; TO REPLACE ORIGINAL CABLE WHICH HAD BECOME DEFECTIVE DUE TO NORMAL USAGE AND AGE. 	 THIS CABLE IS SIMILAR TO A THROTTLE CABLE WITH AN INSIDE CABLE WHICH SLIDES IN AN OUTSIDE HOUSING. UPON INSTALLATION, O	F NEW MFG  FLAP FOLLOW UP CABLE, OPERATION WAS VERY ROUGH AND INTERMITTENT.  SMOOTH OPERATION IS CRITICAL TO MEET MM SPE	CS AND AIRCRAFTS FLIGHT MANUAL REQUIREMENTS FOR CERTAIN SPECIFIED  FLIGHT CONFIGURATIONS.  CONTACTED MFG SERVICE CENTER 	AND THEN MFG TECH SUPPORT DIRECT.  MFG ASSURED, VERBALLY THE CABLE HAS BEEN MFG TO ORIGINAL SPECIFICATIONS.  FROM FIRST 	GLANCE, CABLE IS OBVIOUSLY CONSTRUCTED IN A DIFFERENT MANNER AND OF DIFFERENT MATERIAL OF ORIGINAL PART ON THIS AND OTHE	1	H	7	1 	3O	3	O		3A21    	E8CE				 
	20080725		CE  	2008	7	25	2008FA0000500    	1	20080713	G	7897		WIRE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D5      	52112	NE  					THRUST REVERSER	CHAFED          	D				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			EA	23	67SF	6216 				5500243				ON CLIMB OUT, AFTER DEPARTURE, THE LT THRUST REVERSER DEPLOY LIGHT ILLUMINATED.  NO ABNORMAL FLIGHT CHARACTERISTICS WERE	 FELT IN THE AC.  AFM PROCEDURES WERE FOLLOWED AND A SAFE LANDING BACK AT DEPARTURE AIRPORT WAS MADE.  AFTER LANDING, TH	E PILOT CYCLED THE LT THRUST REVERSER AND THE LIGHT EXTINGUISHED.  THE TRIP WAS CANCELLED UNTIL THE AIRCRAFT COULD BE IN	SPECTED.  INVESTIGATION REVEALED A WIRE FOR THE DEPLOY SWITCH HAD CHAFED TO GROUND AT THE STRUCTURE OF THE LT THRUST REV	ERSER OB STANG.  THE DAMAGED WIRE WAS REPAIRED AND THE WIRE BUNDLE IN THAT AREA WAS REPOSITIONED TO PREVENT ANY FURTHER 	CHAFING.  OPS CHECK OF THE THRUST REVERSER SYSTEM AFTER REPAIR WAS NORMAL.  (K)	1	L	7	2 	4F	4	F		A22CE   	E25EA				 
	20080728		CE  	2008	7	28	2008FA0000501    	1	20080715	G	5730		SKIN            			BEECH 	300   	300BEECH    	1152930	CE  										WING	DAMAGED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	613BA					FL396				AIRCRAFT WAS BROUGHT IN FOR INSPECTION OF DOUBLE ROW OF RIVETS AT WING STA 209.016.  RIVETS WERE FOUND SMOKING AND PAINT	 WAS POPPED ON THE RIVET HEADS.  USED BOROSCOPE TO INSPECT RIVET BUCKTAILS.  FOUND ALL OF THE RIVETS IN THE DOUBLE ROW O	F THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN.  THESE RIVETS WERE INSTALLED NEW AT THE FACTORY.  AIRCRAFT HAS A TT OF 1	659.1.  RECOMMEND INSPECTING THESE RIVET FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43.13-1	B.  (K)		2	L	7	2 	4T				A24CE   					 
	20080728			2008	7	28	2008FA0000502    	4	20080718	G	2200	6222263016	AMPLIFIER       			ISRAEL	1124  	1124A       	4500103	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					AUTOPILOT	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	818JH					341				AFTER (1) HOUR DISENGAGES AUTOPILOT.  PRELIMINARY INSPECTION RESULTS, NO DEFECTS NOTED AFTER BENCH CHECK.  (K)						2	M	7	2 	4F	4	F		A2SW    	E6WE				 
	20080728		CE  	2008	7	28	2008FA0000503    	1	20080715	G	5730		SKIN            			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					RT WING	DAMAGED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	291B					FL559				AIRCRAFT WAS BROUGHT IN FOR PHASE INSPECTION.  DURING INSPECTION A DOUBLER ROW OF RIVETS AT WING STATION 209.016 WERE FO	UND WITH PAINT POPPING OFF OF THE RIVET HEADS.  USED BOROSCOPE TO INSPECT RIVET BUCKTAILS.  FOUND ALL OF THE RIVETS IN T	HE DOUBLE ROW OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN.  THESE RIVETS WERE INSTALLED NEW AT THE FACTORY.  AIRCRAF	T HAS A TT OF 201.8.  RECOMMEND INSPECTING THESE RIVETS FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS	 IAW AC 43.13-1B.  (K)		2	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20080728		GL  	2008	7	28	2008FA0000505    	3	20080722	G	6197	1219310	CONNECTOR       	WOODWARD    		DIAMON	DA40  	DA40        	2990002	GL  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCC2Y	HCC2YR1     	GL  	PROP GOVERNOR	DAMAGED         	B			WOGR	A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			GL	03	412PJ	300  			00272	40495	L3186051A	CH38785B		ON JUNE 28TH, 2008, DURING CLIMB OUT, PASSING THROUGH 4000 FEET THE ENGINE SUDDENLY WENT INTO AN OVER SPEED CONDITION OF	 OVER 3100 RPM. THE AIRCRAFT REMAINED UNDER CONTROL AND WAS LANDED SAFELY AT AIRPORT AFTER AN EMERGENCY WAS DECLARED.  U	PON DISASSEMBLY OF THE GOVERNOR, IT WAS DISCOVERED THAT THE 1219-310 PLUG HAD BECOME DISLODGED FROM THE GOVERNOR BODY.  	THIS SEPARATION AND THE RESULTANT LOSS OF PROPELLER SERVO PRESSURE ALLOWED THE PROP TO RETRACT TO ITS LOW PITCH POSITION	 AND OVERSPEED THE ENGINE.  A PROBABLE CAUSE WAS LACK OF PROPER TORQUE DURING ASSEMBLY.  APPLICATION OF LOCK-TIGHT TO TH	E PLUG AND INDEPENDENT SECOND PARTY VERIFICATION OF TORQUE DURING ASSEMBLY IS SUGGESTED.  (K)	1	L	7	1 	3O	3	O	NT	A47CE   	E1CE	5	C	P920	 
	20080728		SO  	2008	7	28	2008FA0000506    	1	20080702	G	7714	ACA500	TRANSMITTER     			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					LT ENGINE	MALFUNCTIONED   	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	61WH					1075				TRANSMITTER CAUSED LT ENGINE TO SPOOL BACK TO IDLE, AC RETURNED TO AIRPORT AND LANDED WITH NO INCIDENT.  (K)						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
	20080728		CE  	2008	7	28	2008FA0000507    	1	20080715	G	5730		SKIN            			BEECH 	300   	300BEECH    	1152930	CE  										WING	DAMAGED         	B			KX5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	613BA					FL396				AIRCRAFT WAS BROUGHT IN FOR INSPECTION OF DOUBLER ROW OF RIVETS AT WING STA 209.016.  RIVETS WERE FOUND SMOKING AND PAIN	T WAS POPPED ON THE RIVET HEADS.  USED BOROSCOPE TO INSPECT RIVET BUCKTAILS.  FOUND ALL OF THE RIVETS IN THE DOUBLER ROW	 OF THE SKIN LAP AT WS 209.016 WERE UNDER DRIVEN.  THESE RIVETS WERE INSTALLED NEW AT THE FACTORY.  AC HAS A TT OF 1659.	1.  RECOMMEND INSPECTING THESE RIVETS FOR POPPED PAINT AND SMOKING CONDITION AND INSTALLING NEW RIVETS IAW AC 43..13-1B.	  (K)		2	L	7	2 	4T				A24CE   					 
	20080728		CE  	2008	7	28	2008FA0000508    	1	20080716	G	5210	5043006221	BRACKET         			BEECH 	200   	B200        	1152922	CE  										PAX DOOR LATCH	MISINSTALLED    	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	05	786DD	661  			BB1171	BB1171				PILOT REPORTED DOOR CAME OPEN IN FLIGHT.  UPON LANDING, IT WAS FOUND THE MAIN CABIN DOOR HAD DEPARTED AIRCRAFT.  DOOR WA	S RECOVERED.  DURING INSPECTION AND DISASSEMBLY OF THE DOOR, SEVERAL ISSUES WERE FOUND.  1) UPPER FORWARD LATCH HOOK WAS	 FOUND WITHOUT RIGGING HOLES INSTALLED AND WAS INCORRECTLY RIGGED.  2) DOOR BELLCRANK, PN 50-430031-29 WAS FOUND BENT AN	D TWISTED.   3) MAIN CABIN DOOR LATCH BRAZE ASSEMBLY WAS CATCHING ON HOOK.  DID NOT ALLOW FOR A SMOOTH TRANSITION TO A L	OCKED POSITION.  (K)		1	L	7	2 	4T				A24CE   					 
	20080805		SO  	2008	8	5	2008FA0000509    	1	20080722	G	3250	9539500	ARM             			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					NLG STEERING	WORN            	B			BIER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	2190K	4792 				347970096				NLG MOUNT ASSY ATTACHMENT POINT FOR STEERING ARM ASSY HAS EXCESSIVE WEAR AT LWR MOUNT HOLE, SRM DOES NOT SPECIFY AT FIX 	OR ALLOWABLE LIMIT FOR PN 95551-23.  DISCREPANCY FOUND DURING INSP IAW SB 1123A & B AND ANNUAL INSPECTION IAW SRM INSPEC	TION GUIDE.  SB 1123B GIVES THE SERVICE LIMITS TO THE STEERING ARM CENTER PIVOT BUSHINGS AND CENTER PIVOT SLEEVE.  HOWEV	ER THE MORE CRITICAL COMPONENT, THE NLG MOUNT ASSY IS NOT ADDRESSED FOR THE SERVICE LIMIT OF THE STEERING ARM MOUNTING T	ABS.  MFG SHOULD INCORPORATE SERVICE LIMIT DATA THAT COVERS THE NLG MOUNT ASSY AND REPAIR DATA.  (K)		1	L	7	2 	3O	3	O		A7SO    	E9CE				 
	20080811		EU  	2008	8	11	2008FA0000511    	1	20080719	G	2435	105SG1220	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	FAILED          	B			HDNR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	03	350BH					2813	9345			WHILE ACFT WAS CIRCLING AT A SCENE CALL, THE CREW WAS STARTING TO DETECT WHAT SEEMED TO BE BURNING PLASTIC FOLLOWED BY A	 GENERATOR CAUTION LIGHT.  AC LANDED BACK AT HOSPITAL PAD WITHOUT INCIDENT. MAINT WAS DISPATCHED. IT WAS FOUND THAT THE 	STARTER GENERATOR HAD FAILED AND THE PLASTIC FAN BLADES WERE DEFORMED RESULTING IN THE PLASTIC BURNING ODOR.  THE STARTE	R GENERATOR WAS REPLACED AND AN OPERATIONAL CHECK OF THE SYSTEM WAS SATISFACTORY.  (K)			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20080811		CE  	2008	8	11	2008FA0000512    	1	20080702	G	2760	12SX1T	SWITCH          			RAYTHN	390   	390         	7150030	CE  										SPOILERS	FAILED          	B			E81R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	972PF	1146 				RB38				PILOT REPORTED SPOILER FAIL INDICATION IN CRUISE FLIGHT.  ALL SPOILER PANELS DEPLOYED UPON LANDING.  SCU FAULT CODE 44R4	RV3V INDICATED.  ADJUSTED LT & RT SPOILER FINAL POSITION LVDT`S AS REQUIRED IAW MM 27-60-00-501.  REPLACED LT THROTTLE S	WITCH S1, SPOILER SYS FUNCTIONAL CHECKS NORMAL, NO FAULTS INDICATED SUSPECT LT THROTTLE S1 SWITCH TO HAVE PREMATURE INTE	RNAL FAULT.  RECOMMEND MFG INVESTIGATE IF FLEET IS EXPERIENCING PREMATURE FAILURES OF THROTTLE SWITCHES AND REDESIGN SWI	TCH IF REQUIRED.  (K)		1	L	7	2 	3F			RT	A00010WI					 
	20080811		NM  	2008	8	11	2008FA0000513    	1	20080730	G	5753		SPAR            			BOEING	737   	737448      	13844BU	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LT TE FLAP	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
	20080811		NM  	2008	8	11	2008FA0000514    	1	20080730	G	5753		SPAR            			BOEING	737   	737448      	13844BU	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LT WING TE FLAP	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				DURING SCHEDULED INSP, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
	20080811		WP  	2008	8	11	2008FA0000515    	1	20080729	G	5530		INLET           			DOUG  	DC9   	DC982       	3022082	WP  	PWA   	JT8   	JT8D*       	 	NE  					HEAT EXCHANGER	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	886GA					49931				DURING SCHEDULED INSP, FOUND VERTICAL STABILIZER L/E AT HEAT EXCHANGER INLET IS CRACKED APPROX 6.5 INCHES LONG ON LT SID	E.  FOUND TO BE OUT OF LIMITS IAW SRM 55-05 FIG 3. (K)					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
	20080811		EA  	2008	8	11	2008FA0000516    	2	20080721	G	8550	CH481101	OIL FILTER      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					ENGINE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4900H	1    				15284009				FILTER INSTALLED AND OIL CHANGE RUN-UP NORMAL.  FIRST FLIGHT AFTER OIL CHANGE, PILOT NOTICED OIL PRESSURE DROPPING AND H	IGH OIL TEMP, UNABLE TO CORRECT, PILOT RETURNED TO ORIGIN AND REPORTED FINDINGS.  INVESTIGATION FOUND FILTER ELEMENT DEB	RIS UNDER PRESSURE RELIEF VALVE CAUSING LOW OIL PRESSURE, UPON FURTHER INVESTIGATION A SECOND FILTER OF SAME DATE CODE W	AS FOUND TO HAVE LOOSE DEBRIS IN THE FILTERED SIDE OF THE FILTER ELEMENT AND THE ELEMENT WAS BONDED ON ONE END ONLY.  TH	E ENGINE GULLIES WERE FLUSHED WITH AIR AND SEVERAL PIECES OF DEBRIS WERE FOUND, A NOW FILTER OF DIFFERENT DATE CODE WAS 	INSTALLED, SEVERAL GROUND RUNS WERE MADE, NO SIGNIFICANT DEBRIS WAS FOUND.  A NEW FILTER OF A DIFFERENT MFG WAS INSTALLE	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
	20080811		EU  	2008	8	11	2008FA0000517    	1	20080801	G	3210	DIN4718ZP	FITTING         			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12501    	59300	EU  					MLG	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	119BJ					42AC045				CIRCLIP THAT SECURES DOWNLOCK PIN IN MLG LEGS HAS BEEN TWISTING OFF RENDERING THIS DOWNLOCK PIN LOOSE ENOUGH TO FALL OUT	 WHEN GEAR IS RETRACTED, THIS PARTICULAR AC HAD THE AFT SECTION OF THE WHEELWELL DAMAGED DUE TO THE PIN HANGING HALF WAY	 OUT AND CONTACT THROUGH THE LAMINATE.  THIS PIN SHOULD BE SECURED WITH SOMETHING THAT IS PERMANENT LIKE A COTTER PIN OR	 SAFETY WIRE.  THIS PROBLEM WAS DISCOVERED ON A PILOTS PRE-FLIGHT.  (K)			1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
	20080811		SO  	2008	8	11	2008FA0000518    	2	20080717	G	8520	654837	CAMSHAFT        								CONT  	O550  	IO550B      	 	SO  					ENGINE	WORN            	B			Y2GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23		2079 					296655			CAMSHAFT LOBES WORN EXCESSIVELY FORM CORROSION PITS.  (K)											3	O			E3SO				 
	20080811		EA  	2008	8	11	2008FA0000519    	2	20080717	G	8520	LW19173	CAMSHAFT        								LYC   	O540  	IO540*      	41532	EA  					ENGINE	WORN            	B			Y2GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23		1329 					L100268A			CAMSHAFT LOBES WORN FROM CORROSION PITS.  (K)											3	O			1E4				 
	20080811		EA  	2008	8	11	2008FA0000520    	1	20080624	G	2730	C6CTM102827	JACKSCREW       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6*        	52043	EA  					LT ELEVATOR	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	300DZ					644				FOUND SCREW-DRIVE INTERNAL THREADS STRIPPED AND SAFETY SPLIT, PIN MISSING.  PILOT HAD DIFFICULTY CONTROLLING ELEVATOR.  	PART HAD 196.2 IN SERVICE, SINCE REPAIR.  RECOMMENDED TO INSPECT LT ELEVATOR TRIM TAB FOR EXCESSIVE PLAY IAW MM AS PART 	OF PREFLIGHT AND EVERY SCHEDULED INSP.  (K)				1	H	7	2 	3T	3	T	RT	A9EA    	E2NE				 
	20080811		CE  	2008	8	11	2008FA0000521    	1	20080723	G	7120	10191012253	MOUNT           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6*        	52043	EA  					LT ENGINE	CRACKED         	B			GSPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	73WC	6814 				FL135				DURING A PHASE 2, 200 HR INSP, A CRACK WAS FOUND ON THE LT ENGINE MOUNT UPPER IB COWLING BRACKET.  THE CRACK EXTENDED FR	OM THE TOP OF THE WELD AND WAS APPROXIMATELY 1 INCH IN LENGTH.  THE ADJACENT AREAS DID NOT APPEAR DAMAGED..  TECH SUPPOR	T WAS CONTACTED AND THE MOUNT SENT TO A QUALIFIED WELDER FOR REPAIR.  CAUSE OF CRACK IS UNKNOWN.  (K)				2	L	7	2 	4T	3	T		A24CE   	E2NE				 
	20080811		SO  	2008	8	11	2008FA0000522    	1	20080731	G	2530	50231L0V5280	PAN             			GULSTM	G1159 	GIV         	3980115	SO  	PWC   	PW615 	PW615FA     	52282	NE  					OVEN	MISINSTALLED    	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	13	416QS					1316				CABIN SMOKE DUE TO DRIP PAN IN OVEN BEING IMPROPERLY INSTALLED CAUSING DRIPPINGS FROM FOOD TO CONTACT OVEN LOWER BURNER 	ELEMENTS.  (K)					2	L	7	2 	4F	4	F	RT	A12EA   	E00073EN				 
	20080811		SO  	2008	8	11	2008FA0000523    	1	20080707	G	8120	LW18302	MOUNT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					TURBOCHARGER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	3580X					318052085	L628661A			FOUND MOUNT FOR TURBOCHARGER TO BE BROKEN COMPLETELY THROUGH ON IB LOWER TUBE ON RT ENGINE.  CRACK WAS APPROXIMATELY 4 T	O 5 INCHES FROM FWD LOWER ATTACH POINT.  NO REPORTED VIBRATION ISSUES OF OPERATIONAL ISSUES.  (K)					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20080811			2008	8	11	2008FA0000524    	4	20080802	G	2300	G888012	CONTROL HEAD    			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TPE331	TPE3313     	01514	WP  					NR 1 NAV/COMM	FAILED          	D				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		DE	DESCENT        	1			SO	14	980S					249	P75665			AS CREW REPORTED DURING DESCENT THREW 16000 FT 1.40 HR INTO FLIGHT EXPERIENCED A SUDDEN ELECTRICAL BURNING ODOR THAT WAS	 ACCOMPANIED BY SMALL PLUME OF SMOKE.  COMPLETED ALL MEMORY ITEMS ON THE CHECKLIST AND DECLARED EMERGENCY FOR PRIORITY L	ANDING.  SHORTLY THEREAFTER WHILE DESCENDING TO 6000 FT THE SMOKE AND ELECTRICAL ODOR CLEARED AND NOTED NR 1 NAV/COM CON	TROL NO LONGER WORKING AND PULLED CIRCUIT BREAKER.  AT THAT TIME EMERGENCY WAS OVER AND REQUESTED NORMAL HANDLING TO THE	 AIRPORT.  UPON FURTHER INSPECTION BY TECH, THE NR 1 NAV/COM CONTROL HEAD HAD FAILED CAUSING THE PROBLEM.  REPLACEMENT P	ART INSTALLED.  REMOVED UNIT PN G8060-12, SN 273 SENT FOR EVALUATION AND REPAIR.  (K)	2	L	7	3 	4F	4	T		A46EU   	E4WE				 
	20080811		EA  	2008	8	11	2008FA0000525    	2	20080722	G	7414	AB382584	CONTACTOR       	BENDIX      		BLANCA	17    	1731ATC     	1220437	GL  	LYC   	O540  	TIO540*     	41532	EA  					MAGNETO	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	222SN					31004				A BROKEN CONTACT BREAKER WAS FOUND DURING TROUBLESHOOTING AN IGNITION PROBLEM.  THE CONTACTOR RIVET WAS BROKEN ON THE MA	GNETO.  THE CONTACTOR RIVET MAY BE INSUFFICIENT TO PROPERLY HOLD THE CONTACTOR IN PLACE.  (K)					1	L	7	1 	3O	3	O		A18CE   	E14EA				 
	20080811		SO  	2008	8	11	2008FA0000526    	2	20080619	G	7414	K3823	DISTRIBUTOR     			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					MAGNETO	WORN            	B			AKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	16MS	182  				18267267				REMOVED NEW MAGNETOS PN 6310, SN 07061208 & 07061310..  ACCOMPLISHED SB 3-08 PREMATURE CARBON BRUSH WEAR.  BOTH CARBON B	RUSHES HAD PREMATURE WEAR AS DEPICTED IN THE CENTER ILLUSTRATION FIG 1, PAGE 3 OF 5. (K)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
	20080811		SO  	2008	8	11	2008FA0000527    	2	20080619	G	7414	M1827	CAM             			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					MAGNETO	WORN            	B			AKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	16MS	182  			07061208	18267267				REMOVED NEW MAGNETOS PN 6310, SN 07061308 & 07061310.  ACCOMPLISHED SB 2-08, MAGNETO  CONTACT POINT CAMP PREMATURE WEAR.	   INSTALLED 2 NEW CONTACT POINT ASSEMBLIES PN M3081; SET "E" GAP AND TIMED TO THE ENGINE.  (K)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
	20080811		CE  	2008	8	11	2008FA0000528    	1	20080729	G	3222		STRUT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					NLG	DAMAGED         	B			QFBR	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			NM	01	6448V					172RG0709				PILOT REPORTED A CLUNKING NOISE COMING FROM THE NLG.  UPON INSPECTION, IT WAS NOTED THAT .2500 INCH UP AND DOWN PLAY AT 	THE LOWER TRUNNION ASSY.  THE AC`S NLG ASSY WAS REMOVED AND DURING FATHER INSPECTION THE BARREL WAS FOUND TO BE THE CULP	RIT.  THE BOLT THAT HOLDS THE HEAD AND TUBE ASSY SHOCK STRUT PN 2443005-1 AND COLLAR ASSY TO THE BARREL HAD SHIFTED AT .	2500 INCH TO THE BARREL BOLT HOLE ELONGATED AND DISPLACING METAL ABOVE THE BOLT HOLE.  THE AC IS USED FOR FLIGHT TRAININ	G, WAS IS SUSPECT PLAYS SOME ROLE BUT BELIEVE THE PROBLEMS HAD BEEN DETECTED BEFORE AND ONLY THE BOLT WAS REPLACED.  (K)		1	H	7	1 	3O	3	O		3A17    	E286				 
	20080811		EA  	2008	8	11	2008FA0000529    	2	20080730	G	8530	74230	GUIDE           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					CYLINDER HEAD	SEIZED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	543ER	889  				172S10522	L3342451E			DURING FLIGHT, THE ENGINE STARTED RUNNING ROUGH AND LOST POWER.  EMERGENCY LANDING COMPLETED WITHOUT DAMAGE OR INJURY.  	MAINT FOUND THE NR 3 EXHAUST VALVE SEIZED IN THE VALVE GUIDE.  FURTHER INVESTIGATION FOUND THE GUIDE BROKEN IN THE CYLIN	DER HEAD.  OPERATOR HAS AIRCRAFT WITH THE NEW ROLLER TAPPET ENGINES.  HAVE BEEN PERFORMING A SB388C INSPECTION ON THE RE	ST OF THE FLEET AND HAVE FOUND THE MAJORITY OF THE EXHAUST VALVES FOR ALL CYLINDERS TO BE TIGHT IN THE GUIDES.  MFG RECO	MMENDS A 1000 HOUR INTERVAL FOR THESE ENGINES FOR SB388C INSPECTION.  WILL BE INITIATING A 600 HOUR INTERVAL FOR THE SB3	88C FOR OUR FLEET.  HAVE REVISED LEANING PROCEDURES.  (K)	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080811		SO  	2008	8	11	2008FA0000530    	1	20080714	G	2420	365662R	STATOR          			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  	HARTZL	HCC3Y	HCC3YR      	GL  	ALTERNATOR	SHORTED         	C				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	11	2125V					32R7780431	L1664445A	DY4143A		THE AC SUFFERED LOSS OF ELECTRICAL POWER WHILE IN CONTACT WITH ATC WHEN LOST  RADIO CONTACT.  CONTACTED BKP VIA CELL PHO	NE AND STATED HIS PROBLEM AND REQUESTED RUNWAY LIGHT AND WHEN THEY WERE TURNED ON HE WAS WITHIN SIGHT OF THE RUNWAY AND 	USED EMERGENCY RELEASE OF THE LANDING GEAR AT 120 KNOTS.  AS AC TOUCHED DOWN THE NOSE GEAR COLLAPSED CAUSING THE AC TO S	KID OFF RUNWAY.  DAMAGE WAS CONFINED TO THE PROP, MLG DOORS AND RT WING L/E, WING TIP.  NO FLIGHT PLAN HAD BEEN FILED AN	D VFR CONDITIONS PREVAILED.  NO INJURIES.  TESTED ALTERNATOR FOUND STATOR HAD SHORTED OUT, IN TURN HAD SHORTED OUT RECTI	FIER.  (K)	1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P25EA	 
	20080811		EA  	2008	8	11	2008FA0000531    	2	20080728	G	7314		SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2B  	41979	EA  					NR 2 ENG	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	05	3589X				E2048	318052138	L244768A			FUEL PUMP DRIVE SHAFT SEAL FAILED RESULTING IN LARGE FUEL LEAK AT DRAIN.  (K)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20080811		GL  	2008	8	11	2008FA0000532    	1	20080801	G	2450		BUSS BAR        			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					CB PANEL	LOOSE           	B			YEBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	839CT					2938				PILOT REPORTED THE NR 2 ALTERNATOR WAS INTERMITTENT.  WHILE TROUBLESHOOTING THE NR 2 ALTERNATOR, FOUND 13 SCREWS LOOSE A	ND 1 SCREW MISSING ON THE COPPER CIRCUIT BREAKER BUSS BAR.  THE 1 SCREW MISSING WAS ON THE NR 2 ALTERNATOR CIRCUIT BREAK	ER BUSS FEED.  PROBABLE CAUSE FOR THIS WOULD BE THAT THEY WERE NOT TIGHT FROM FACTORY.  RECOMMEND CHECKING TORQUE OF ALL	 CIRCUIT BREAKER SCREWS AT NEXT MAINTENANCE ACTION.  (K)			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
	20080811		CE  	2008	8	11	2008FA0000533    	1	20080714	G	7160	45A35042003	SKIN            			BEECH 	MU300 	400A        	1155402	CE  										RT ENGINE INLET	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	470LX	1491 				RK478				REPORTED RT ENG INLET CRACKED AT 9:00 POSITION.  THE INLET WAS REMOVED AND REPAIRED AND REINSTALLED ON THE AC.  (K)						2	H	7	2 	4F			RT	A16SW   					 
	20080808		SO  	2008	8	8	2008FA0000534    	1	20080712	G	2820	1500106151	LINE            			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6*        	52043	EA  					FUEL SYSTEM	CHAFED          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	07	5339G					4697095				FOUND FUEL LINE, PN 1500106-151, CHAFED AGAINST THROTTLE CABLES , PROP CONTROL CABLES  BELOW THROTTLE. THIS LINE PROVIDE	S FUEL PRESSURE TO THE 2 MANUAL ENGINE PRIMER PUMPS AT THE BASE OF THE QUADRANT.  HAD THIS LINE CHAFED THROUGH, FUEL UND	ER PRESSURE WOULD HAVE FLOWED INTO THE AIRPLANE CABIN.  THE ONLY WAY TO SHUT OFF FUEL FLOW TO THIS LINE WOULD BE TO CLOS	E THE FRONT ENGINE FUEL SELECTOR VALVE, AND SHUT DOWN THE FRONT ENGINE.  THIS IS A POTENTIAL HAZARDOUS CONDITION AND COU	LD CAUSE AN INFLIGHT CABIN FIRE WITH RESULTANT LOSS OF LIFE AND AIRCRAFT IF NOT FOUND AND CORRECTED.  (K)		1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
	20080811		SW  	2008	8	11	2008FA0000535    	1	20080730	G	3234	5040560006	DOWNLOCK        			MOONEY	M20   	M20B        	5870206	SW  	LYC   	O360  	O360A1A     	41514	EA  	MCAULY	2A36C	D2A36C*     	GL  	CONTROL LEVER	WORN            	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	74542	3371 				1853	L402336	58618		LANDING GEAR LEVER BECAME DISENGAGED FROM THE DOWN LOCK LATCHING ASSY ON THE PILOT`S LOWER CENTER INSTRUMENT PANEL. AC W	AS ON THE GROUND DURING LANDING ROLLOUT.  THIS ALLOWED GEAR TO COLLAPSE.  SB M20-88B, 5/10/94.  (K)					1	L	7	1 	3O	3	O		2A3     	E286	5	C	P880	 
	20080811		EA  	2008	8	11	2008FA0000537    	1	20080724	G	5730		SKIN            			CNDAIR	CL600 	CL6001A11   	1900308	EA  										WING	CORRODED        	B			ZLJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	100QR					1043				SURFACE CORROSION (PITTING) DISCOVERED ON BOTH WINGS LOWER SURFACES ADJACENT TO AND OB OF WHEEL WELLS, CORROSION DEEMED 	UNUSUALLY SEVERE.  (K)					2	L	7	2 	4F			RT	A21EA   					 
	20080811		NM  	2008	8	11	2008FA0000538    	1	20080730	G	5753		SPAR            			BOEING	737   	737448      	13844BU	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LT WING TE FLAP	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	742VA					24773				DURING SCHEDULED INSP, FOUND CORROSION ON LT IB MID FLAP, MID SPAR UPPER CHORD.  (K)						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
	20080811		CE  	2008	8	11	2008FA0000539    	1	20080502	G	3244	15117300	WHEEL           			BEECH 	200   	B200        	1152922	CE  										MLG	CRACKED         	B			E5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	200ND	2738 				BB1612				CRACK INDICATIONS LOCATED IN BEED AREA OF WHEELS REAVEALED BY FLUORESCENT PENETRANT.  (K)						1	L	7	2 	4T				A24CE   					 
	20080903		CE  	2008	9	3	2008FA0000540    	1	20080502	G	3246	4088	WHEEL           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLG	CRACKED         	B			HJ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	200ND					BB1612				CRACK INDICATIONS LOCATED IN BEAD AREA OF WHEELS, REVEALED BY FLUORESCENT PENETRANT.  (K)						1	L	7	2 	4T	3	T		A24CE   	E2NE				 
	20080903		WP  	2008	9	3	2008FA0000541    	2	20080801	G	7250	30753507	MODULE          			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					LPT	FAILED          	B				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	03	225PB	3495 				258558	107662			AIRCRAFT EXPERIENCED A VIBRATION IN FLIGHT.  CREW SHUTDOWN NR 1 ENGINE AND LANDED.  MAINT CREWS DETERMINED THE THIRD STA	GE LOW PRESSURE TURBINE (LPT) MODULE HAD EXPERIENCED A BLADE FAILURE. ONE BLADE WAS MISSING A PIECE ABOUT ONE INCH LONG.	 MAINT ALSO DISCOVERED A CRACK IN THE THIRD STAGE STATOR WHICH EXTENDED BETWEEN ONE THIRD TO ONE HALF THE CIRCUMFERENCE 	OF THE HOUSING. NO OTHER ANOMALIES WERE NOTED DURING THE DISASSEMBLY OF THE ENGINE. PARTS WERE SENT TO MFG FOR INVESTIGA	TION AND REPAIR. (K)		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
	20080903		SW  	2008	9	3	2008FA0000542    	1	20080728	G	6220	471201281	BEAM            			BELL  	47    	47G         	1181002	SW  										MAIN ROTOR	CRACKED         	B			E5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21										BEAM CRACK INDICATION AT EAR END (FPT). HUB - CRACK INDICATIONS AT RADIUS ON STUB ENDS (FMT). (K)						1	G	7	1 	3O				H1      					 
	20080903		SW  	2008	9	3	2008FA0000543    	1	20080728	G	6220	471201171	HUB             			BELL  	47    	47G         	1181002	SW  										MAIN ROTOR	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21										BEAM - CRACK INDICATION AT EAR END (FPT).  HUB - CRACK INDICATIONS AT RADIUS ON STUB ENDS.  (K)						1	G	7	1 	3O				H1      					 
	20080903		EU  	2008	9	3	2008FA0000544    	1	20080730	G	2421	ALU8521	ALTERNATOR      			SOCATA	TB9   	TB9         	8680694	EU  	LYC   	O320  	O320D2A     	41508	EA  					ENGINE	FAILED          	B			NI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03		1    								ALTERNATOR WILL FAIL ABOVE 2500 RPM, LOW VOLTAGE LIGHT COMES ON AND THE VOLTMETER INDICATES BATTERY VOLTAGE. OPS CHECK D	URING GROUND RUNS ARE NORMAL MAX RPM DURING GROUND RUN 2400 RPM. ALTERNATOR APPEARS TO BE RPM SENSITIVE.  POSSIBLE CAUSE	: BRUSHES NOT RIDING TRUE ON SLIP RING. OVERHAUL PROCESS MAY CONTRIBUTE TO PROBLEM. AN ADDITIONAN (2) ALU8521 ALTERNATOR	S FROM INVENTORY PRODUCE THE SAME SYMPTOMS, SN E113128 AND F043304. BOTH ALTERNATORS FAILED WITHIN 2 HOURS OF OPERATION.	  BOTH WERE O/H UNITS.  (K)		1	L	7	1 	3O	3	O	NT	AS1EU   	E274				 
	20080903		CE  	2008	9	3	2008FA0000545    	1	20080712	G	3610	65550384	BELLOWS         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  						RUPTURED        	B			QFYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	63	17PL					5600412	PCEJC0312			THE BELLOWS INSIDE THE BRADED CONNECTION CRACKED OUT LEAVING A HOLE ABOUT .75 IN IN DIA AT THE UP STREAM SIDE OF THE FLE	XIBLE CONNECTOR.  THE PROBLEM WAS DISCOVERED ON A MAINT RUN UP AT WHICH TIME THE FIRE DETECTION SYS WAS ACTIVATED FROM A	N OVERHEAT SITUATION.  RECOMMEND REMOVING THE ELBOWS AND CHECKING THE BELLOWS FOR CRACKS WITH A BORESCOPE.  (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
	20080903		CE  	2008	9	3	2008FA0000546    	1	20080717	G	2750	98600581	CONTROL CABLE   			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					TE FLAPS	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	2423S					21061275				ORDERED NEW FLAP FOLLOW UP CABLE; TO REPLACED ORIGINAL CABLE WHICH HAD BECOME DEFECTIVE DUE TO NORMAL USAGE AND AGE.						1	H	7	1 	3O	3	O		3A21    	E8CE				 
	20080903		SW  	2008	9	3	2008FA0000547    	1	20080628	G	3260	560006	DOWNLOCK        			MOONEY	M20   	M20B        	5870206	SW  	LYC   	O360  	O360A1A     	41514	EA  					MLG	WORN            	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	19	74542	3371 				1853	L402336			LANDING GEAR LEVER BECAME DISENGAGED FROM THE DOWNLOCK LATCHING ASSY ON THE PILOT`S LOWER CENTER INSTRUMENT PANEL. AC WA	S ON THE GROUND DURING LANDING ROLLOUT.  THIS ALLOWED GEAR TO COLLAPSE, SB M20-88B, 5-10-94.  (K)					1	L	7	1 	3O	3	O		2A3     	E286				 
	20080903		SO  	2008	9	3	2008FA0000548    	1	20080804	G	5330	69904000	SKIN            			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUSELAGE	CRACKED         	B			L6QR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	121TF	1520 				3257351				UPPER COMM/NAV ANTENNA DOUBLER AND SKIN CRACKED FROM FWD SEAM ALONG BOTH ANTENNA MOUNT NUTPLATE LINES. CRACKS ARE APPROX	 6 INCHES LONG WITH ADDITIONAL CRACKING RADIATING OUT FROM FWD NUTPLATES TO FWD DOUBLER MOUNTING RIVETS. ANTENNA DOUBLER	 IS CRACKED COMPLETELY THROUGH ON LT SIDE AND 90 PERCENT THROUGH ON RT SIDE. DAMAGE PICTURE AVAILABLE UPON REQUEST.  DAM	AGE APPEARS TO HAVE BEEN CAUSED BY PROLONGED OIL CANNING OF THE UPPER SKIN PANEL FROM AERODYNAMIC LOADS AGAINST THE ANTE	NNA DURING FLIGHT.  TO PREVENT REOCCURRENCE REPAIR WITH FLUSH PATCH IAW 43.13-1B, SEC 4, HOWEVER BEND .5 INCH LIP ON LT,	 RT AND AFT EDGES OF BACKING PATCH TO INCREASE STIFFNESS AND REDUCE OIL CANNING EFFECT. JOG FRONT EDGE OF BACKING PATCH 	1	L	7	1 	3O	3	O		A3SO    	E14EA				 
	20080903		SO  	2008	9	3	2008FA0000549    	1	20080804	G	5330	99813004	DOUBLER         			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUSELAGE	CRACKED         	B			L6QR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	121TF	1520 				3257351				UPPER COMM/NAV ANTENNA DOUBLER AND SKIN CRACKED FROM FWD SEAM ALONG BOTH ANTENNA MOUNT NUTPLATE LINES. CRACKS ARE APPROX	 6 INCHES LONG WITH ADDITIONAL CRACKING RADIATING OUT FROM FWD NUTPLATES TO FWD DOUBLER MOUNTING RIVETS. ANTENNA DOUBLER	 IS CRACKED COMPLETELY THROUGH ON LT SIDE AND 90 PERCENT THROUGH ON RT SIDE. DAMAGE PICTURE AVAILABLE UPON REQUEST.  DAM	AGE APPEARS TO HAVE BEEN CAUSED BY PROLONGED OIL CANNING OF THE UPPER SKIN PANEL FROM AERODYNAMIC LOADS AGAINST THE ANTE	NNA DURING FLIGHT.  TO PREVENT REOCCURRENCE REPAIR WITH FLUSH PATCH IAW 43.13-1B, SEC 4, HOWEVER BEND .5 INCH LIP ON LT,	 RT AND AFT EDGES OF BACKING PATCH TO INCREASE STIFFNESS AND REDUCE OIL CANNING EFFECT. JOG FRONT EDGE OF BACKING PATCH 	1	L	7	1 	3O	3	O		A3SO    	E14EA				 
	20080903		EA  	2008	9	3	2008FA0000550    	1	20080729	G	6300	269D53085	DRIVE SHAFT     			SCWZER	269   	269D        	8059501	EA  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	277DT	674  				0028	CAE845057			DURING PREFLIGHT, THE M/R DROOP STOP NUT WAS FOUND TO BE LOOSE. UPON FURTHER INSP IT WAS DETERMINED THAT M/R HUB SHOULD 	BE REMOVED TO LOOK FOR SIGNS OF WEAR. ONCE HUB WAS REMOVED AND INSPECTED, MODERATE WEAR (FRETTING) WAS FOUND ON DROOP ST	OP RETAINER PLATE (PN 269A1320), DROOP STOP RETAINER RING (PN 269D1329), DROOP STOP RETAINER (PN 269A1332) AND UPPER SCI	SSORS SUPPORT (PN 269A1328-901) TO THRUST BEARING TUBE SPACER ASSY (PN 269A13183). ONCE THESE PARTS WERE REMOVED, THE DR	IVE SHAFT WAS REMOVED FOR INSP. ONCE DRIVE SHAFT WAS REMOVED THE DRIVE SHAFT THRUST BRG WAS REMOVED FOR INSP AND CORROSI	ON WAS FOUND ON DRIVE SHAFT THRUST BRG JOURNAL. CORROSION WAS REMOVED AND FURTHER VISUAL EXAMINATION REVEALED A POSSIBLE	1	G	7	1 	3U	3	U	0	4H12    	E4CE				 
	20080903			2008	9	3	2008FA0000551    	2	20080806	G	7261		BEARING         			DOUG  	MD90  	MD9030      	3023690	NM  										OIL PUMP	SEIZED          	B			HZ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										PUMP SEIZED, OIL PUMP BEARING BRACKET SHOWED SIGNS OF RUBBING WITH THE OIL PUMP GEAR.  PENDING ENGINEERING EVALUATION.  	(K)					2	L	7	2 	4F			RT	A6WE    					 
	20080903		CE  	2008	9	3	2008FA0000552    	1	20080521	G	2910	SA7670024001	LINE            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										HYD SYSTEM	RUPTURED        	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	23	484JC					258644				HYDR FLEXABLE LINE TO RT MLG DOOR ACTUATOR RUPTURED DURING FLIGHT.  LOSS OF FLUID CAVITATED RT AND LT ENGINE DRIVE HYDR 	PUMPS. LINE RUPTURED IN  SIDEWALL NEAR SWAGED END FITTING FOR CONNECTOR.  PRESSURE IS 3000 PSI CONSTANT.  NO LANDING GEA	R ACTUATION WAS IN PROCESS. SUSPECT MFG DEFECT. AC MFG NOTIFIED.  THIS IS FIRST INSTANCE OF THIS FOR THS AC.  LT MLG DOO	R HYDR LINE RUPTURED 2 MONTHS BEFORE IN THE SAME EXACT WAY AND CAUSED THE SAME DAMAGE.  MFG NOTIFIED AGAIN.			2	L	7	2 	4F			RT	A3EU    					 
	20080903		CE  	2008	9	3	2008FA0000553    	1	20080808	G	2910	SA7670024001	LINE            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										HYD SYSTEM	RUPTURED        	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	23	484JC	2369 				258644				HYDR FLEXIBLE LINE TO THE LT LANDING GEAR DOOR ACTUATOR RUPTURED DURING FLIGHT.  LOSS OF FLUID CAVITATED LT AND RT ENG D	RIVEN HYDR PUMPS.  LINE RUPTURED IN SIDEWALL NEAR SWAGED END FITTING FOR CONNECTOR.  PRESSURE IS 3000 PSI CONSTANT.  NO 	LANDING GEAR ACTUATION WAS IN PROCESS.  SUSPECT MFG DEFECT.  AC MFG NOTIFIED.  THIS IS SECOND OCCURRANCE FOR THIS AC.  S	AME LINE RUPTURED 2 MONTH PREVIOUSLY ON RT SIDE ACTURATOR CAUSING SAME DAMAGE.  MFG AGAIN NOTIFIED. (K)			2	L	7	2 	4F			RT	A3EU    					 
	20080902		CE  	2008	9	2	2008FA0000554    	1	20080813	G	7160	125083029	INTAKE DUCT     			CESSNA	206   	TU206G      	2073357	CE  										INDUCTION BOX	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	602MB	10   				U20604052				MANUFACTURER SUPPLIED ENG INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS.  THIS PARTICUL	AR ACFT AND ANOTHER IDENTICAL MODEL ACFT THIS FACILITY MAINTAINS HAVE BEEN CONVERTED TO AN IO-550-F ENG.  AFTER THE STC 	CONVERSION, THE CRACKING PROBLEM HAS INCREASED SIGNIFICANTLY.  CONTACTED THE STC HOLDER AND HAVE RESPONDED WITH A SCHEME	 TO REINFORCE THIS DUCT.  THIS REPAIR STATION IS LOOKING INTO THIS ALTERATION TO THIS DUCT WHICH MAY REQUIRE PER SUPPORT	.  AT PRESENT, THE DUCTS ARE REQUIRING REPAIRS OR REPLACEMENT EVERY 50 HOURS.  A PMA REPLACEMENT DUCT MADE FROM COMPOSIT	E MATERIAL IS NO LONGER AVAILABLE.  (S)	1	H	7	1 	3O				A4CE    					 
	20080825		EA  	2008	8	25	2008FA0000555    	1	20080804	G	3260		INDICATION SYS  			CNDAIR	CL600 	CL6002B16   	1900305	EA  										MLG	MALFUNCTIONED   	C				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			SW	99	190MP					5161				ON APPROACH TO KSSI, WHEN LANDING GEAR DEPLOYED, ONLY RECEIVED NOSE DOWN INDICATION, NO MAIN GEAR DOWN INDICATION.  CYCL	ED SEVERAL TIMES.  CREW DIVERTED TO KAGS AND USED EMERGENCY PROCEDURE TO LOWER GEAR.  ALL GEAR DOWN AND LOCKED FOR LANDI	NG.  MAINTENANCE WAS UNABLE TO DUPLICATE.  CHECKED ADJUSTMENTS OF MAIN LANDING GEAR PROXIMITY SWITCHES, VISUALLY INSPECT	ED DOWNLOCK WIRING HARNESSES AND ACCOMPLISHED MAIN LANDING GEAR RETRACTION AND EXTENSION SEVERAL TIMES AND PERFORMED AN 	EMERGENCY EXTENSION.  NO DEFECTS NOTED.  REPLACED 4 NEW DOWNLOCK INDICATOR BULBS (PRECAUTIONARY).  A MAINTENANCE CHECK F	LIGHT WAS ACCOMPLISHED AFTER MAINTENANCE WITH ALL OPERATIONS NORMAL.  THERE IS NO HISTORY OF THIS DISCREPANCY ON THIS AC	2	L	7	2 	4F			RT	A21EA   					 
	20080902		CE  	2008	9	2	2008FA0000556    	1	20080702	G	2931	1240583000	TRANSDUCER      			LEAR  	60    	60LEAR      	5170707	CE  										HYD PRESSURE	MALFUNCTIONED   	C				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SW	99	262FX	633  				323				HYDRAULIC PRESSURE GAUGE READ ZERO ON LANDING CHECK.  FLAPS AND LANDING GEAR EXTENDED NORMALLY.  GAUGE WAS SEEN TO FLUCT	UATE BETWEEN NORMAL TO 1000 PSI TO ZERO PSI ON APPROACH.  BRAKES AND THRUST REVERSERS OPERATED NORMALLY.  GAUGE READS ZE	RO DURING TAXI.  CREW DECLARED AN IFE AS A PRECAUTION.  MAINTENANCE REPLACED THE HYDRAULIC PRESSURE TRANSDUCER.  OPS CHE	CK AND LEAK CHECK PERFORMED SATISFACTORILY.  (S)			2	L	7	2 	4F			RT	A10CE   					 
	20080826		NM  	2008	8	26	2008FA0000557    	1	20080801	G	2742	900C2010375103	CONTROL ROD     			DOUG  	MD900 	MD900       	3027375	NM  										VERTICAL STAB	BROKEN          	C				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	25	902RN					90000121				EXPERIENCED EXCESSIVE LT PEDAL (2-3 INCHES) DURING CRUISE FLIGHT AT 70 TO 80 PERCENT TRANSMISSION TORQUE.  DURING POST F	LIGHT FOUND THAT THE LT VERTICAL STABILIZER MOVED FREELY.  FURTHER INSPECTION REVEALED THAT THE LT VERTICAL STABILIZER C	ONTROL SYSTEM (VSCS) ACTUATOR CONTROL ROD WAS BROKEN AT THE THREADED PORTION.  (S)				1	G	7	2 	3U			NC	H19NM   					 
	20080903		CE  	2008	9	3	2008FA0000558    	1	20080801	G	5753	0425118	FITTING         			CESSNA	140   	140         	2071602	CE  										LT TE FLAP	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	76671					11111				THE PART WAS BEGINNING TO RUST THROUGH IN LOCATION RESPONSIBLE FOR ATTACHING THE LT FLAP TO THE FLAP CONTROL. THE DEFECT	 WAS FOUND DURING AN ANNUAL INSPECTION. PROBABLE CAUSE WAS RUSTING DUE TO AGE. A MORE THOROUGH INSPECTION OF THE AREA DU	RING PREFLIGHT SHOULD HELP DETECT THE PROBLEM SO THAT CORRECTIVE ACTION CAN BE TAKEN.				1	H	7	1 	3O			NC	A768    					 
	20080903		EA  	2008	9	3	2008FA0000559    	2	20080810	G	7414		DRIVE SHAFT     			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					MAGNETO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2952R				03092108	28R35344				DISTRIBUTOR (POINT CAM SHAFT BROKE FLUSH WITH UPPER MAG GEAR INNER RACE CAUSING TOTAL MAG FAILURE.  PART WAS RETURNED TO	 OWNER.  (K)					1	L	7	1 	3O	3	O		2A13    	1E10				 
	20080903		CE  	2008	9	3	2008FA0000560    	1	20080808	G	3222	S18271	VALVE           			CESSNA	172   	R172K       	2072431	CE  										NOSE STRUT	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	9927V					R1722354				A NEW VALVE WAS ORDERED AND INSTALLED TO CURE A SUSPECTED LEAK IN THE VALVE CORE.  THE NEW VALVE ARRIVED WITH A BRIGHT A	PPEARANCE, EITHER CHROME OR NICKEL PLATED.  WITH THE NEW VALVE INSTALLED, THE STRUT LEAK WORSENED.  AN EXTERNAL INSP REV	EALED THAT THE COSMETIC PLATING WAS FLAKING FROM THE HEX FLATS.  THE VALVE WAS REMOVED AND IT WAS FOUND THAT THE PLATING	 WAS ALSO FLAKING IN THE THREAD-AREA, AND THIS RESULTED IN A LEAK AROUND THE VALVE.  THIS VALVE EMPLOYS A NPT THREAD (1/	4 INCH PIPE THREAD) AND THE THREADS FORM THE SEAL WHEN INSTALLED.  THE REMAINING PLATING WAS EASILY SCRAPED FROM THE THR	EADS WITH A PICK AND THE VALVE WAS REINSTALLED WITHOUT FURTHER DIFFICULTY.  SUBMITTER ADMITS THAT THE PLATING RESULTS IN	1	H	7	1 	3O				3A17    					 
	20080903		SO  	2008	9	3	2008FA0000561    	1	20080513	G	2497		WIRE            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O320  	O320*       	41508	EA  					ALTERNATOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	2163F				H092370	447995167				INTERNAL FAILURE DUE TO BROKEN WIRES INTERNALLY, HEAVY SPARKING INSIDE ENGINE COMPARTMENT.  (K)						1	L	7	2 	3O	3	O		A19S0   	E274				 
	20080903		CE  	2008	9	3	2008FA0000562    	1	20080627	G	5311	12943003723	FRAME           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  					FS 363.25	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	534M	10817				UE333				DURING STRUCTURAL INSP, FOUND LOWER FRAME WEB CRACKED AT FLANGE CORNER.  TEE ATTACHED TO FRAME CRACKED THRU LOWER RIVET 	HOLE.  DOUBLER ATTACHED TO LOWER AFT SIDE OF WEB WAS ALSO CRACKED.  THE AFT CLIP, ATHAT ATTACHES THE LOWER FRAME TO THE 	SIDEWALL SEAT TRACK STRINGER, WAS LEFT OUT AT BUILD.  THE STRESSES NOT BEING TRANSFERRED TO SUPPORTING STRUCTURE, BECAUS	E OF THE MISSING CLIP, MAY HAVE ADDED TO THE FRAME FAILURE.  THE DAMAGE WAS REPAIRED IAW SRM AND DER REPORT.  (K)			2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
	20080903		CE  	2008	9	3	2008FA0000563    	1	20080808	G	2810	5038903417	FUEL CELL       			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LT WING	PLUGGED         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	350RV	60   				FL585				PILOT REPORTED FUEL IMBALANCE OF 200 LBS AFTER TOPPING OFF TANKS.  FUEL QUANTITY INDICATING AND FUEL VENT SYSTEM WERE CH	ECKED AND CONFIRMED GOOD.  DURING DEFUEL, NOTED THAT LT WING TRANSFER TO LT NACELLE TANK WAS TOO SLOW TO ALLOW FULL SERV	ICING OF LT WING FUEL SYSTEM .  ACCESSED FUEL TRANSFER TUBE FROM INSIDE OF LT IB AFT FUEL CELL, TO NACELLE FUEL TANK, AN	D FOUND IT PLUGGED WITH A RAG.  REMOVED RAG, CLEANED WING FUEL STRAINER, AND SECURED FUEL SYSTEM.  LT FUEL SYSTEM CAN NO	W BE SERVICED TO FULL.  (K)		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20080903		CE  	2008	9	3	2008FA0000565    	1	20080813	G	7160	125083029	INTAKE DUCT     			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O550  	IO550*      	 	SO  					ENGINE	CRACKED         	B			RC0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	602MB	10   				U20604052				MFG SUPPLIED ENGINE INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS.  THIS PARTICULAR AC 	AND ANOTHER IDENTICAL MODEL AC THIS FACILITY MAINTAINS, HAVE BEEN CONVERTED TO ANOTHER ENGINE AFTER THE STC CONVERSION. 	 CRACKING PROBLEM HAS INCREASED SIGNIFICANTLY.  HAVE CONTACTED STC HOLDER, THEY HAVE RESPONDED WITH A SCHEME TO REINFORC	E THIS DUCT.  THIS REPAIR STATION IS LOOKING INTO THIS ALTERATION TO THIS DUCT WHEICH MAY REQUIRE DER SUPPORT.  AT PRESE	NT, THE DUCTS ARE REQUIRING REPAIRS OF REPLACEMENT EVERY 50 HOURS.  A PMA REPLACEMENT DUCT MADE FROM COMPOSITE MATERIAL 	IS NO LONGER AVAILABLE. (K)	1	H	7	1 	3O	3	O		A4CE    	E3SO				 
	20080827		NM  	2008	8	27	2008FA0000566    	1	20080218	G	7830	315A2502102	PANEL           			BOEING	737   	737         	UTILSYS	NM  										THRUST REVERSER	DELAMINATED     	B			Z6WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07		33297								THE TRANSLATING SLEEVE OF THE NR2 OTBD THRUST REVERSER HALF, INNER BOND PANEL ASSY (ACOUSTIC) HAS AN AREA APPROXIMATELY 	30 INCHES X 85 INCHES WHERE THE PANEL HAS DELAMINATED/SEPARATED FROM THE CORE.  THIS AREA STARTED AS 12 SMALL AREAS OF D	ELAMINATION AND CONTINUES TO GROW.  THE PANEL IS BEING  SCRAPPED AS A RESULT.  THE BONDING SURFACE OF THE PERFORATED PAN	EL APPEARS TO HAVE BEEN INADEQUATELY PREPPED PRIOR TO BONDING IN THE ORIGINAL BUILD.  THIS CONDITION WAS DISCOVERED AT S	PIRIT AEROSYSTEMS REPAIR STATION Z6WR3367 WHERE IT WAS SENT FOR REPAIR FROM CONTINENTAL AIRLINES.  (S)		2	L	7	2 	4F			RT	A16WE   					 
	20080828		NM  	2008	8	28	2008FA0000567    	1	20080822	G	5313		LONGERON        			DOUG  	MD80  	MD83        	3023681	NM  										BS 154 L23L	DAMAGED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	874GA					49643				DURING SCHEDULED REPAIR, FOUND DOUBLE DRILLED ON LONGERON 23L AT FS 154.5.  (S)						2	L	7	2 	4F			RT	        					 
	20080828		NM  	2008	8	28	2008FA0000568    	1	20080822	G	5313		LONGERON        			DOUG  	MD80  	MD83        	3023681	NM  										BS 150 L23L	DAMAGED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	874GA					49643				DURING SCHEDULED REPAIR, MISDRILLED 3 EACH HOLES AT FS 150 AND 3 INCHES BELOW LONGERON 23L.  (S)						2	L	7	2 	4F			RT	        					 
	20080903		EU  	2008	9	3	2008FA0000570    	1	20080729	G	6220	704A33651158	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					M/R SWASHPLATE	WORN            	B			P49R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	277HC	688  			M1687	2052				COMPLIED WITH 2 YEAR / 500 HR INSP.  TASK 62.30.00.601 M/R SHAFT INSP.  WHILE PERFORMING INSP OF SWASHPLATE GUIDE UNIBAL	L FOUND WHILE ROTATING SWASHPLATE.  UPPER SEAL FOR BRG WAS NOT ROTATING BECAUSE IT WAS NOT FIRMLY ATTACHED TO OUTER RACE	 OF BRG WITH THE SEAL BEING LOOSE & UNSECURED IT WORE INTO SWASHPLATE BRG OUTER STOP RING.  REPLACED SWASHPLATE BRG, OUT	ER STOP RING WITH NEW.  RECOMMENDATION WOULD BE WHILE GREASING SWASHPLATE BRG DURING 100 HOUR INSP, LIFT SWASHPLATE BOOT	 TO INSPECT BRG SEAL FOR MOVEMENT DURING ROTATION. (L)		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
	20080903		CE  	2008	9	3	2008FA0000571    	1	20080722	G	2730		CONTROL CABLE   			MTSBSI	MU2   	MU2B36A     	5780413	CE  										ELEVATOR	BROKEN          	B			IZ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	868MA	9216 				708SA				PILOT COMPLAINED OF POOR ELEVATOR TRIM OPS.  UPON INSP, FOUND ELEVATOR TRIM CABLE 311AS-14-7245 BROKEN (RT CABLE).  311A	S-14-7362 (LT CABLE), 010A-61179-81 (RT AFT) CABLES FRAYED.  IDLER PULLEY SHAFT ON PITCH TRIM SERVO SHEARED.  REPLACED C	ABLES & SERVO, OPS CHECKED.  RIGGED AS NEEDED.				1	H	7	2 	3T				A10SW   					 
	20080903		SO  	2008	9	3	2008FA0000572    	1	20080818	G	3233	35380000000	ACTUATOR        			GULSTM	G159  	G159        	3952202	SO  	GARRTT	TFE731	TFE7314R    	01518	WP  					RT MLG	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	5950C	774  				213				RT MLG SIDE BRACE ACTUATOR LEAKING FROM SWITCH ASSY.  SIDE BRACE ACTUATOR REMOVED, REPLACED WITH REPAIRED ACTUATOR ASSY.						2	L	7	2 	4T	4	F		1A17    	E6WE				 
	20080903		CE  	2008	9	3	2008FA0000573    	1	20080821	G	2842	1183810025	FLOAT VALVE     			RAYTHN	390   	390         	7150030	CE  										FUEL TANK	SEPARATED       	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			WP	01	3725L	1219 				RB155				DURING 1200 HR INSP WHICH REQUIRES OPENING ALL WING AND FUSELAGE FUEL TANK ACCESS PANELS FOR INTERNAL INSPECTION IN BOTH	 LT & RT CTR FUSELAGE TANKS, FWD FLOAT VENT VALVES FLOAT SECTION OF VALVE ASSY WAS FOUND SEPARATED AND LAYING LOOSE INSI	DE FUEL TANK AREA.  RECOMMEND INSP OF LT & RT FWD VENT VALVE FLOAT ASSEMBLIES AT NEXT EARLIEST TIME OR INSP.  REPLACE AL	L SUSPECTED OR FAULTY FLOAT VALVES.			1	L	7	2 	3F			RT	A00010WI					 
	20080903		SO  	2008	9	3	2008FA0000574    	2	20080815	G	7414		IMPULSE COUPLING			CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	92551	1736 				18260256	275543R	891141		PILOT PERFORMED PRE-FLIGHT INSP DISCOVERED OIL ON FWD PORTION OF COWLING, SLIGHT OIL RESIDUE ON WINDSHIELD.  MECHANIC RE	MOVED TOP COWLING TO INVESTIGATE, DISCOVERED MAGNETO HOUSING SHATTERED AT AREA IMMEDIATELY ADJACENT TO IMPULSE COUPLING.	  APPARENTLY IMPULSE COUPLING ENGAGING MECHANISM SOMEHOW CONTACTED ACTUATING PIN WHILE OPERATING (OR ENGINE BACKFIRED, W	E DON`T HAVE FURTHER INFORMATION TO ASCERTAIN THIS CONDITION) SHATTERED MAGNETO BODY HSG.  MAGNETO WAS STILL FIRING, FIX	ED TO ENGINE (NOT LOOSE) ENGINE OPS WAS REPORTED NORMAL UPON ARRIVAL OF LAST FLIGHT, WHICH SEEMS TO INDICATE THAT MAGNET	O HAD OPERATED IN THIS CONDITION FOR WHAT APPEARS TO BE AT LEAST AN HOUR OR MORE.  NO MISFIRE OR MAGNETO DROP DETECTED.	1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
	20080904		NM  	2008	9	4	2008FA0000575    	1	20080821	G	2421		SHAFT           			DOUG  	MD90  	MD9030      	3023690	NM  										AC GENERATOR	SEIZED          	C			HZ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		17572			436					GENERATOR UNIT SEIZED. THE GENERATOR FAILURE ROOT CAUSE WAS DETERMINED TO BE A ROTOR BAND SHAFT WHICH RESULTED IN AN OUT	 OF BALANCE CONDITION. THE OUT OF BALANCE ROOT CAUSED AN EARLY FAILURE OF THE ADE BEARING. ALL OTHER DAMAGE RESULTED FRO	M THE BEARING FAILURE. PENDING ENGINEERING EVALUATION. (K)				2	L	7	2 	4F			RT	A6WE    					 
	20081001		EA  	2008	10	1	2008FA0000577    	2	20080612	G	8530	AEL12688P020	VALVE SEAT      								LYC   	O360  	IO360A1A    	41514	EA  					CYLINDER HEAD	DAMAGED         	B			Y2GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23										INTAKE VALVE SEAT CAME LOOSE FROM THE SEAT BORE IN THE CYLINDER HEAD.  THE LOOSE SEAT DAMAGE TO THE CYLINDER HEAD, VALVE	, AND VALVE SEAT.  INTERFERENCE FIT BETWEEN THE VALVE SEAT AND THE CYLINDER HEAD WAS NOT CORRECT.  THIS WAS AN OVERHAULE	D CYLINDER. (K)									3	O			1E10				 
	20081001		EA  	2008	10	1	2008FA0000578    	2	20080716	G	8530	AEL12688P020	VALVE SEAT      								LYC   	O360  	IO360C1E6   	41514	EA  					CYLINDER HEAD	DAMAGED         	B			Y2GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23										INTAKE VALVE SEAT CAME LOOSE FROM THE SEAT BORE IN THE CYLINDER HEAD.  THE LOOSE SEAT DAMAGE TO CYLINDER HEAD, VALVE, AN	D VALVE SEAT.  INTERFERENCE FIT BETWEEN THE VALVE SEAT AND THE CYLINDER HEAD WAS NOT CORRECT.  THIS WAS AN OVERHAULED CY	LINDER. (K)									3	O			1E10				 
	20080909		SO  	2008	9	9	2008FA0000579    	1	20080610	G	2916		RESERVOIR       			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  					HYD SYSTEM	LOW             	G				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CE	01	727HB					318112006	L266868A			ON FINAL APPROACH THE LANDING GEAR HANDLE WAS PLACED IN THE DOWN POSITION.  THE GEAR WAS VIEWED IN THE MIRROR AT 45 DEGR	EE ANGLE.  THERE WERE NO GREEN LIGHTS INDICATING GEAR DOWN AND LOCKED. THE PILOT TRIED TO RAISE AND LOWER THE GEAR AGAIN	 WITH NO MOVEMENT EITHER DIRECTION.  THE PILOT THEN PROCEEDED TO MANUALLY PUMP THE GEAR DOWN.  AFTER THREE GREEN LIGHTS 	WERE ON, THE AIRCRAFT WAS FLOWN BACK, WITH THE GEAR DOWN.  MAINT NOTE: HYDR RESERVOIR WAS FOUND TO BE IMPROPERLY SERVICE	D. TRAINING WAS CONDUCTED FOR ALL MAINT ON PROPERLY SERVICING THE POWERPACK.  THIS CAN BE TRICKY AS IT IS DIFFICULT TO S	EE THE FLUID LEVEL.  (K)	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20080909		CE  	2008	9	9	2008FA0000580    	1	20080827	G	2435		BEARING         			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					STARTER GEN	FAILED          	B			OW5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	27	802Q				95264	S5500157	PCE102330			FRONT BEARING FAILURE IN FLIGHT. (K)						1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
	20081001		SO  	2008	10	1	2008FA0000581    	1	20080812	G	5100	SL53E19600	VERNATHERM      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  		FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AL	03	27663	392  				317852094	L152068A	DJ10231A		THIS VERNATHERM HAD A SHAFT AND NUT ASSY THAT WAS SECURED WITH A ROLL PIN.  THE SHAFT FAILED AT ROLLPIN.  THE NUT, SHAFT	 PIECE AT ROLLPIN TRAVELED THRU THE OIL GALLY AND LODGED AT A FITTING.  HIGH OIL TEMP ALERTED US TO THIS FAILURE, OIL PR	ESSURE WAS NORMAL.(K)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081006		EA  	2008	10	6	2008FA0000583    	2	20080708	G	8530		CYLINDER HEAD   			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C16    	GL  	ENGINE	SEPARATED       	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			WP	19	5268U					172RG0314	RL2898936A	04136		ON JULY 8, 2008, MADE AN EMERGENCY LANDING IN DESSERT TERRAIN AFTER THE ENGINE BEGAN TO EXHIBIT SEVERE VIBRATIONS, LOSS 	OF POWER AND  SMOKE.  THE NR 2 CYLINDER WAS FOUND TO HAVE SEPARATED FROM THE CASE, SEVEN OF THE EIGHT HOLD STUDS WERE FO	UND TO HAVE SHEARED.  ONLY ONE HOLD DOWN STUD WAS LT INTACT.  THERE WAS NO HISTORY IN THE AC LOGS TO INDICATE IF THE HOL	D DOWN STUDS HAD BEEN REPLACED.  (K)			1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
	20080909		CE  	2008	9	9	2008FA0000584    	1	20080731	G	2510	551900921	SEAT FRAME      			CESSNA	500   	550         	2076604	CE  										COCKPIT SEAT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	64TF					5500064				UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  CHAI	R WAS REPAIRED IAW STO-1042WI STRUCTURAL SEAT REPAIR.  (K)					1	L	7	2 	4F				A22CE   					 
	20081006			2008	10	6	2008FA0000585    	1	20080818	G	2421	11522185	GENERATOR       																		FAILED          	B			HZ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		1572 								FAILS SATURATION CURVE CHECK-ZERO VOLTS ANY PHASE. BROKEN LOWER CROSSOVER ON ROTOR.  PENDING ENGINEERING EVALUATION. (K)																			 
	20081003		EA  	2008	10	3	2008FA0000586    	2	20080915	G	8520	TT73806	PUSHROD         								LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11							L1972215			(3) PUSHRODS (TT73806) WERE INSTALLED IN THIS ENGINE AND ALL 3 HAD APPROXIMATELY A .3750 INCH VERTICAL CRACK ON BOTH END	S. CAUSE UNKNOWN - NO RECOMMENDATIONS. (K)										3	O			E223				 
	20081006			2008	10	6	2008FA0000587    	4	20080819	G	6113	D57691P	DOME            			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	SPINNER	CRACKED         	B			NT3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	25	9485V	22   				700043		CH42078B		THE SPINNER ASSY FAILED IN FLIGHT ON A 2.2 HR FLIGHT LEG. APPROXIMATELY 1.5 HRS INTO THE FLIGHT A SMALL SHUDDER WAS FELT	 AND ALL INDICATION CHECKED NORMAL. THE AC COMPLETED THE FLIGHT AND IT WAS NOTED THAT 4" X 4" SECTION OF THE SPINNER BRO	KE OFF. THE COWLING HAD TWO SCRAP MARKS AND NO OTHER DAMAGE WAS NOTED.  MFG SL-61-286 WAS ACCOMPLISHED 7.31 HRS PRIOR TO	 FAILURE. OWNER REPORTS SPINNER WAS CHECKED ON PREFLIGHT APPROXIMATELY 1.5 HRS PRIOR TO FAILURE. SPINNER TT 21.64 HRS. P	ROBABLE CAUSE: SPINNER DOME IS TOO LARGE FOR A SPINNER WITHOUT A FORWARD BULKHEAD FOR SUPPORT. (K)		1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
	20081003		SO  	2008	10	3	2008FA0000588    	1	20080826	G	3220	502341	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  										NG LOCKING PAW	SHEARED         	D			MOVV	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	239AT					4496038				DURING FAA CHECK RIDE, THE NOSE LANDING GEAR DID NOT PROVIDE A GREEN LIGHT AND THE GEAR UNSAFE WARNING LIGHT AND HORN OP	ERATED. AFTER AN UNEVENTFUL LANDING. THE ACFT WAS BROUGHT INTO MAINT FOR TROUBLESHOOTING AND REPAIRS. THE PIVOT BOLT FOR	 THE NOSE GEAR LOCKING PAW HAD SHEERED IN TWO. THE FAIL POINT IS LOCATED 1.25 INCHES FROM THE BOTTOM OF THE BOLT HEAD. T	HIS PREVENTED THE PAW FROM ACTUATING PROPERLY AND CLOSING THE DOWN LIMIT SWITCH. UPON REPLACEMENT WITH A NEW BOLT, THE P	AW ACTUATED PROPERLY AND THE GEAR RETRACTION AND EMERGENCY EXTENSION WERE NORMAL WITH PROPER INDICATIONS.  (K)		1	L	7	2 	3O				A19S0   					 
	20081006		GL  	2008	10	6	2008FA0000589    	1	20080826	G	2110	220045510	DRIVE SHAFT     			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					COMPRESSOR	SHEARED         	B			5CSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	433CF					0710				THIS AC HAS HAD 5 FAILURES OF THE AIR CONDITIONING COMPRESSOR DRIVE SHEAR SHAFT. THE AVERAGE TIME BETWEEN FAILURES IS 35	.8 HOURS. THE SAME SHAFT BUILT BY ANOTHER MFG, HAS HAD ZERO FAILURES. WE HAVE HAD SEVERAL FAILURES IN DIFFERENT AC WITH 	THIS PART. THE DESIGN OF THE OTHER SYSTEM SHAFT IS SLIGHTLY DIFFERENT.  MFG WILL NO LONGER COVER THIS PART UNDER WARRANT	Y. WE HAVE TRIED SEVERAL RECOMMENDATION FROM MFG TO SOLVE THIS PROBLEM TO NO AVAIL. (K)			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
	20081006		CE  	2008	10	6	2008FA0000590    	1	20080813	G	3222	998201005	STRUT           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					NLG	MALFUNCTIONED   	C			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	1250					FA88				POSITION OF THIS TORQUE LINK MOUNT RELATIVE TO THE SHIMMY DAMPNER ARMS HOLE ARE SUCH THAT THE TWO PARTS INTERFERE WITH E	ACH OTHER AND DONT ALLOW THE STRUT TO COMPRESS CLOSER THAN 2 INCHES FROM FULLY COLLAPSED. (K)					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081003		EA  	2008	10	3	2008FA0000591    	2	20080805	G	8520	ST203P010	PISTON RING     			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03	2170Q	25   				177RG0570	L1256851A			ENGINE WAS OVERHAULED USING MFG PISTON RINGS ST203P010. AFTER 25.4 HRS, RINGS STILL NOT SEATED AND EXCESSIVE BLOW-BY WAS	 FOULING PLUGS. REPLACED WITH ANOTHER SET OF ST203P010 AFTER HAVING CYLINDERS REWORKED. AFTER 4.2 HRS, ENGINE WAS OPERAT	ING SO POORLY, DUE TO BLOW-BY, THAT IT WAS CONSIDERED UNSAFE AND GROUNDED.  INDEPENDENT HARDNESS TESTING BY QUALITY TEST	ING SVCS, INC, COMFIRMED THE RINGS WERE SOFT. COMPARATIVE TESTS WERE PERFORMED AGAINST PISTON RINGS. AFTER SWITCHING TO 	OTHER, THERE HAVE BEEN NO PROBLEMS.(K)		1	H	7	1 	3O	3	O		A20CE   	1E10				 
	20081006		CE  	2008	10	6	2008FA0000592    	1	20080821	G	3230	12801111	SWIVEL FITTING  			CESSNA	182   	R182        	2072734	CE  										LT GEAR LEG	FAILED          	H				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	03	4652T					R18201725				BRAKE SWIVEL JOINT FAILED LEADING TO FAILURE OF LT BRAKE WHEN EXITING RUNWAY. (K)						1	H	7	1 	3O			RT	3A13    					 
	20081006		EU  	2008	10	6	2008FA0000593    	1	20080811	G	3520	MC1014101	OXYGEN MASK     			BRAERO	DH125 	BAE125800A  	1500285	EU  										CABIN	FAILED          	D			G13R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	862CW					258062				THREE OXYGEN MASKS WERE FOUND TO HAVE THE SAME FAULT. WHEN THE EMERGENCY/PRESS TO TEST CONTROL WAS TURNED TO EMERGENCY T	HERE WAS NOT A POSITIVE INCREASE IN PRESSURE. REF MFG MM 35-20-52, PAGE 502 TEST (13). PROBABLE CAUSE: UNKNOWN, RECOMMEN	DATION: INCREASE HOW OFTEN CREW OXYGEN MASKS ARE TESTED AND INSURE THAT THEY ARE BEING TESTED PROPERLY.(K)				2	L	7	2 	4F			RT	A3EU    					 
	20081006		EU  	2008	10	6	2008FA0000594    	1	20080811	G	3520	MC1014101	OXYGEN MASK     			BRAERO	DH125 	BAE125800A  	1500285	EU  										CABIN	DAMAGED         	D			G13R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	897CW					258077				THREE OXYGEN MASKS WERE FOUND TO HAVE THE SAME FAULT. WHEN THE EMERGENCY/PRESS TO TEST CONTROL WAS TURNED TO EMERGENCY T	HERE WAS NOT A POSITIVE INCREASE IN PRESSURE. REF MFG MM 35-20-52, PAGE 502 TEST (13). PROBABLE CAUSE: UNKNOWN, RECOMMEN	DATION: INCREASE HOW OFTEN CREW OXYGEN MASKS ARE TESTED AND INSURE THAT THEY ARE BEING TESTED PROPERLY. (K)				2	L	7	2 	4F			RT	A3EU    					 
	20081007		EA  	2008	10	7	2008FA0000595    	1	20080821	G	3241	60025663	PCB             			CNDAIR	CL600 	CL600*      	1900302	EA  										MLG	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	604SJ				JAN82118	1042				UPON LANDING, THE LT OB TIRE BLEW. UPON INSP, TIRE SHOWED SIGNS OF A SEVERE SKID. TESTED THE ANTISKID SYS & TESTED NORMA	L. TESTED ALL 4 WHEEL SPEED SENSORS AND FOUND THAT WITH THE BRAKES SET & FULL HYD PRESSURE ON, BOTH OB MAIN WHEELS WOULD	 NOT RELEASE WHEN SPINNING STOPPED ON WHEEL SPEED SENSORS. BOTH IB WHEELS RELEASED NORMALLY WHEN TESTED. CONTACTED MFG T	ECH SUPPORT & INFORMED THE COMPUTER HAD 2 IDENTICAL PCB CARDS THAT COULD BE SWAPPED FOR TROUBLESHOOTING PURPOSES. ONE CA	RD IS FOR THE IB MAIN WHEELS AND 1 CARD IS FOR THE OB MAIN WHEELS. SWAPPED CARDS AND THE PROBLEM FOLLOWED TO THE IB MAIN	 WHEELS. NOW THE OB MAINS WOULD RELEASE NORMALLY DURING A SIMULATED SKID CONDITION BUT THE IB MAINS WOULD NOT RELEASE. R	2	L	7	2 	4F			RT	A21EA   					 
	20081007		CE  	2008	10	7	2008FA0000596    	1	20080821	G	7820	83004	MUFFLER         			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	22355	339  				15068233	682287A			END CAP SEPARATED (CLEAR BREAK) FROM MUFFLER CAR.  FAILURE OCCURED IN THE BEND RADIAS OF END CAP. NOT IN THE END CAP TO 	MUFFLER CAP, WELD. (K)					1	H	7	1 	3O	3	O		3A19    	E252				 
	20081003		NE  	2008	10	3	2008FA0000597    	2	20080826	G	7250	305086010	SUPPORT         			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   	      	CFE73811B   	 	NE  					NR 4 BEARING	CRACKED         	B			ZN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	48CG	3031 				041	P105194			THE NR 4 BEARING SUPPORT, PN 305086010, CRACKED CAUSING THE ENGINE TO SEIZE. AT OPERATING TEMPERATURES, THE NR 4 BEARING	 SUPPORT AND INVESTMENTCAST MANIFOLD MAY HAVE BECAME LOOSE, PERMITTING RELATIVE MOVEMENT BETWEEN THE PARTS. SB CEF738-7	2-8060 REPLACES THE NR 4 BEARING SUPPORT WITH SUPPORT ASSY PN 305086012, WHICH HAS BEEN DESIGNED WITH AN INCREASED INTER	FERENCE FIT TO ELIMINATE MOVEMENT. (K)			2	L	7	2 	4F	4	F	RT	A50NM   	E44NE				 
	20081007		GL  	2008	10	7	2008FA0000598    	1	20080814	G	5344	DA4522100002	HINGE           			DIAMON	DA40  	DA40        	2990002	GL  										AFT PAX DOOR	BROKEN          	D			L10R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	681DS	523  				40611				THE REAR CABIN DOOR AFT HINGE HAS BROKE AS DECRIBED IN AC 43-16A ALERT 360.  PROBABLE CAUSE IS REAR HOLD-OPEN CYLINDER.						1	L	7	1 	3O			NT	A47CE   					 
	20081006		GL  	2008	10	6	2008FA0000599    	1	20080814	G	5210	DA4522100002	HINGE           			DIAMON	DA40  	DA40        	2990002	GL  										AFT CABIN DOOR	CRACKED         	D			L10R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	504DS					40204				THE REAR CABIN DOOR AFT HINGE HAS A CRACK IN THE SAME AREA AS DESCRIBED IN AC 43-16A ALERT 360. PROBABLE CAUSE IS REAR H	OLD-OPEN CYLINDER. (K)					1	L	7	1 	3O			NT	A47CE   					 
	20081006		CE  	2008	10	6	2008FA0000600    	1	20080702	G	3240		BRAKE ASSY      			CESSNA	525   	525B        	2076616	CE  	WILINT	FJ44  	FJ44        	66000	GL  					MLG	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	03	92MA					525B0048				NORMAL LANDING UNTIL BRAKE APPLICATION, AT BRAKE APPLICATION AC YAWED AGRESSIVELY TO THE LT. AC WAS CONTROLLED WITH RT B	RAKE AND NOSE WHEEL STEERING. RT BRAKE APPEARED WEAK, AS SPEED DECREASED DIRECTION CONTROL WAS HARDER TO MAINTAIN. AC DE	CELERATED SLOWER THAN NORMAL APPROACHING END OF RUNWAY. EMERGENCY BRAKE WAS APPLIED. LT BRAKE GRABBED FORCING THE ACFT O	FF THE RUNWAY INVESTIGATION IN TO SOURCE OF THE PROBLEM IS ON GOING.  PN AND PART NAME WILL FOLLOW AFTER MFG TEST COMPON	ENTS. (K)		1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
	20081003		CE  	2008	10	3	2008FA0000601    	1	20080901	G	8011	149NL	STARTER         			CESSNA	172   	172S        	2072439	CE  										ENGINE	FAILED          	B			NO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	GMEGS	55   				10723				STARTER MOTOR FAILURE, AFTER PRE-FLIGHT CHECK, THE STARTER MOTOR WAS UNABLE TO TURN THE ENGINE OVER. (K)						1	H	7	1 	3O			NT	3A12    					 
	20081003		CE  	2008	10	3	2008FA0000602    	1	20080814	G	7921	99103434	OIL COOLER      			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  						CRACKED         	B			MT9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	9762F					20800181	PCE17397			UPPER MOUNTING FLANGE HAS A 1.25 INCH CRACK AGAINST OIL COOLER BODY. (K)						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
	20081003		CE  	2008	10	3	2008FA0000603    	1	20080723	G	2820		RING            			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					REFUELING SYS	DISLODGED       	W			NUUY	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	35	390EV					RB				PRESSURE REFUELING CONNECTION CAP FOUND WITH SEALING RING DISLODGED AND HOLDING THE CHECK VALVE OPEN WHEN THE CAP IS INS	TALLED. FUEL LEAK FROM CAP CAUSING FUEL TO FLOW FROM IT UP THE SIDE OF THE AC. THE FUEL FLOWING UP THE OUTSIDE OF THE AC	FT HAS BEEN DRAWN INTO THE REAR MAINT BAY BY DIFFERENTIAL PRESSURE AT THE GROUND POWER SOCKET AND SPRAYED OVER FLYING CO	NTROL CABLES AND ELECTRICAL EQUIPMENT IN THE MAINT BAY AND TAIL CONE, THE DE-ICE CONTROL UNIT, STROBE POWER SUPPLY, PITC	H TRIM COMPUTER, COCKPIT VOICE RECORDER AND MAIN POWER DISTRIBUTION AND RELAY BOX ARE ALL CONTAMINATED. (K)		1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
	20081003		GL  	2008	10	3	2008FA0000604    	1	20080814	G	5610		CANOPY          			AMTR  	ZODIAC	CH601XL     	05615PW	GL  										COCKPIT	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	451BB					601051S				CANOPY OPENED IN FLIGHT RESULTING IN THE ACFT ENTERING INTO A NOSE DIVE ATTITUDE AND IMPACTING THE GROUND SERIOUSLY INJU	RING ONE PILOT AND MINOR INJURIES TO THE OTHER PILOT. THE CANOPYS LOCKING MECHANISMS AND OVERALL STRUCTURE DO NOT SEEM 	RELIABLE. THE LT AND RT LATCHING POINTS BOLTS DO NOT APPEAR TO BE LONG ENOUGH AND/OR PROVIDE ENOUGH MATERIAL FOR THE CAN	OPY LOCKS TO LATCH DOWN ON. THE CANOPY PLEXIGLASS IS VERY THIN AND COVERS A LARGE CANOPY AIRFRAME AREA WHICH MAKES THE C	ANOPY LOOSE AND WOBBLY. THE TWO GASEOUS RETRACT/ EXTEND SHOCKS ON EACH SIDE OF THE FWD CANOPY ALSO APPEAR TO BE TOO STRO	NG (40 PSI EACH) WHICH MAY CAUSE THE CANOPY TO HAVE A TENDENCY TO EXTEND IN THE OPEN POSITION IN FLIGHT. IN GENERAL, THE	1	L	7	1 	  				EXPA1L71					 
	20081003		CE  	2008	10	3	2008FA0000605    	1	20080807	G	3246	D30260	WHEEL           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					LT MLG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	17	9925V	4450 				17264559				AFTER LANDING,  WHILE TAXIING, HEARD A LOUD BANG. THEN ANOTHER BANG AND THE ACFT DROPPED LEFT. STOPPED, CONTACTED GROUND	 AND ASKED FOR ASSISTANCE. FOUND THE LT MAIN TIRE FLAT AND OUTER RIM FROM THE LT MAIN WHEEL WAS LYING 6 FT BEHIND ACFT, 	THE ATTACH BOLTS WERE SCATTERED ACROSS THE TAXIWAY. COULD ONLY FIND FOUR OF THE SIX BOLTS. ASI EXAMINATION OF THE WHEEL,	 THERE WAS A SPLIT IN THE INNER TUBE AND THE FOUR OUTER RIM ATTACH BOLTS THAT WERE FOUND HAD METAL FROM THE CENTER WHEEL	 HUB EMBEDDED IN THE BOLT THREADS WHERE THEY HAD PULLED OUT OF THE HUB.  TWO BOLTS WERE NOT LOCATED.  INSPECTED THE BOLT	 ATTACH AREAS OF THE HUB WITH A  MAGNIFYING GLASS, FOUND SOME CORROSION BUT NO APPARENT CRACKS NOTED.  IT APPEARS THAT E	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081006		CE  	2008	10	6	2008FA0000606    	1	20080815	G	3222	63420003	FORK            			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					NLG	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	300BV	1928 				5250418				DURING ROUTINE TAXI TO PERFORM MAINT CHECKS AFTER AC HAD BEEN PAINTED, NOSE GEAR AXLE BROKE LOOSE FROM NOSE GEAR STRUT. 	INVESTIGATION SHOWED BOTH WHEEL BEARING HAD HEAVY RUST AND DID NOT TURN FREELY ON THE AXLE. VERY LITTLE GREASE WAS FOUND	 IN EIGHER OF THE NOSE WHEEL BEARINGS. IT APPEARS THAT DURING THE TAXI, THE BEARINGS SEIZED ON THE AXLE AND THE RESULTAN	T STRESS AND HEAT CAUSED ONE SIDE OF THE NOSE STRUT ASSY TO BREAK WHICH IN TURN ALLOWED THE NOSE WHEEL AND AXLE TO COCK 	AND BEND THE OTHER SIDE OF THE NOSE STRUT. IMPROPER LUBRICATION OF THE NOSE WHEEL BEARINGS IS SUSPECTED AS A PROBABLE CA	USE.  (K)	1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
	20081007		NE  	2008	10	7	2008FA0000607    	2	20080906	G	7250	BRR19985	TURBINE BLADES  			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					HP TURBINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	551GA	3516 				606	11325			DURING A RECENT MID LIFE INSPECTION OF THIS ENGINE BY THE MFG, 58 OF 74 FIRST STATE TURBINE BLADES WERE FOUND  CRACKED B	EYOND SERVICEABLE LIMITS. THIS WAS A HIGH FAILURE RATE CONSIDERING THE LOW TOTAL ENGINE HOURS. A REPORT FROM THE MFG INT	ENDING TO PROVIDE AN UNDERSTANDING FOR THE HIGH RATE OF FAILURE STATED THAT SAND WAS INGESTED AND WAS BLOCKING SOME COOL	ING HOLES LEADING TO THERMAL STRESSES WHICH CAUSED THE CRACKS.  OF INTEREST IS THAT WHILE BOTH ENGINES ON THIS PARTICULA	R AIRFRAME WERE NEVER SEPARATED SINCE NEW AND ALWAYS OPERATED IDENTICALLY BY THE SAME CREWS, AND BOTH INSPECTED AT THIS 	TIME, ONLY ONE ENGINE EXHIBITED THIS ALARMINGLY HIGH RATE OF FAILURE TO THE STAGE 1 BLADES. THE SISTER ENGINE EXHIBITED 	2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
	20081007		GL  	2008	10	7	2008FA0000608    	2	20080904	G	7200	2544198	BEARING         	HONEYWELL   		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					PT GOVERNOR	FAILED          	B			HEFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	396RL		1648 		BR44409	45396	890360			SPOOL BEARING ASSY (PN 2544198) FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES AND CAUSED DRIVE SHAFT (PN 2539033) GU	IDE POST AND FORK ON GOVERNOR LEVER ASSY. (PN 2523293) TO BEND. ONE FLYWEIGHT (PN 2544200) WAS DAMAGED FROM THE SPOOL BE	ARING CHAFING. (K)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081003		GL  	2008	10	3	2008FA0000609    	2	20080905	G	7230		BLADE           			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20J     	03013	GL  					COMPRESSOR	FAILED          	B			HEFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	43MA	6228 	2904 		KR66644	4156				THIRD STAGE COMPRESSOR BLADE, ONE OF THE BLADES WAS "THROWN" FROM THE PART.  NOTE: THIS COMPRESSOR WHEEL IS A ONE-PIECE 	BLADE DISK. (K)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081003		GL  	2008	10	3	2008FA0000610    	2	20080908	G	7200	2544198	BEARING         			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30      	03013	GL  					SPOOL	FAILED          	B			HEFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	520RL	2932 	942  			52052	CAE895008			SPOOL BEARING ASSY FAILED INTERNALLY. BEARING ASSY NO LONGER ROTATES AND CAUSED DRIVE SHAFT GUIDE POST AND FORK IN GOVER	NOR LEVER ASSY TO BEND.  THE UPPER BEARING LOWER SHIELD AND RETAINER HAS COME OFF.  THE LOWER BEARING IS INTACT BUT NO L	ONGER ROTATES. (K)				1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
	20081007		SO  	2008	10	7	2008FA0000611    	1	20080814	G	3200	4049B	TUBE            			MAULE 	MX7   	MXT7160     	5470204	SO  	LYC   	O320  	O320*       	41508	EA  					AT FORK OLEO	SHEARED         	B			TODR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	31865	572  				17003C				OLEO TUBE (PN 4049B) SHEARED OFF AT FORK ASSY (PN 4086E) UPON LANDING DAMAGE DONE TO PROP, ENGINE, ENGINE MOUNT, NOSE GE	AR MOUNT, FIREWALL M ATTACH POINTS, LOWER COWL, AIR INTAKE PLUS ANY HIDDEN DAMAGE FOUND ON INSPECTION.  PN FOUND ON MFG 	DRAWING NR 4050X, DATED 6/7/1988.  OLEO TUBE ITEN NR 17, FORK ASSY, ITEM NR 5. (K)				1	H	7	1 	3O	3	O		3A23    	E274				 
	20081003			2008	10	3	2008FA0000612    	2	20080903	G	7414		BEARING         			CESSNA	182   	182T        	2072703	CE  										MAGNETO	BURNED          	B			L9OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	53610	503  			02111750	18281223				REMOVED MAGNETO TO S/B3-08 AND MFG 500 HOUR INSPECTION. REMOVED HARNESS CAP FOUND A LIGHT SMOKE COLORED FILM COVERING CA	P AND DISTRIBUTOR BLOCK. REMOVED MAGNETO FROM ENGINE FOUND BEARING BAR BURNED THROUGH ON LEFT SIDE WHEN VIEWED FROM DRIV	E END. (K)				1	H	7	1 	3O			NT	3A13    					 
	20081007		GL  	2008	10	7	2008FA0000613    	3	20080903	G	6111	C13019S	CLAMP           			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  	BLADE	FAILED          	B			ZY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	90BD	5569 				LA134		EAA1457		PROPELLER UNIT WAS OVERHAULED ON JULY 28, 2008, WO 79785. THE PROPELLER WAS INSTALLED ON ACFT AUG 27, 2008. UPON RUN UP 	OF ACFT, THE MECHANIC NOTED A GREASE LEAK FROM THE PROPELLER BLADE. A CRACK WAS FOUND. O/H FACILITY WAS NOTIFIED OF THE 	FINDINGS. THE PROPELLER WAS REMOVED FROM THE ACFT AND RETURNED TO THE FACILITY FOR INSPECTION .  O/H FACILITY VERIFIED T	HE SAME FINDINGS. BLADE CLAMP WAS REMOVED AND REPLACED WITH AN OHC CLAMP ASSY. ALL WORK WAS PERFORMED IAW SRM 118F, 202A	, AND 133C. (K)		1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA	 
	20081007		GL  	2008	10	7	2008FA0000614    	3	20080909	G	6110	B3476A2	ROD             			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	BROKEN          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	V2LFC				BUA26256			BUA26256		BETA ROD CRACKED, BROKEN.  PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT.  MALF	UNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081007		GL  	2008	10	7	2008FA0000615    	3	20080909	G	6110	B30012	RING            	HARTZL      		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	BROKEN          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	V2LFC	29388			BUA26256					BETA RING CRACKED, BROKEN.  PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT. MALF	UNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE.  (K)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081007			2008	10	7	2008FA0000616    	4	20080815	G	2562	DCELL	BATTERY         			PIPER 	PA28  	PA28161     	7102803	SO  										ELT	LEAKING         	B			KABR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	44FT	297  			043551	287716219				BATTERYS LEAK ACID ON TO SPRINGS AND CORRODED THEM. (K)						1	L	7	1 	3O				2A13    					 
	20081007		CE  	2008	10	7	2008FA0000617    	1	20080822	G	2121	903840311	BLOWER          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	VENT	FAILED          	B			BNGR	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	19	904RB		764  			LJ1088	PCE25175	FY2838		PILOT DETECTED SMOKE IN CABIN, LANDED.  TROUBLESHOT ODOR,  CHECK IN ENGINE BAYS, NO DEFECT NOTED. FOUND CABIN VENT BLOWE	R NOT WORKING, CHECKED BLOWER SYSTEM WIRING, NO DEFECTS NOTED, CHECKED VENT BLOWER UNDER PILOT FLOOR AND FOUND BLOWER MO	TOR LOCKED UP. REMOVED ASSY FOUND MOTOR HAD BURNED, ELEC ODOR. REMOVED AND REPLACED VENT BLOWER WITH OVERHAULED UNIT. OP	ERATION CHECKED NORMAL. THIS MOTOR RUNS ON LOW SPEED ANYTIME AUTO COOL OR AUTO HEAT SWITCH IS ON OR WITH BLOWER SWITCH I	N LOW OR HIGH AND ENGINES ARE RUNNING. DURING INSPECTION WITH THIS LOCATION OPEN, CHECK BLOWER FOR PROPER OPERATION AND 	SPEED. (K)	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	5	C	STC	 
	20081007		SO  	2008	10	7	2008FA0000618    	1	20080819	G	2810	3848808	TANK            			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540*      	41532	EA  					FUEL	LEAKING         	B			SVTR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	53646	607  				3246214				THE ACFT OPERATOR DROPPED THE ACFT OFF WITH A COMPLAINT OF A FUEL LEAK IN THE LT WING. THERE WAS EXTERNAL STAINING AT TH	E IB AFT EDGE OF THE TANK ASSY WHERE IT ATTACHES TO THE WING SKIN. THE TANK WAS REMOVED FROM THE AIRCRAFT TO LOOK FOR TH	E LEAK. IT APPEARS THAT THE SEALANT HAD DISSOLVED OR WASHED OUT OF THE TANK.  THE TANK WAS SENT FOR INSPECTION AND REPAI	R.  THEY VERIFIED THAT THE SEAM WAS LEAKING AND REPAIRED IT. THERE WAS NO VISIBLE PHYSICAL DAMAGE TO THE TANK OR MOUNTIN	G  STRUCTURE. AT THE AGE OF THIS AIRCRAFT, WOULD NOT EXPECT TO SEE A TANK LEAK LIKE THIS UNLESS THE SEALANT WAS IMPROPER	LY MIXED AT THE FACTORY OR ASSY OR SOME COMPONENT IN THE FUEL WAS DISSOLVING THE SEALANT. (K)	1	L	7	1 	3O	3	O		A3SO    	1E4				 
	20081007		CE  	2008	10	7	2008FA0000619    	1	20080915	G	2400		CONTACT         			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					RELAY	ERODED          	B			CROR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	300TN	415  				FA168				HAD 3 FAILURES OF THE SAME RELAY, FIRST RELAY LASTED 457 HOURS, SECOND RELAY LASTED 187 HOURS, AND THE THIRD RELAY LASTE	D 415 HOURS. MOST OF THE TIME THE FAILURE STARTS WITH THE 2 MICRO SWITCHES IN THE COVER GOING BAD. FOR HAVING RELATIVELY	 LOW TIME, THE MAIN CONTACTS WERE ERODED FAIRLY WELL. (K)				2	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081007			2008	10	7	2008FA0000620    	4	20080915	G	2397	M3902957357	SOCKET          			SKRSKY	S76   	S76B        	8143007	NE  										CONNECTOR	MISINSTALLED    	B			AMCR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	09	520AC	2422 				760380				CREW COULD NOT TRANSMIT ON AN FM FREQUENCY THROUGH NR 1 AUDIO CONTROL BOX. MAINT FOUND CONNECTOR PIN SOCKET INSTALLED BA	CKWARD. THE PART FOR THE WIRE WAS INSTALLED TOWARD THE PIN SIDE, AND THE PIN SIDE HAD THE WIRE CRIMPED INTO IT. THE SOCK	ET IS SYMMETRICAL. UNIT HAS BEEN LIKE THIS FOR MANY YEARS. (K)				1	G	7	2 	4U				H1NE    					 
	20081003		NE  	2008	10	3	2008FA0000621    	2	20080826	G	7230	307241613	COMPRESSOR WHEEL			AMD   	FALC90	FALCON900EX 	2730009	EU  	GARRTT	TFE731	TFE73160    	 	NE  					ENGINE	SEPARATED       	B			ZN3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	58CG					47	112349			THE CREW REPORTED VIBRATION AND ITT RISE. POWER WAS PULLED BACK TO IDLE AND THE AC LANDED WITHOUT INCIDENCE. DISASSEMBLY	 FINDINGS REVEALED THE LPC2 ROTOR ASSY  (PN 307241613). DISC PN 30603731, SN 990316003093, EXHIBITED MATERIAL LOSS IN TH	E FORM OF A DISC POST SEPARATION. (K)				2	L	7	3 	4F	4	F	RT	A46EU   	E1NM				 
	20081003		CE  	2008	10	3	2008FA0000622    	1	20080904	G	7810	265202231	COWLING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					EXHAUST	CRACKED         	B			MT9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	9634B					208B0141				THE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET.	 IT WAS NOTICED THAT ANOTHER CARAVAN IN THE HANGER FOR INSPECTION HAD THE SAME CRACK (LENGTH AND LOCATION) THAT HAD BEEN	 PREVIOUSLY REPAIRED BY INSTALLING A DOUBLER PATCH. (K)				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081003		CE  	2008	10	3	2008FA0000623    	1	20080905	G	5730		SKIN            			CESSNA	310   	310Q        	2074242	CE  										LT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	13	100EL					310Q0688				FOUND CRACK IN UPPER WING SKIN AS DESCRIBED IN SB MEB08-3.  CRACK EXTENDS 4 INCHES FORE AND AFT PARALLEL TO LT WING MAIN	 LANDING GEAR ASIDE BRACE WING RIB NR 502210451 OB FLANGE. CRACK IS APPROXIMATELY CENTERED IN MLG WHEEL WELL OPENING. CR	ACK WAS FOUND VISUALLY DURING COMPLIANCE WITH MEB76-2 MAIN LANDING GEAR RIB SIDE BRACE CRACKS, DURING INSTALLATION OF SK	414-8E. (K)			1	L	7	2 	3O				3A10    					 
	20081003		SO  	2008	10	3	2008FA0000624    	2	20080905	G	8520		BUSHING         			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					PISTON PIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	414NC					414A0484				DURING CYLINDER NR 2 REMOVAL TO CORRECT CRACKED CYLINDER, FOUND CONNECTING ROD PISTON P/N BUSHING CRACKED WITH LARGE PIE	CE MISSING FROM EDGE.  FAILURE IS AS NOTED IN MFG SB071. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE BUSHINGS C	RACKED IN SAME LOCATION.  MFG HAS CHANGED BUSHING SLIP LOCATION TO POSITION IAW FIGURE 3 OF SB B807. (K)				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
	20081007		SO  	2008	10	7	2008FA0000625    	2	20080905	G	8520		BUSHING         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					PISTON PIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	410AJ					421C1093	823531R			DURING CYLINDER NR 5 REMOVAL TO CORRECT HIGH OIL CONSUMPTION , FOUND CONNECTING ROD PISTON PIN BUSHING CRACKED WITH LARG	E PIECE MISSING FROM EDGE.  FAILURE IS AS NOTED IN MFG SB SB07-1. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE B	USHINGS CRACKED IN SAME LOCATION. MFG HAS CHANGED BUSHING SLIP LOCATION TO POSITION IAW FIGURE 3 OF SB SB071. (K)				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
	20081003		CE  	2008	10	3	2008FA0000627    	1	20080723	G	5753	710516000015	HINGE BRACKET   			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360*       	41514	EA  					LT WING TE FLAP	CORRODED        	G			BEJS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	6708A	7712 				ME302				LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFOR	M VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K)					1	L	7	2 	3O	3	O		A29CE   	E286				 
	20081007		CE  	2008	10	7	2008FA0000628    	1	20080722	G	5753	10516000015	HINGE BRACKET   			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360*       	41514	EA  					LT WING TE FLAP	CORRODED        	G			BEJS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	6638D	9976 				ME268				LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORT RIBS, WHERE HINGE BRACKET PIN FLAP. UNABLE TO PERFORM VI	SUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED INSIDE OF SKIN.  (K)					1	L	7	2 	3O	3	O		A29CE   	E286				 
	20081003		CE  	2008	10	3	2008FA0000629    	1	20080722	G	5753	10516000015	HINGE BRACKET   	BEECH       		BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360*       	41514	EA  					LT WING TE FLAP	CORRODED        	G			BEJS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	110SU	11007				ME81				LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFOR	M VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN.  (K)					1	L	7	2 	3O	3	O		A29CE   	E286				 
	20081003		CE  	2008	10	3	2008FA0000630    	1	20080723	G	5753	10516000015	HINGE BRACKET   	BEECH       		BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360*       	41514	EA  					LT WING TE FLAP	CORRODED        	G			BEJS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	278D	16533				ME23				LT FLAP OB HINGE BRACKET, SEVERE CORROSION AT IB AND OB SUPPORTING RIBS WHERE HINGE BRACKET JOINS FLAP. UNABLE TO PERFOR	M VISUAL INSPECTION OF AREA AS DAMAGE IS CONCEALED BY SKIN. (K)					1	L	7	2 	3O	3	O		A29CE   	E286				 
	20081006			2008	10	6	2008FA0000631    	4	20080911	G	6122	210044	ROD             	WOODWARD    		BEECH 	58    	58          	1152740	CE  										GOVERNOR	BROKEN          	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	6681L				1098981	TH1088				LIFT ROD WAS DISCOVERED BROKEN AT DISASSEMBLY. (K)						1	L	7	2 	3O				3A16    					 
	20081007			2008	10	7	2008FA0000632    	4	20080911	G	6122	B20429	DRIVE SYSTEM    	MCAULY      							CONT  	O520  	IO520*      	17032	SO  						BROKEN          	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	CGFLM				790221					SPRING-DRIVE DISCOVERED BROKEN AT DISASSEMBLY. (K)											3	O			E5CE				 
	20081007		SW  	2008	10	7	2008FA0000633    	1	20080826	G	6711	206076031107	SERVO           			BELL  	206   	206B3       	1181506	SW  										RT CYCLIC	MALFUNCTIONED   	C				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			SW	99	6NJ					4534				DURING START, PILOT NOTICED CYCLIC STICK COULD NOT BE MOVED WHEN THE HYD OFF PROTAKE OFF CHECK WAS INITIATED.  WITH HYD 	POWER ON, FLT CONTROL OP NORM.  THE HELICOPTER RETURNED FROM FLT, THE HYDRAULIC FIELD AND SERVO WERE HOT, IT WAS A VERY 	HOT DAY, TEMP ABOUT 96 DEGREES.  PILOT NOTICED THE CYCLIC STICK COULD NOT BE MOVED DURING HIS HYD CHECK.  IT WAS SHUT DO	WN AND BROUGHT INTO THE HANGAR MX.  A HYD MULE WAS HOOKED UP AND OPS NORMAL.  BELL HELICOPTER TECH REP WAS NOTIFIED AND 	ASKED TO COME TO THE FACILITY.  THE TECHS DID A GROUND RUN FOR APPROX 15 MIN W/O INCIDENT.  AFTER HOVERING FOR 5 MINUTES	, THE PROBLEM RETURNED.  THE PROB APPEARED TO BE THE RT HYD SERVO (S/N 8528).  LT SERVO WAS NEAR OVERHAUL, WE REPLACED I	1	G	7	1 	3U				H2SW    					 
	20081007		SO  	2008	10	7	2008FA0000635    	2	20080824	G	8500		ENGINE          			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  						POWER LOSS      	B			IGBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	8546U					17252446	29446D4D			AC WAS NOT OPERATING UNDER PART 135, IT WAS UNDER PART 91 FLIGHT WHEN INCIDENT OCCURRED. PILOT STATEMENT "ENROUTE, AS WE	 CRESTED THEMOUNTAINS, THE ENGINE STARTED SPUTTERING, AND RPMS WERE DROPPING. APPLIED CARB HEAT, TRIED SWITCHING BETWEE	N FUEL TANKS, MAGNETOS, AND THE RPMS KEPT DROPPING.  WE THEN WENT THROUGH THE FORMAL CHECK LIST TO NO AVAIL. THE DECISIO	N WAS MADE TO LAND AT RADAR FACILITY.  BY THIS TIME THE ENGINE HAD STOPPED. WE MADE THE EMERGENCY LANDING AT THE FACILIT	Y AND CAME TO A FULL STOP. DURING THE DESCENT, TRIED STARTING THE ENGINE MULTIPLE TIME, BUT IT DIDNT START. NO ONE WAS 	INJURED AND THE PLANE WAS NOT DAMAGED.	1	H	7	1 	3O	3	O	NT	3A12    	E253				 
	20081007		CE  	2008	10	7	2008FA0000636    	1	20080910	G	3233	20410202	PIVOT ASSY      			CESSNA	177   	177RG       	2073709	CE  										MLG ACTUATOR	SHEARED         	B			H5GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	7503V	4800 				177RG0802				PILOT COULDNT OBTAIN GEAR DOWN INDICATION AFTER EXTENDING GEAR. JACKED AC AND FOUND MAIN GEAR WOULDNT COMPLETELY ENTER	 DOWN-AND-LOCKED POSITION. FOUND MAIN GEAR RETRACT ACTUATOR REAR MOUNTING/ PIVOT PIN HAD ONE SIDE COMPLETELY SHEARED. TH	IS ALLOWED/CAUSED THE TUBULAR MOUNT STRUCTURE TO FLEX FROM SIDE TO SIDE AND CRACK MOST OF THE WAY THROUGH. (K)				1	H	7	1 	3O				A20CE   					 
	20081007		SO  	2008	10	7	2008FA0000637    	1	20080902	G	5510	510229615	ANGLE           			AMRGEN	AA5   	AA5B        	3960105	SO  										HORIZONTAL STAB	CRACKED         	B			H5GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	28665	4640 				AA5B0739				MAINT NOTICED A CLICKING NOISE AND EXCESSIVE MOVEMENT WHEN APPLYING UP AND DOWN PRESSURE TO HORIZONTAL STABILIZER TIPS. 	FOUND DELAMINATION, CRACKS AND WRINKLES IN HORIZONTAL STAB FWD SPAR CARRY-THROUGH ATTACH ANGLES INSIDE EMPENNAGE. WE BEL	IEVE THE SINGLE MOST CAUSE TO BE PILOTS AND MAINT PUSHING DOWN ON THE FWD SSPAR AREA TO RAISE THE NOSEWHEEL OFF THE GROU	ND. (K)			1	L	7	1 	3O				A16EA   					 
	20081007		SO  	2008	10	7	2008FA0000638    	1	20080902	G	5510	510229616	ANGLE           			AMRGEN	AA5   	AA5B        	3960105	SO  										HORIZONTAL STAB	CRACKED         	B			H5GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	28665	4640 				AA5B0739				MAINT NOTICED A CLICKING NOISE AND EXCESSIVE MOVEMENT WHEN APPLYING UP AND DOWN PRESSURE TO HORIZONTAL STABILIZER TIPS. 	 FOUND DELAMINATION, CRACKS, AND WRINKLES IN HORIZONTAL STAB FORWARD SPAR CARRY-THROUGH ATTACH ANGLES INSIDE EMPENNAGE. 	 WE BELIEVE THE SINGLE-MOST CAUSE TO BE PILOTS AND MAINTENANCE PUSHING DOWN ON THE FWD SPAR AREA TO RAISE THE NOSEWHEEL 	OFF THE GROUND. (K)			1	L	7	1 	3O				A16EA   					 
	20080930		GL  	2008	9	30	2008FA0000639    	1	20080902	G	5753	13431003	HINGE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					TE FLAPS	CORRODED        	B			ACOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	121HC	724  				0277				FLAP HINGES IN ALL POSITIONS BOTH LT AND RT HAVE INTERGRANDULAR CORROSION NEAR THE POINT OF FAILURE. PN 13431-003,  PN 1	3431-004, 13432-002, QTY 2, 13433-006, 13433-005.  CONDITION WAS FOUND AT ANNUAL INSPECTION. (K)					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
	20081007		SO  	2008	10	7	2008FA0000640    	2	20080801	G	7414	M3215	BRUSHES         			COLUMB	LC41  	LC41550FG400	5150011	NM  	CONT  	O550  	TSIO550C    		SO  					MAGENTO	WORN            	B			BIER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	623TS	243  				41668	914471			DETECTED NUMEROUS MAGNETOS WITH CARBON BLOCKS AND COILS TABS THAT ARE PREMATURELY WEARING OUT IN MAGNETO PN 6320. HAVE H	AD CUSTOMERS WITH MAGNETO FAILURES AS EARLY AS 5.5 HOURS ON THEIR NEW MAGNETOS. EVEN THOUGH MFG HAS IDENTIFIED THIS ISSU	E AND PUT OUT GUIDANCE TO INSPECT MAGNETOS WITHIN THE NEXT 50 HOURS OF OPERATION AS OF MAY 2, 2008, THIS ISSUE IS A MAJO	R CONCERN TO ALL CUSTOMERS DUE TO THE PERFORMANCE ISSUES THEY HAVE EXPERIENCED WITH THESE MAGNETOS AND THE ADDITIONAL DO	WN-TIME OF THE AC DUE TO THE FREQUENT INSP REQUIRED (EVERY 100 HRS). MFG NEEDS TO RESOLVE THEIR PRODUCT DEFICIENCY IMMED	IATELY AND THE ANSWER SHOULDNT BE THE CUSTOMERS BEAR THE COST OF REPLACEMENT OR THE ADDED COST OF FREQUENT INSPECTIONS.	1	L	7	1 	3O	3	O	NT	A00003SE	E5SO				 
	20081007		EU  	2008	10	7	2008FA0000641    	1	20080917	G	3230	A223801	SWITCH          			AMD   	FALC20	FALCON20C5  	2730107	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					MLG	INOPERATIVE     	B			DJSR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	23	531FL		2389 			113	P95155C			LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K)						2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
	20081007		EU  	2008	10	7	2008FA0000642    	1	20080919	G	3230	123371	CONTROL SWITCH  			AMD   	FALC20	FALCON20C5  	2730107	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					MLG	INOPERATIVE     	B			DJSR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	23	531FL		2389 			113	P95155C			LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF.  (K)						2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
	20081003		NM  	2008	10	3	2008FA0000643    	1	20080918	G	8011	6420871A7	ADAPTER         			COLUMB	LC42  	LC42550FG350	5150012	NM  	CONT  	O550  	IO550N      	17042	SO  					STARTER	FAILED          	B			BIER	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	21	964SG					42518	689029			OWNER/OPERATOR COMPLAINS THAT HIS ENGINE USES EXCESSIVE OIL OVER SHORT AND LONG FLIGHTS, SOME TIME AS MUCH AS (2) QUARTS	  IN LESS THAN A 2 HOUR FLIGHT.  REPLACED STARTER ADAPTER ASSY WITH NEW PART FROM MFG AND PROBLEM STILL OCCURS WITH OIL 	BEING PUMPED TO THE OIL SEPERATOR DURING THE GROUND ENGINE RUN. A COPY OF FAA FORM 8130-3 AND SHIPPING DOCUMENTS ARE ATT	ACHED TO THIS SDR WITH ADDITIONAL INFORMATION. (K)			1	L	7	1 	3O	3	O	NT	A00003SE	E3SO				 
	20081003		GL  	2008	10	3	2008FA0000644    	3	20080918	G	6111	A66315A	CLAMP           													HARTZL	HCA2	HCA2MVK2    	GL  	PROPELLER BLADE	BROKEN          	B			ME4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	C6BH4		1873 					H138		BLADE CLAMP FOUND TO BE CRACKED DURING MAGNETIC PARTICLE INSPECTION. CRACK IS LOCATED IN REAR HALF EXTENDING FROM THE A-	321 OUTER BOLT HOLE TO THE INSIDE OF THE CLAMP. DURING TEARDOWN INSPECTION, A-321 BOLT REMOVED FROM THIS CLAMP WAS BROKE	N IN HALF.  (K)														5	C	P24EA	 
	20081003		GL  	2008	10	3	2008FA0000645    	3	20080918	G	6111	A321	BOLT            													HARTZL	HCA2	HCA2MVK2    	GL  	BLADE CLAMP	BROKEN          	B			ME4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19								H138		A-321 CLAMP BOLT WAS FOUND TO BE BROKEN DURING TEARDOWN INSPECTION. BOLT IS CRACKED IN (2) PIECES APPROXIMATELY .5 THE L	ENGTH DOWN THE TREADED AREA. CLAMP THAT IT WAS ATTACHED TO WAS LATER FOUND TO BE CRACKED DURING MAG PARTICLE INSPECTION.	 (K)														5	C	P24EA	 
	20081008		SW  	2008	10	8	2008FA0000646    	1	20080901	G	6210	407015001111	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	B			UOHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	407LG					53143				M/R BLADE HAS 2706.0 HRS TT WHEN CLEANING BLADE FOR REINSTALLATION, MANY SHALLOW CRACKS WERE FOUND ON THE TOP SURFACE OF	 BLADE 24 INCH IB OF TRIM TAB. THE CRACKS RUN 45 DEGREES TO BLADE SPAN. CONTACTED MFG PRODUCT SUPPORT AND WAS INFORMED T	HAT THIS CONDITION IS CALLED "TRACER STRANDS" AND IS A CONDITION NEEDING REPAIR. PRODUCT SUPPORT ALSO INFORMED US THAT T	HIS WOULD BE REFERENCED INT THE MANUALS IN THE NEAR FUTURE AND THAT NEWER BLADES HAVE BEEN CORRECTED FOR THIS PROBLEM. (	K)		1	G	7	1 	3U			O	H2SW    					 
	20081008		EA  	2008	10	8	2008FA0000647    	1	20080912	G	5347	SH670RPA0045	SEAT TRACK      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF34*       	30015	NE  					FS 424-513	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	636BR					7307				LT FLOOR SEAT TRACK AT FS 424.0-513.0 FOUND TO BE CORRODED BEYOND LIMITS.  REMOVED AND REPLACED SEAT TRACK IAW SRM 51-41	-00. (K)					2	L	7	2 	4F	4	F	RT	A21EA   					 
	20081008		EA  	2008	10	8	2008FA0000648    	1	20080912	G	5347	SH670RPA0045	SEAT TRACK      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										FS 409	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	636BR					7307				LT FLOOR SEAT TRACK AT FS 409.00+16-409.00+128 FOUND TO BE CORRODED BEYOND LIMITS. REMOVED AND REPLACED SEAT TRACK IAW S	RM 51-41-00.  (K)					2	L	7	2 	4F			RT	A21EA   					 
	20081008		EA  	2008	10	8	2008FA0000649    	2	20080922	G	7414	7710398	MAGNETO         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					LEFT	SEIZED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	13	712TT		643  			17275235	L1173239A			DURING FLIGHT, A SHUDDER AND SLIGHT LOSS OF POWER WAS REPORTED BY THE PILOT. PRIOR TO THE NEXT FLT DURING THE MAGNETO CH	ECK IT WAS DISCOVERED THAT THE LT MAGNETO WAS INOPERATIVE. FURTHER INVESTIGATION FOUND THE LT MAGNETO CONDENSER WAS OUT 	OF THE MAGNETO CASE AND THE MOUNT FLANGE WAS BROKEN. THE MAGNETO HAD SEIZED, CAUSING THE CASE TO BREAK FREE OF THE ENGIN	E. THE INTERNAL PARTS MELTED AND DESTROYED.  INSP OF THE INSIDE OF THE ENGINE DRIVE GEARS AND CASE DID NOT REVEAL ANY DA	MAGE. OIL WAS DRAINED AND INLET SCREEN CHECKED WITH NO METAL FOUND. THE MAGNETO WAS REPLACED. ACCORDING TO THE LOGBOOKS,	 THE REMOVED MAGNETO HAD BEEN OVERHAULED AND INSTALLED AT ENGINE OVERHAUL ON 6/30/08 WITH NO INDICATION OF FURTHER MAINT	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081008		CE  	2008	10	8	2008FA0000650    	1	20080905	G	5320	45A336065	BRACKET         			BEECH 	MU300 	400A        	1155402	CE  										FUSELAGE	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	95GK	8304 				RK27				DURING SCHEDULED AIRFRAME INSPECTION FOUND PN 45A33606-5 AND PN 45A33606-6 CABIN UNDER FLOOR REINFORCING BRACKETS AT CAB	IN DOOR ENTRANCEWAY CRACKED. SEE SRM 53-10-50-001, FIG 1, SHEET 2 OR 3, ITEMS 29 AND 30.  SUSPECT CRACKED FROM FATIGUE, 	ALSO POSSIBLY FROM PREVIOUS ROUGH CABIN DOOR STEP ASSY HANDLING. AC TECHNICIANS/ INSPECTORS SHOULD INSPECT THIS AREA CAR	EFULLY DURING SCHEDULED INSPECTIONS ON HIGHER TIME AIRCRAFT, AND/OR AIRCRAFT WITH PREVIOUS HISTORY OPERATED BY CHARTER/A	IR TAXI/ FRACTIONAL OPERATORS. (K)		2	H	7	2 	4F			RT	A16SW   					 
	20081008		SO  	2008	10	8	2008FA0000651    	1	20080828	G	5343	67054803	TRUNNION        			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	27GS					28R7737160				AIRCRAFT CAME IN FOR HARD STARTING. WHILE REMOVING LOWER COWL, TO ACCESS LOWER SPARK PLUGS, TECH NOTICED THE NOSE LANDIN	G GEAR TRUNNION CRACKED WHERE DRAG BRACE ATTACHES TO IT. (K)					1	L	7	1 	3O	3	O		2A13    	1E10				 
	20081008		NE  	2008	10	8	2008FA0000652    	2	20080822	G	8500		ENGINE          			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340*      	52016	NE  						STOPPED         	D				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SW	03	2391Z					3010452	12403			ENGINE QUIT IN MID-AIR. ENGINE HAD 1195.0 HOURS SINCE MAJOR OVERHAUL. (K)						1	L	7	1 	3R	3	R		A9SW    	5E2				 
	20081008		EA  	2008	10	8	2008FA0000653    	1	20080816	G	5347		SEAT TRACK      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										BS 409-559	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	636BR					7307				(3) SEAT TRACK SECTIONS WERE FOUND TO BE CORRODED BEYOND LIMITS DURING AN INSPECTION AT WL 79.50 - FS 409.0+12 TO FS559.	0 RT SIDE, WL 72.50 - FS 409.0+12 TO 559.0 RT SIDE, WL 79.50 - FS409.0+12 TO FS559.0 LT SIDE. (K)					2	L	7	2 	4F			RT	A21EA   					 
	20081008		EA  	2008	10	8	2008FA0000654    	2	20080723	G	8530	HIO360F1AD	CYLINDER HEAD   			ENSTRM	F28   	F28F        	3300412	GL  	LYC   	O360  	HIO360*     	41514	EA  					ENGINE	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	8626E					744				DURING CYLINDER OVERHAUL A DAMAGE SEAT POCKET CUTTER USE USED. THIS RESULTED IN A VALVE SEAT POCKET THAT MEASURED WITHIN	 LIMITS BUT LACKED THE PROPER SURFACE CONTACT. AFTER APPROXIMATELY 3 HOURS OF ENGINE OPERATION, THE VALVE SEAT CAME OUT 	CAUSING THE INTAKE VALVE TO BREAK. THIS CAUSED A LOSS OF ENGINE POWER AND THE HELICOPTER MADE A HARD LANDING.  HELICOPTE	R WAS DESTROYED BY FIRE. (K)			1	G	7	1 	3O	3	O		H1CE    	1E10				 
	20081006		WP  	2008	10	6	2008FA0000655    	1	20080921	G	7810	C1691	MUFFLER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	3203D	200  				11598				MUFFLER WAS HEAT BLISTERED AND CRACKED AT TAIL PIPE TRANSITION. COLLECTOR WAS BURNED THRU UNDER CLAMP AT NR 1 CYLINDER, 	ALSO HEAT BLISTERED. (K)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081008		WP  	2008	10	8	2008FA0000656    	1	20080921	G	7820	C1691	MUFFLER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540*      	41532	EA  					EXHAUST	BULGED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	510KJ	799  				10338				MUFFLER FOUND - BULGED - BLISTERED AND HEAT CRACKED AT TAILPIPE TRANSITION. (K)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081006		CE  	2008	10	6	2008FA0000657    	1	20080919	G	7810	265202231	COWLING         			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  					EXHAUST	CRACKED         	B			MT9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	9653F					20800114	PCE17260			THE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET.	 (K)					1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
	20081008		SO  	2008	10	8	2008FA0000658    	1	20080901	G	5711	6707002	SPAR            			PIPER 	PA28  	PA28R200    	7102811	SO  										LT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13										LT WING SPAR CRACKED IN THE AREA OF WHERE THE PIVOT BLOCK IS INSTALLED. (K)						1	L	7	1 	3O				2A13    					 
	20081008		CE  	2008	10	8	2008FA0000659    	1	20080916	G	2520	71500	SEAT            			BBAVIA	8     	8KCAB       	2110612	CE  										CABIN	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	7698S					26276				REAR SEAT PN 7-1500 FAILED AT THE LT HINGE POINT. THE AN3 SERIES BOLT PULLED THRU THE HINGE LUGS WHICH ARE WELDED TO THE	 SEAT FRAME BOTTOM. THE RT HINGE HOLES SHOW ELONGATION, BUT REMAINED INTACT. THE AC WAS DOING SPIN TRAINING AT THE TIME 	OF THE INCIDENT. RECOMMEND THAT THE SEAT FRAME BE MODIFIED TO CURRENT STANDARDS INSTALLED ON NEWER AC. (K)				1	H	7	1 	3O				A21CE   					 
	20081008		SO  	2008	10	8	2008FA0000660    	2	20080917	G	7414	10357174	CONTACT         			BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  					RT MAGNETO	FAILED          	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	01	4998B	34   			F159517DR	D4516	33951			RT MAGNETO FAILED COMPLETELY IN FLIGHT DUE TO THE TIP OF THE CONTACT POINTS HAVING SEPARATED FROM HE ASSY.  THIS LEFT TH	E CONTACTS AND THEREFORE PRIMARY ELECTRICAL CIRCUIT IN A CONTINUALLY OPEN POSITION. RENDERING THE MAGNETO INOPERATIVE.  	IN A PHONE CONVERSATION WITH THE MFG REP, MFG IS AWARE OF THE POTENTIAL CONDITION AND HAD ISSUED A DISTRIBUTOR INFORMATI	ON BULLETIN D1B2008-3. RECALLING CONTACT ASSY AT THE DISTRIBUTOR LEVEL MFG WITH DATE CODES OF 0716-0816 OR THE (16) WEEK	 OF 2007 TO THE (16) WEEK OF 2008.  THE CONTACTS THAT WERE INSTALLED IN THIS MAGNETO IN MAY OF2008 DURING A ROUTINE 500 	HR INSP, HAD APPARENTLY MADE THEIR WAY INTO THE RETAIL INVENTORY SYS.  (K)	1	L	7	1 	3O	3	O		A777    	E267				 
	20081008		GL  	2008	10	8	2008FA0000661    	1	20080917	G	8011		CASTING         			DIAMON	DA40  	DA40        	2990002	GL  	CONT  	IO360 	IO360*      	17025	CE  					STARTER	BROKEN          	B			MZER	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	15	273DS				F4L08012	40954	L3417151E			CUSTOMER ATTEMPTED TO START ENGINE. WHILE CRANKING ENGINE, CUSTOMER REPORTED A LOUD "CLUNK" AND THE PROPELLER STOPPED RO	TATING. INVESTIGATED PROBLEM AND FOUND THE STARTER DRIVE CASTING BROKE FROM STARTER MOTOR. THE CASTING INCLUDED A BEARIN	G FOR THE STARTER DRIVE SHAFT. SHAFT AND BENDIX GEAR WAS STILL ATTACHED TO THE STARTER MOTOR. (K)				1	L	7	1 	3O	3	O	NT	A47CE   	E1CE				 
	20081008		CE  	2008	10	8	2008FA0000662    	1	20080922	G	2810		SEAL            			RAYTHN	390   	390         	7150030	CE  	WILINT	FJ44  	FJ442A      		GL  					FUEL CAP	DISLODGED       	W				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			EA	35	390EU					RB242				PRESSURE REFUELING CONNECTION CAP FOUND WITH SEALING RING DISLODGED AND HOLDING THE CHECK VALVE OPEN WHEN THE CAP IS INS	TALLED. FUEL LEAKING FROM CAP CAUSING FUEL TO FLOW FROM IT UP THE SIDE OF THE AIRCRAFT. THE FUEL FLOWING UP THE OUTSIDE 	OF THE AIRCRAFT HAS BEEN DRAWN INTO THE REAR MAINTENANCE BAY BY DIFFERENTIAL PRESSURE AT THE GROUND POWER SOCKET AND SPR	AYED OVER FLYING CONTROL CABLES AND ELECTRICAL EQUIPMENT IN THE MAINT BAY AND TAILCONE, THE DE-ICE CONTROL UNIT, STROBE 	POWER SUPPLY, PITCH TRIM COMPUTER, COCKPIT VOICE RECORDER AND MAIN POWER DISTRIBUTION AND RELAY BOX ARE ALL CONTAMINATED	.	1	L	7	2 	3F	4	F	RT	A00010WI	E3GL				 
	20081006		NE  	2008	10	6	2008FA0000663    	2	20080826	G	7314	50466	PUMP            			RKWELL	NA265 	NA26560     	7630106	CE  	PWA   	JT12  	JT12A8      	52042	NE  					LT ENGINE FUEL	WORN            	C			UVVR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CE	03	XCCAM	6367 	632  			306145	P689751			AFTER TAKEOFF THE PILOT COULD NOT ADJUST THE LT ENGINE POWER OUTPUT. ENGINE REMAINED AT TAKEOFF POWER WHILE POWER LEVER 	WAS RETARDED TO IDLE.  PILOT RETURNED TO AIRPORT AND SUCCESSFULLY SHUTDOWN THE LT ENGINE BY PLACING POWER LEVER TO CUT-O	FF POSITION AND MADE AN UNEVENTFUL LANDING. FUEL CONTROL, PN 706633, SN 55832 WAS REMOVED FROM THE ENGINE DRIVEN FUEL PU	MP AND WAS FOUND THAT THE FUEL CONTROL DRIVE SHAFT REMAINED ENGAGED IN FUEL CONTROL DRIVE SPLINE ON THE FUEL PUMP.  FURT	HER INSPECTION OF FUEL CONTROL UNIT REVEALED THAT THE FUEL CONTROL DRIVE SHAFT RETAINER PLATE HAD WORN COMPLETELY THROUG	H AND ALLOWED DISENGAGEMENT OF FUEL CONTROL DRIVE SHAFT FROM FUEL CONTROL UNIT. FUEL PUMP, PN 50466, SN 3ACF34 WAS INSPE	2	L	7	2 	4J	4	J	RT	A2WE    	1E9				 
	20081015		SO  	2008	10	15	2008FA0000665    	1	20081006	G	2460	454668	CIRCUIT BREAKER 			PIPER 	PA28  	PA28161     	7102803	SO  										COCKPIT	FAILED          	B				K				NONE                    				H	G		ELECT. POWER LOSS-50 PC   	MULTIPLE FAILURE          		NR	NOT REPORTED   	1			CE	05	8325T	6923 				288116134				FIVE CIRCUIT BREAKERS FAILED INTERMITTENTLY.  THE FAILED CIRCUIT BREAKERS WERE ALL RATED AT 5 AMPS, PIPER P/N 454668, DA	TE CODE 7903.  THE FIVE CIRCUITS AFFECTED WERE; ENGINE GAUGES, TURN COORDINATOR, INSTRUMENT PANEL LIGHTS, OVERHEAD LIGHT	S AND RADIO LIGHTS.				1	L	7	1 	3O				2A13    					 
	20081015		CE  	2008	10	15	2008FA0000666    	1	20080910	G	5542	5533000095	SKIN            			CESSNA	500   	560CESSNA   	2076750	CE  										RUDDER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	905LC	7599 				5600334				THE LOWER FORWARD RUDDER SKIN IS CRACKED 2.5 INCHES, THIS WAS FOUND DURING ROUTINE PHASE INSPECTIONS.  THE RUDDER SKIN P	ART NUMBER IS 5533000-95.  THIS IS THE THIRD CRACK FOUND IN THE SAME LOCATION ON THE SAME MODEL AIRPLANE THIS CALENDER Y	EAR.				2	L	7	2 	4F			RT	A22CE   					 
	20081015		CE  	2008	10	15	2008FA0000667    	1	20081007	G	5610	6656100000009	WINDSHIELD      			LEAR  	45    	45LEAR      	5170805	CE  										COCKPIT	CRACKED         	E				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	13	241LJ	1778 				241				AIRCRAFT DEPARTED LAX PASSING THROUGH 18000 FT CREW HEARD A POP AND PILOT'S WINDSHIELD OUTER PLY CRACKED.  CREW DECLARED	 EMERGENCY AND RETURNED TO LAX.  LANDING WAS UNEVENTFUL.  INSPECTION OF WINDSHIELD BY STANDARD AERO - LAX FOUND OUTER PL	Y WINDSHIELD HAD FAILED.  STANDARD AERO - LAX CURRENTLY REPLACING WINDSHIELD WITH NEW.				2	L	7	2 	4F			RT	T00008WI					 
	20081015		NE  	2008	10	15	2008FA0000668    	2	20081003	G	8530	66713	GUIDE           	LYC         		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	UNDERSIZE       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	99	4126A	464  				12096	L3247448E			MOMENTARY SEVERE VIBRATION, POWER LOSS AND ENGINE RPM DROP OCCURRED IN-FLIGHT THEN RETURNED TO NORMAL.  COMPRESSION CHEC	K (COLD) REVEALED STUCK INTAKE VALVE ON NR 6 CYL.  INTAKE VALVE GUIDE ID MEASURED .4035" (UNDERSIZED).  LIMITS .4040 / .	4050.  NO BUILDUP FOUND ON VALVE GUIDE OR STEM.  VALVE GUIDE REAMED TO PROPER SIZE PER LYC.  TABLE OF LIMITS SSP1776.  N	O REOCCURRENCE REPORTED.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081017		CE  	2008	10	17	2008FA0000669    	1	20081002	G	2752	232507911	ATTACH BRACKET  			LEAR  	35    	35A         	5170602	CE  										T/E FLAP	CRACKED         	B			AJCA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	308BW	9341 	600  			438				DURING 600 HOUR INSPECTION FOUND TWO SHEARED ALUMINUM RIVETS, ALONG WITH A 0NE INCH CRACK IN LT FLAP ACTUATOR ATTACHMENT	 BRACKET, P/N 2325079-11.  INSTALLED NEW BRACKET ASSEMBLY, P/N 2325079-17.  THIS BRACKET HAS TWO STEEL RIVETS IN PLACE O	F THE ORIGINAL ALUM RIVETS.				2	L	7	2 	4F				A10CE   					 
	20081016		CE  	2008	10	16	2008FA0000671    	1	20080924	G	2797	CC75LA61	WIRE HARNESS    			CESSNA	208   	208B        	2073701	CE  										FLAP SYSTEM	CHAFED          	B			MT9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	9738B	11206				208B0097				TIE WRAP WAS MISSING FROM THE CLAMP AT FS 201.50, WHICH ALLOWED THE WIRING BUNDLE CONTAINING THE WIRES FOR THE FLAP SYS 	PRIMARY MOTOR TO SAG AND CHAFE THROUGH WIRE NR CC75 TO THE FLAP SYSTEM AND PARTIALLY THROUGH LA61 TO THE CARGO AREA LIGH	TS ON THE BULKHEAD.  THIS CAUSED THE FLAPS TO ONLY RECEIVE POWER TO THE PRIMARY MOTOR IN ONE DIRECTION.  SINCE WIRE LA61	 WASN`T CHAFFED COMPLETELY THROUGH THE CARGO AREA LIGHTS WERE STILL WORKING.  (K)			1	H	7	1 	3T				A37CE   					 
	20081016		CE  	2008	10	16	2008FA0000672    	1	20080926	G	5340	65651285	CHANNEL         			CESSNA	500   	560CESSNA   	2076750	CE  										CABLE PULLEY	MISLOCATED      	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	809QS					5600698				DURING PHASE 5 INSP, FOUND ELEVATOR TRIM CABLE CONTACTING ELEVATOR SELECTOR DRIVE CHAIN.  FOUND THE TRIM CABLE PULLEY CH	ANNEL BRACKET MIS-LOCATED.  ORDERED NEW CHANNEL BRACKET AND RELOCATED PULLEY TO CLEAR SECTOR DRIVE CHAIN.  (K)					2	L	7	2 	4F			RT	A22CE   					 
	20081015		CE  	2008	10	15	2008FA0000673    	1	20080924	G	5350	671261713	FRAME           			CESSNA	750   	750         	2076810	CE  										TAIL CONE	CRACKED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	960QS					7500160				DURING ROUTINE INSP, FOUND FWD FRAME PN 6712617-13 CRACKED IN (2) LOCATIONS, ON THE TOP LT AND RT SIDES.  ALSO FOUND FRA	ME AFT OF THIS ONE CRACKED.  PN 6712617-14 ON THE TOP RT SIDE.  (K)					2	L	7	2 	4J			RT	T00007WI					 
	20081015		CE  	2008	10	15	2008FA0000674    	1	20080924	G	5350	671261713	FRAME           			CESSNA	750   	750         	2076810	CE  										TAIL CONE	CRACKED         	E			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	978QS					7500187				DURING ROUTINE INSP FOUND FWD FRAME PN 6712617-13 CRACKED. THE CRACKED FRAME WAS LOCATED IN THE UPPER LT SIDE UNDER THE 	RUDDER TO STINGER FAIRING.  (K)					2	L	7	2 	4J			RT	T00007WI					 
	20081016		CE  	2008	10	16	2008FA0000675    	1	20080908	G	2731	666000134	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TRIM	BROKEN          	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	641QS					5605295				DURING ROUTINE INSP, FOUND BROKEN STRANDS ON ELEVATOR TRIM CABLE ASSY PN 666000134.  DAMAGE FOUND WHERE CABLE PASSES THR	OUGH A SERIES OF "S" PULLEYS.  (K)					2	L	7	2 	4F			RT	A22CE   					 
	20081016		CE  	2008	10	16	2008FA0000676    	1	20080908	G	2731	666000134	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  										TAIL	BROKEN          	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	627QS					5605227				DURING ROUTINE INSP, FOUND CABLE STRANDS BROKEN AND FRAMED.  THE DAMAGED AREA OF THE CABLE IS WHERE IT GOES OVER A SERIE	S OF "S" PULLEYS MOUNTED IN THE HORIZ STAB.  SHOULD MAKE THIS A TIME CHANGE ITEM.  (K)					2	L	7	2 	4F			RT	A22CE   					 
	20081016			2008	10	16	2008FA0000677    	4	20080930	G	2562	AK451	ELT             			PIPER 	PA34  	PA34200T    	7103406	SO  										CABIN	FAILED          	B			BIER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2190K					347970096				ELT EMERGENCY LOCATOR TRANSMITTER WILL NOT TEST PROPERLY ON A CONSISTENT BASIS BY DISPLAYING CORRECT 3-DIGIT COUNTRY COD	E OR 15 DIGIT HEX ID CODE.  THIS ELT HAS BEEN TESTED WITH (2) DIFFERENT 406 MHZ TESTERS DISTRIBUTED BY PN 453-1000 AND P	N 453-0131 (MEASURE MODEL MEZ 1000 AND PSION ORGANIZER II MODEL LZ64) AND THE PERFORMANCE OF THE 451 ELT HAS BEEN UNSATI	SFACTORY.  INCONSISTENT RESULTS INCLUDED A DIFFERENT COUNTRY CODE DISPLAYED (305) RATHER THAN CODE 369 OR 366 FOR THE US	A AND DIFFERENT 15 DIGIT HEX ID CODE OF 26273300A5FF7FE RATHER THAN THE ACTUAL CODE FOR THE UNIT BEING TESTED (2E285980E	4FFBFF). RAN ADDITIONAL TESTS DUE TO THE INCONSISTENT RESULTS AND THE UNIT FAILED TO OPERATE PROPERLY.  UNIT WAS REPLACE	1	L	7	2 	3O				A7SO    					 
	20081015			2008	10	15	2008FA0000678    	4	20080930	G	2562	AK451	ELT             			PIPER 	PA34  	PA34200T    	7103406	SO  										CABIN	NO TEST         	B			BIER	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	21	2190K					347970096				ELT EMERGENCY LOCATOR TRANSMITTER WILL NOT TEST PROPERLY ON A CONSISTENT BASIS BY DISPLAYING CORRECT 3-DIGIT COUNTRY COD	E OR 15 DIGIT HEX ID CODE.  THIS ELT HAS BEEN TESTED WITH (2) DIFFERENT 406 MHZ TESTERS.  DISTRIBUTED, PN 453-1000 AND 4	53-0131 AND THE PERFORMANCE OF THE 451 ELT HAS BEEN UNSATISFACTORY.  INCONSISTENT RESULTS INCLUDED A DIFFERENT COUNTRY C	ODE DISPLAYED (305) RATHER THAN CODE 369 OR 366 FOR THE USA AND DIFFERENT 15 DIGITS HEX ID CODE OF 26273300A5FF7FE RATHE	R THAN THE ACTUAL CODE FOR THE UNIT BEING TESTED (2E28598052FFBFF). RAN ADDITIONAL TESTS DUE TO THE INCONSISTENT RESULTS	 AND THE UNIT FAILED TO OPERATE PROPERLY. UNIT WAS REPLACED BY ANOTHER ELT.  THE INCONSISTENT RESULTS WERE THE SAME.  (K	1	L	7	2 	3O				A7SO    					 
	20081016		NM  	2008	10	16	2008FA0000679    	1	20080829	G	2910	25W711008293	LINE            			ISRAEL	1125  	1125        	       	NM  										HYD RESERVOIR	CHAFED          	B			JGVR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	09	111EL					055				TROUBLESHOT HYDRAULIC SYS AND FOUND THE AUXILIARY HYDRAULIC SYS RETURN LINE THAT CONNECTS THE RETURN HYDRAULIC FILTER TO	T THE AUXILIARY HYDRAULIC TANK CHAFED, WHICH CAUSED A SLOW LEAK IN THE HYDRA SYS.  ACCOMPLISHMENT OF SB 1125-29-254 "HYD	RAULIC TUBE CLEARANCE" PROVIDES INSTRUCTIONS FOR A ONE TIME INSP OF THE CLEARANCE BETWEEN THE PRESSURE TUBE AND THE RETU	RN TUBE IN THE AREA OF THE HYDR AUXILIARY RESERVOIR. PROCEDURES ARE GIVEN TO ADJUST  OR REPLACE THE AFFECTED TUBE ASSEMB	LIES DEPENDENT UPON THE INSPECTION FINDINGS.  ACFT WAS REPAIRED BY REPLACEMENT OF AUXILIARY HYDRA RETURN TUBE PN 25W7110	08-293 AND ENSURING CLEARANCES WERE MET IAW THE ACCOMPLISHMENT INSTRUCTIONS OF SB 1125-29-254.  (K)	2	L	7	2 	4F			RT	A16NM   					 
	20081016		GL  	2008	10	16	2008FA0000680    	3	20080929	G	6110	A3204	SCREW           			PIPER 	PA32  	PA32300     	7103212	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP BLADE	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		200  						CH43680B		CUSTOMER COMPLAINED OF AN EXCESSIVELY LOOSE BLADE PRELOAD ON (1) BLADE 4 MONTHS AFTER OVERHAUL. INSP REVEALED EXCESSIVE 	WEAR ON END OF BLADE PRELOAD SCREWS CAUSING LOOSENESS OF BLADE. OPPOSITE SCREW WAS WORN ALSO BUT NOT TO EXTENT TO BE NOT	ICEABLE. SECOND OCCURRENCE OF THIS TYPE NOTICED.  INSPECTION OF NEW SCREWS IN STOCK REVEALED IRREGULAR END, IE NOT FLAT 	BUT ANGULAR.  REPLACED BOTH SCREWS AND RETURNED TO SERVICE.  (K)			1	L	7	1 	3O				A3SO    		5	C	P920	 
	20081028		SO  	2008	10	28	2008FA0000681    	2	20081014	G	8530	AEC631397	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					NR 1	CRACKED         	D				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			SW	99	6036	355  				E1422	296794R			AIRCRAFT OWNER REPORTED SEVERE VIBRATION. AFTER INSPECTION IT WAS FOUND THAT SPINNER BULKHEAD WAS SEVERELY CRACKED. AFTE	R FURTHER INSPECTION NR 1 CYLINDER WAS FOUND TO BE CRACKED ALL AROUND THE CIRCUMFERENCE OF THE CYLINDER DIAMETER.  THE C	RACK WAS RIGHT AT THE 9TH AND 10TH COOLING FINS.  THIS CYLINDER HAD A TOTAL TIME OF 355 HOURS SINCE NEW.  THIS CYLINDER,	 DUE TO IT'S IDENTIFICATION MARKINGS DID NOT APPLY TO AD 2004-8-10, HOWEVER IT DID APPLY TO ECI'S MSB 06-2 WHICH IDENTIF	IES THIS CYLINDER FOR INSPECTION FOR CRACKS.  THE AD 2004-8-10 SHOULD PROBABLY INCLUDE ALL CYLINDERS IN ECI'S MSB 06-2. 	 THE CONDITION WAS REPORTED IMMEDIATELY AFTER TAKEOFF AND THE PILOT RETURNED IMMEDIATELY TO THE AIRPORT AND LANDED UNEVE	1	L	7	1 	3O	3	O		3A15    	E3SO				 
	20081016		CE  	2008	10	16	2008FA0000682    	1	20080621	G	2720	05701051	CONTROL CABLE   			CESSNA	170   	170A        	2072304	CE  										RUDDER	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	9739A	6459 				19200				CABLE BROKE AFT OF REAR PULLEY AND BULKHEAD. NO INSPECTION HOLES IN THIS AREA.  (K)						1	H	7	1 	3O				A799    					 
	20081020		EU  	2008	10	20	2008FA0000683    	1	20080919	G	3210		LANDING GEAR    			AMD   	FALC20	FALCON20C5  	2730107	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  						FAILED          	B			DJSR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	23	531FL					113	P95155C			LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K)						2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
	20081020		EU  	2008	10	20	2008FA0000684    	1	20080917	G	3260	A223801	POSITION SWITCH 			AMD   	FALC20	FALCON20C5  	2730107	EU  										MLG	INOPERATIVE     	B			DJSR	A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			GL	23	531FL					113				LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. (K)						2	L	7	2 	4F			RT	A7EU    					 
	20081020		CE  	2008	10	20	2008FA0000685    	1	20080926	G	2697		WIRE            			LEAR  	45    	45LEAR      	5170805	CE  										FIRE DETECTION	CHAFED          	B			HMGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	45NM	1158 				253				APU FIRE DETECT CIRCUIT BREAKER POPPED ON RT COCKPIT CIRCUIT BREAKER PANEL DURING POWER UP OF AIRCRAFT.  TROUBLESHOT SYS	TEM FOUND WIRING CHAFED AT FUSELAGE STATION 614.210 AFT EQUIPMENT BAY UPPER AVIONICS SHELF SUPPORT ANGLE PN 4525708307. 	THE ANGLE DOES NOT HAVE ANY PROTECTION TO PREVENT CHAFING OF WIRING FROM THE FACTORY AND IT APPEARS THAT CLEARANCE IS NO	T GREAT ENOUGH TO KEEP THE WIRING FROM CHAFING.  HAVE NOTIFIED MFG TECH SUPPORT. (K)			2	L	7	2 	4F			RT	T00008WI					 
	20081020		CE  	2008	10	20	2008FA0000686    	1	20080929	G	2910	6317003136	LINE            			CESSNA	525   	525         	2076601	CE  										HYD SYSTEM	RUPTURED        	B			EWCR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	39	44CK	2416 				5250401				RUPTURE OF TUBE AT SIDE WHERE BENDING DIES LT MARKING BOTH ABOVE AND BELOW OPENING.  AFTER TAKEOFF, LOW FLUID AND PRESSU	RE WARNING LIGHTS CAME ON AND ACFT RETURNED TO AIRPORT. ACFT WAS TURNED OVER TO SERVICE CENTER.  LEAK WAS LOCATED AND TH	E LINE REPLACED ALONG WITH BOTH HYDRAULIC PUMPS.  (K)				1	L	7	2 	4F			RT	A1WI    					 
	20081020		EA  	2008	10	20	2008FA0000688    	2	20081001	G	7314	154739704	PUMP            			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					FUEL SYSTEM	CRACKED         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			FS	60	66419					18280132	L2616748A			PUMP HOUSING CRACKED ALONG SEAM.  POSSIBLE WEAK SPOT UPON MANUFACTURING.  (K)						1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
	20081028		CE  	2008	10	28	2008FA0000689    	1	20081003	G	2731	6660161156660161	PUSHROD         			CESSNA	560   	560XL       	2076702	CE  										ELEVATOR TAB	WORN            	C				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			NM	07	669TT	694  				5605684				ON RETURN FLIGHT TO HOME STATION, CREW COMPLAINED OF SLIGHT VIBRATION IN FLIGHT.  CREW FELT THE VIBRATION WAS ISOLATED T	O THE ELEVATOR CONTROL SYSTEM.  UPON PRELIMINARY INSPECTION OF THE ELEVATOR SYSTEM, FOUND BOTH ELEVATOR TRIM TABS PLAYS 	BEYOND THE TOLERANCE DEFINED IN 560XL AMM TASK 27-31-00 220.  REMOVED AND REPLACED PUSH RODS (P/N 6660161-15 AND 6660161	-17) ON BOTH ELEVATOR TRIM TABS IAW 560XL AMM 27-32-03 PARAGRAPH 4D(3)(A).  AIRCRAFT RETURNED TO SERVICE.  SUBSEQUENT FL	IGHT REVEALED NO FURTHER ISSUE.		2	L	7	2 	4F			RT	A22CE   					 
	20081028		SO  	2008	10	28	2008FA0000690    	2	20081017	G	8530	AEC631397	CYLINDER        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	414AN	654  				414A0819	813675R			UPON INSPECTION FOUND THAT NR 1 AND NR 5 CYLINDERS WERE CRACKED AND LEAKING FUEL ORIGINATING JUST INBOARD OF THE FUEL NO	ZZLE BETWEEN THE 16TH AND 18TH COOLING FINS.  CYLINDERS WERE NEW WHEN INSTALLED AT ENGINE OVERHAUL.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
	20081023			2008	10	23	2008FA0000693    	4	20080911	G	6122	210044	ROD             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					GOVERNOR	BROKEN          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	6681L					TH1088				LIFT ROD WAS DISCOVERED BROKEN AT DISASSEMBLY.  (K)						1	L	7	2 	3O	3	O		3A16    	E5CE				 
	20081023			2008	10	23	2008FA0000694    	4	20080911	G	6122	B20429	SPRING DRIVE    	MCAULY      							CONT  	O520  	IO520*      	17032	SO  					GOVERNOR	BROKEN          	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	CGFLM				790221					SPRING DRIVE DISCOVERED BROKEN AT DISASSEMBLY.  (K)											3	O			E5CE				 
	20081023		EA  	2008	10	23	2008FA0000695    	1	20080909	G	6120	B3476A2	ROD             	HARTZL      		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BETA SYSTEM	BROKEN          	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	V2LFC				BUA26256					BETA ROD CRACKED, BROKEN.  PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT.  MALF	UNCTION FOUND 3 HOURS FLIGHT TIME AFTER LOCAL REPAIR OF BLADE. (K)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081023		EA  	2008	10	23	2008FA0000696    	1	20080909	G	6120	B30012	BETA RING       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	BROKEN          	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	V2LFC							BUA26256		BETA RING CRACKED, BROKEN.  PROPELLER WAS INVOLVED IN PROP STRIKE AT MID STATION OF BLADE NR 2 BY A FOREIGN OBJECT.  MAL	FUNCTION FOUND 3 HOURS FLIGHT TIME  AFTER LOCAL REPAIR.  (K)					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081023		SO  	2008	10	23	2008FA0000697    	2	20080930	G	7414		SPRING          			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					IMPULSE COUPLING	BROKEN          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	21	622CP	4    			D08BA175	1932	360623			DURING MAGNETO CHECK ON GROUND RUN-UP 30 SEPT 2008, THE PILOT REPORTED THAT WHEN THE LT MAG WAS SELECTED THE ENGINE WOUL	D NOT STAY RUNNING. ACFT WAS BROUGHT IN FOR MAINT AND IT WAS DISCOVERED THAT THE MAGNETO IMPULSE COUPLING SPRING WAS BRO	KEN IN THE LEFT MAGNETO. THE LT MAGNETO WAS REMOVED AND REPLACED, GROUND RUN CHECK WAS GOOD, AND ACFT WAS RETURNED TO SE	RVICE. (K)			1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
	20081030		NM  	2008	10	30	2008FA0000698    	1	20081019	G	3510		VALVE           			BOEING	767   	7673CB      	1385187	NM  										OXYGEN BOTTLE	OUT OF ADJUST   	B				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	592HA					33468				AIR NEW ZEALAND FAA REPAIR STATION ANZY 188C  AKL - FLT NZ707 - DURING PRE-FLIGHT, TECH CREW NOTED THAT CREW OXY PRESSUR	E ON EICAS DROPPED FROM 1600 PSI TO APPROX 300 PSI WHILE DEPRESSING THE TEST BUTTONS ON THE CREW OXY MODULES.  ENGINEER 	CALLED ON HEADSET TO INVESTIGATE.  ENGINEER CHECKED CREW BOTTLE AND FOUND THAT THE VALVE WAS APPROX ONLY 1/3 OPEN AND NO	T SAFETY WIRED.  BOTTLE VALVE SUBSEQUENTLY FULLY OPENED AND COPPER WIRED IN POSITION AS REQUIRED.  CREW OXYGEN CHECKS NO	W NORMAL WITH NO NOTICEABLE DROP IN PRESSURE ON EICAS.  AIR NEW ZEALAND MAINTENANCE QUALITY RISK AND SAFETY (MQRS) SAFET	Y INVESTIGATION GROUP HAS RAISED THE FOLLOWING AIR NEW ZEALAND INVESTIGATION (08/SI/135).	2	L	7	2 	4F			RT	A1NM    					 
	20081027		CE  	2008	10	27	2008FA0000699    	1	20081010	G	5313	50440012319	STRINGER        			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6*        	52043	EA  					FS 298	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	902XP	5781 				LJ1136				REAR PRESSURE BULKHEAD, FS 298.00, ON RT SIDE. STRINGER NR 9 WAS FOUND CRACKED ON THE AFT SIDE OF THE REAR PRESSURE BULK	HEAD AT THE POINT WHERE THE ZEE STIFFENER IS ATTACHED TO THE STRINGER WITH (6) RIVETS. (K)					1	L	7	2 	3T	3	T		3A20    	E2NE				 
	20081027		NE  	2008	10	27	2008FA0000700    	3	20080718	G	6111	6607132886	BLADE           													ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		37586						DR6176385		PROP RECEIVED FOR ROUTINE O/H.  AFTER PROP WAS DISASSEMBLED IT WAS NOTED THAT BLADE NR 2, SN 1141 HAD A CRACKED ROOT END	 OUTER SLEEVE. BLADE IS REJECTED FROM FURTHER SERVICE. SB SF 340.60.A106 ADDRESSES THIS. (K)															6	C	P30NE	 
	20081027			2008	10	27	2008FA0000701    	4	20081006	G	2210	4006719910	SERVO           			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					YAW DAMPENER	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	544CB		46   			1536SA				8/11/08 INSTALLED YAW DAMPENER.  10/06/08 - CUSTOMER COMPLAINT OF INDUCED YAW WHEN ENGAGING AUTO PILOT. REMOVED YAW DAMP	ENER AND FOUND UNIT CONTAMINATED WITH WATER. UNIT IS MOUNTED WITH DRIVE SHAFT UP AND WITH NO DRAIN, THIS PROVIDES FOR WA	TER TO BE TRAPPED IN THE SERVO.  RECOMMEND SEALING THE UNIT BETTER OR PROVIDING DRAINS FOR UNIT.  (K)				1	H	7	2 	3T	3	T	RT	A10SW   	E2WE				 
	20081027		SO  	2008	10	27	2008FA0000702    	1	20081016	G	3210	6569100	TORQUE LINK     			PIPER 	J3    	J3C65       	7100510	SO  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	70127	5440 				17106				CRACK FOUND DURING 100 HR INSPECTION.  LAST INSPECTION FOR AD 72-08-06. DONE AT 5214.07 HR, PRESENT TIME 5440.53 (225.76	 HR).  SUGGEST PART BE LIFE LIMITED.  THIS IS 2ND SET CRACK. THIS FLEET WITH OVER 5000 HR. TIME IN SERVICE. (K)					1	H	7	1 	3O				A691    					 
	20081027		CE  	2008	10	27	2008FA0000703    	1	20081002	G	2730	NAS428420	BOLT            			BEECH 	200   	200BEECH    	1152920	CE  										ELEVATOR CONTROL	OUT OF ADJUST   	B			ML2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	124EK					BB1993				DURING A PHASE 1-4 INSPECTION ON AC. BOLT FOR ELEVATOR CONTROL SYS. WAS FOUND TO BE ADJUSTED ALL THE WAY DOWN AND WAS NO	T PROVIDING A STOP FOR THE  BALLAST. IN THIS CONDITION, THE POSSIBILITY EXISTS FOR THE INTERCONNECT LINK BETWEEN THE BAL	LAST WEIGHT BELLCRANK AND THE CONTROL COLUMN BRACKET TO TRAVEL PAST AN OVERCENTER CONFIGURATION AND MAY PREVENT PROPER C	ONTROL OF THE ELEVATOR SYSTEM IF THE ELEVATOR PRIMARY OR SECONDARY STOPS FAIL OR ARE ADJUSTED INCORRECTLY.  THE PHASE IN	SPECTION BEING CONDUCTED IS THE INITIAL INSPECTION ON THE AC, AND LOG RESEARCH DID NOT REVEAL ANY PRIOR MAINTENANCE ON T	HE ELEVATOR CONTROL SYSTEM RIGGING.  (K)	1	L	7	2 	4T				A24CE   					 
	20081030		NM  	2008	10	30	2008FA0000704    	1	20081024	G	5711	9252502	SPAR CAP        			LKHEED	P3A   	P3A         	5260103	NM  										RT WING	FRACTURED       	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	00	921AU	16842	1465 			151385				DURING INSPECTION TO DETERMINE THE SOURCE OF A FUEL LEAK A FRACTURE WAS FOUND IN THE LOWER FORWARD RIGHT SPAR CAP AT WIN	G STA 75 EMANATING FROM NUT PLATE FASTENER HOLE ON FORWARD FLANGE TO THE EDGE OF FLANGE MEMBER WITH SLIGHT ENCROACHMENT 	AFT FROM SAME HOLE, APPROX .125 INCH.  SECOND FRACTURE SHOWS AT WS 72.2 FROM FORWARD FLANGE NUT PLATE HOLE INTO THE VERT	ICAL FLANGE SEVERING THE FLANGE.  A THIRD FRACTURE WAS APPRECIATED AT WS 71R IN THE SPAR WEB.  THE CRACK APPEARS TO STAR	T AT A HI-LOK PIN HOLE AT THE LOWER CAP AND PROPAGATES APPROXIMATELY THREE INCHES VERTICAL WITH SOME INBOARD TRACK.		2	L	7	4 	4T			RT	A32NM   					 
	20081027		CE  	2008	10	27	2008FA0000705    	1	20080929	G	2910	6317003136	LINE            			CESSNA	525   	525         	2076601	CE  										HYDRAULIC SYS	RUPTURED        	B			EWCR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	44CK					5250401				RUPTURE OF TUBE AT SIDE WHERE BENDING DIES LEFT MARKING, BOTH ABOVE AND BELOW OPENING. AFTER TAKEOFF, LOW FLUID AND PRES	SURE WARNING LIGHTS CAME ON AND ACFT RETURNED TO DEPARTURE. ACFT WAS TURNED OVER TO REPAIR STATION.  LEAK WAS LOCATED AN	D LINE REPLACED ALONG WITH BOTH HYDRAULIC PUMPS. (K)				1	L	7	2 	4F			RT	A1WI    					 
	20081027		SO  	2008	10	27	2008FA0000706    	1	20081014	G	3246	16109302	WHEEL           			PIPER 	PA32  	PA32R300    	7103213	SO  										MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	1228H					32R7780146				WHEEL FOUND CRACKED, INNER HALF APPROX 2 INCH LONG.  (K)						1	L	7	1 	3O				A3SO    					 
	20081031		SO  	2008	10	31	2008FA0000707    	1	20081026	G	5712	9560401	SPAR CAP        			PIPER 	PA34  	PA34200     	7103405	SO  										RT WING	CORRODED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05	14258	4695 				347350180				DURING ANNUAL INSPECTION, SEVERE INNER GRANULAR CORROSION WAS FOUND IN THE RIGHT WING, MAIN UPPER SPAR CAP AT THE AFT PO	RTION OF THE T-CAP, IN THE VICINITY OF THE WHEEL WELL IN PARTICULAR THE LOCATION OF WHEEL SPIN OFF.  DURING TIME, CAUSED	 DAMAGE TO THE POINT OF SPAR REPLACEMENT.				1	L	7	2 	3O				A7SO    					 
	20081028		CE  	2008	10	28	2008FA0000708    	1	20080924	G	3010		LINE            			CESSNA	208   	208B        	2073701	CE  										DE-ICE SYSTEM	FROZEN          	D				K				NONE                    				N	L		FALSE WARNING             	NO TEST                   		IN	INSP/MAINT     	1			SO	03										DURING MX OPERATION OF DE-ICE BOOTS MINUTES AFTER ACFT RETURNED FROM FLT, OPERATION OF THE DEICE BOOTS PRODUCED NORMAL C	OCKPIT INDICATION (GREEN PRESSURE LIGHT). NOTICED, THOUGH, THAT THE RT WING DEICE BOOTS DID NOT INFLATE DESPITE THE INFL	ATION INDICATION IN THE COCKPIT. FROZEN WATER WAS FOUND AT A BEND IN THE DEICE AIR SUPPLY DUCTING IN THE RT WING ROOT. T	HIS ALLOWED PRESSURE TO BUILD UP AND ACTIVATE THE PRESSURE SWITCH, PRODUCING A NORMAL INDICATION IN THE COCKPIT DESPITE 	THE BOOTS NOT ACTUALLY INFLATING. IF THIS WERE TO OCCUR IN THE TAIL, IT WOULD BE EVEN MORE UNDETECTABLE. RECOMMEND A CAL	IBRATED LEAK IN PNEUMATIC SUPPLY DUCTING IN THE FUSELAGE/ WING TO PREVENT THE ACCUMULATION OF WATER. (K)	1	H	7	1 	3T				A37CE   					 
	20081028		SO  	2008	10	28	2008FA0000709    	1	20081014	G	3246	16109302	WHEEL           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	1228H					32R7780146				CLEVELAND WHEEL, HOLE FOUND CRACKED, INNER HALF APPROX 2 INCHES LONG. (K)						1	L	7	1 	3O	3	O		A3SO    	E14EA				 
	20081104		CE  	2008	11	4	2008FA0000710    	1	20081027	G	6120		TUBE            			BEECH 	95    	95B55       	1152729	CE  										NACELLE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	527T	4985 				TC576				ALUMINUM TUBING TO PROP GOVERNOR FOUND CHAFED DUE TO TIE RAP RUBBING TUBE.  FABRICATED NEW TUBE, INSTALLED AND LEAK CHEC	KED.					1	L	7	2 	3O			RT	3A16    					 
	20081104		GL  	2008	11	4	2008FA0000721    	2	20081027	G	7260	KHU17D31	RELAY           			CESSNA	206   	U206G       	2073356	CE  	ALLSN 	250C  	250C20      	03013	GL  	HARTZL	HCC3Y	HCC3YN      	GL  	ENGINE BAY	INTERMITTENT    	B				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			GL	19	891LL	4565 				U20606937	CAE290031	GC91A		THE PILOT REPORTED THAT AFTER TURNING ON TO THE RUNWAY FOR TAKEOFF AND APPLYING POWER THE ENGINE CHIP LIGHT CAME ON AND 	STAYED ON.  POWER WAS REDUCED, AND TOWER APPROVED A RETURN BACK TO THE RAMP.  THE AIRCRAFT NEVER APPROACED TAKEOFF SPEED	.  THE AIRCRAFT WAS BROUGHT IN AND INSPECTED, UPON APPLYING ELEC POWER TO AIRCRAFT THE CHIP LIGHT WAS NO LONGER ON.  ALL	 THREE CHIP LIGHTS WERE INSPECTED AND FOUND NO DISCREPANCIES.  SUSPECTED WIRING PROBLEM OR RELAY PROBLEM.  REPLACED RELA	Y FOR THE CHIP DETECTORS.		1	H	7	1 	3O	3	U		A4CE    	E4CE	5	C	P25EA	 
	20081104		EA  	2008	11	4	2008FA0000722    	2	20081029	G	7322	105217	CARBURETOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	DAMAGED         	D				O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			NM	03	1401E	247  	247  			17270986	L291176T	WA44044		PILOT WAS MAKING 3RD TOUCH AND GO, ON CLIMBOUT ENGINE STARTED VIBRATING EXCESSIVELY, POWER WAS REDUCED AT PATTERN ALTITU	DE, MIXTURE ADJUSTED, SWITCHED MAGNETO'S FROM R TO L WITH NO CHANGE IN THE VIBRATION.  AIRCRAFT LANDED AND SUBSEQUENT OP	ERATION WHILE TAXIING TO PARKING NO VIBRATION WAS ENCOUNTERED.  A RUN UP WAS ACCOMPLISHED AND AT ENGINE OPERATION ABOVE 	1800 RPM THE VIBRATION REOCCURRED.  MAINTENANCE DISCOVERED THE PROBLEM TO BE THE CARBURETOR ACCELERATION DISCHARGE TUBE 	WAS MISSING AND HAD BEEN INGESTED BY THE ENGINE. THE ENGINE AND CARBURETOR HAD 246.9 HOURS SINCE OVERHAUL BY TEXTRON LYC	OMING.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081104		NM  	2008	11	4	2008FA0000723    	1	20081029	G	5711	9252511	SPAR CAP        			LKHEED	P3A   	P3A         	5260103	NM  										RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	921A	16842	1465 			151385				DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A SECOND CRACK WAS FOUND ON THE FORWARD LOWER CAP AT BUTT	LINE 56R.  THE CRACK WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY-CURRENT SURFACE SCAN.					2	L	7	4 	4T			RT	A32NM   					 
	20081104		NM  	2008	11	4	2008FA0000724    	1	20081029	G	5711	9252502	SPAR CAP        			LKHEED	P3A   	P3A         	5260103	NM  										RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	921A	16842	1465 			151385				DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A TERTIARY FRACTURE WAS FOUND ON THE FORWARD SPAR CAP, HO	RIZONTAL FLANGE, WING STA 143.5.  THE FRACTURE WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY CURRENT.  AN INTERNAL VIS	UAL EXAMINATION IDENTIFIED THE AFT HORIZONTAL FLANGE AND VERTICAL FLANGE HAD ALSO BEEN FRACTURED.  THE AFT FLANGE IS FRA	CTURED APPROXIMATELY .750 INCHES, PROPAGATING AFT TOWARD THE FLANGE END.  THE VERTICAL FLANGE FRACTURE PROPAGATED THROUG	H THE FILLET RADIUS UP TO THE FIRST HORIZONTAL ROW OF HI-LOK PINS.  THE FRACTURE LENGTH IS APPROXIMATELY ONE INCH.  FRAC	TURES WERE CONFIRMED WITH EDDY-CURRENT SURFACE SCAN.	2	L	7	4 	4T			RT	A32NM   					 
	20081104		SO  	2008	11	4	2008FA0000725    	1	20081029	G	5753	6232800162328000	RIB             			PIPER 	PA28  	PA28180     	7102808	SO  										TE FLAP	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										DURING ANNUAL INSPECTION FOUND ALL FLAPS, LEADING EDGE RIBS WERE SEVERELY CORRODED.  DETECTION METHOD WAS TO TAKE THE FO	REFINGER AND THUMB AND SQUEEZE LEADING EDGE AT THE RIB, GOT A CRUNCHING FEEL AND SOUND.					1	L	7	1 	3O				2A13    					 
	20081104		CE  	2008	11	4	2008FA0000726    	1	20081016	G	2120	66151007	TUBE            			CESSNA	560   	560XL       	2076702	CE  										AC BAY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		2331 				5333				ENVIRONMENTAL CONTROL UNIT ASPIRATOR AIR LINE THAT RUNS FROM SECONDARY HEAT EXCHANGER TO ASPIRATOR FOUND BROKEN IN TWO J	UST DOWNSTREAM OF SECONDARY HEAT EXCHANGER ELBOW FITTING.  CESSNA P/N 6615100-7					2	L	7	2 	4F			RT	A22CE   					 
	20081104			2008	11	4	2008FA0000727    	4	20081029	G	2210		AUTOPILOT SYS   			ECLIPS	EA500 	ECLIPSEEA500	3350000	SW  										COCKPIT	UNKNOWN         	C				A				UNSCHED LANDING         				G			MULTIPLE FAILURE          			CR	CRUISE         	1			SW	99	678P					191				FLIGHT FROM SDL TO TUL, DIVERT TO ABQ.  AUTOPILOT DISENGAGED VIOLENTLY AT 410 AND YD OFF.  REFER TO QRH RESET CB.  AUTOP	ILOT BACK ON AT 390. 40 SECONDS LATER, AUTOPILOT AND YD DISENGAGED.  UNABLE TO RESET CB.  FL 370 AUTOPILOT BACK ON AND 3	0 SECONDS LATER DISENGAGED AGAIN.  REMAINED OFF THE REST OF THE FLIGHT.  YD RECOVERED AT 280.  AIRSPEED DISAGREE AT 370.	  REFERRED TO QRH.  ADC SOURCE USED AND STILL GIVING AIRSPEED DISAGREE.  DISAPPEARED AT FL250 AND 265 KNOTS.  PILOT ELEC	TED TO DIVERT TO ABQ.  AIRCRAFT IS BEING WORKED ON AT FACTORY SERVICE CENTER.  UNKNOWN CAUSE AT THIS TIME.		1	L	7	2 	4J			RT	A00002AC					 
	20081031		EU  	2008	10	31	2008FA0000729    	1	20080930	G	2120		UNKNOWN         			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					CABIN	ODOR            	B			QMLR	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			NM	03	106LN					3251				SHORTLY AFTER TAKEOFF, PERSONNEL ONBOARD REPORTED A BURNING ODOR TO THE PILOT. ABORTED FLT AND RETURNED TO HELIPAD TO IN	VESTIGATE.  MECH PERFORMED AN INSPECTION OF THE AIRFRAME, ENGINE, WIRING, HOSES AND THE BELTS OF ALL COMPONENTS. NO DEFE	CTS OR THE SOURCE OF A BURNING ODOR WAS FOUND. SUBSEQUENT CHECK FLIGHT WAS PERFORMED BY THE PILOT & MECHANIC TO INVESTIG	ATE FOR BURNING ODOR, NONE FOUND. THE ACFT WAS RETURNED TO SERVICE. (K)			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20081031		NE  	2008	10	31	2008FA0000730    	2	20080903	G	7321	2523631	BELLOWS         								PWA   	PT6   	PT6A34AG    	52053	NE  					FCU	DAMAGED         	B			IG0R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	03					B32178		PCEPH0028			FCU (PN 32447866-6, SN B32178) BENCH TESTED AND FOUND TO BE UNSERVICEABLE DUE TO BREACHED BELLOWS, (PN 2523631, SN 8011)	. (K)										4	T			E4EA				 
	20081104		CE  	2008	11	4	2008FA0000731    	1	20081030	G	3210	244110010	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LT MLG	SHEARED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			GL	00	5319V	2532 				172RG0505	L3678636E	799482		THE LEFT MAIN LANDING GEAR PIVOT ASSY SHEARED IN TWO NEAR THE ACTUATOR END.  THE SPLICED SECTION WHERE THE DRIVE GEAR IS	 INSTALLED SEPARATED.					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
	20081104		CE  	2008	11	4	2008FA0000732    	1	20081016	G	2120	66151007	TUBE            			CESSNA	560   	560XL       	2076702	CE  										AC BAY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	3	2242 				5341				ENVIRONMENTAL CONTROL UNIT ASPIRATOR AIR LINE THAT RUNS FROM SECONDARY HEAT EXCHANGER TO ASPIRATOR FOUND BROKEN IN TWO, 	JUST DOWNSTREAM OF SECONDARY HEAT EXCHANGER ELBOW FITTING.  CESSNA P/N 6615100-7					2	L	7	2 	4F			RT	A22CE   					 
	20081104		SW  	2008	11	4	2008FA0000733    	1	20081030	G	3233	B10006	COUPLING        	DUKES       		MOONEY	M20   	M20E        	5870212	SW  										LANDING GEAR	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	09	204WF	3483 				210021				DURING APPROACH FOR LANDING, THE PILOT WAS UNABLE TO GET THE LANDING GEAR TO EXTEND, EITHER NORMALLY OR USING THE EMERGE	NCY GEAR EXTENSION SYSTEM.  A GEAR-UP LANDING WAS ACCOMPLISHED WITH ONLY MINOR DAMAGE AND NO INJURIES.  SUBSEQUENT INVES	TIGATION DETERMINED THAT THE COUPLING (P/N B100-06) BETWEEN THE LANDING GEAR MOTOR TRANSMISSION AND THE DRIVE ACTUATOR H	AD BROKEN.  THE COUPLING HAS NO REPLACEMENT REQUIREMENTS, BUT IS RECOGNIZED IN MOONEY SERVICE INSTRUCTION M20-89 AS A PA	RT THAT COULD FAIL DUE TO AGE HARDENING AND DETERIORATION.  THE AIRCRAFT OWNER WAS NOT AWARE OF THIS CONDITION.		1	L	7	1 	3O				2A3     					 
	20081104		EA  	2008	11	4	2008FA0000735    	2	20080925	G	7414	M3828	GEAR            	SLICK       		CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					MAGNETO	DAMAGED         	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	658PW				08080703	18282098	L03291348E			WHILE PERFORMING SB03-08, FOUND THE DISTRIBUTOR GEAR DRIVE GEAR WEARING PREMATURELY AND CAUSING GEAR DUST INSIDE MAGNETO	. GEAR MATERIAL WAS COMING OFF CAUSING IT TO COLLECT INSIDE DISTRIBUTOR CAP. ALSO, FOUND EXCESSIVE AMOUNT OF OIL INSIDE 	MAGNETO. REPLACED MAGNETO. (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
	20081104			2008	11	4	2008FA0000737    	2	20080905	G	7200		ENGINE          			AMD   	FALC20	FALCON200   	2730150	EU  											FOD             	B			UO2R	A				UNSCHED LANDING         				C	J		F.O.D.                    	WARNING INDICATION        		CL	CLIMB          	1			GL	19	69EC					498				AFTER TAKEOFF, OVERSPEED WARNING LIGHT ILLUMINATED. RPM REDUCTION USING PROP GOVERNOR CONTROL NOT SUCCESSFUL, USED THROT	TLE CONTROL TO REDUCE ENGINE RPM. LANDED WITHOUT INCIDENT. REPAIR STATION INSPECTED AND DUPLICATED PROBLEM ON ENGINE GRO	UND RUN. ALL VISUAL INSP REVEALED NO DISCREPANCIES EXCEPT AN EXTRUSION OF SMALL AREA TO THE TOP OF CRANKCASE ABOVE NR 2 	CYLINDER (NO OIL LEAK NOTICED). BECAUSE OF THIS ABNORMALITY, WE REMOVED THE OIL FILTER AND SUCTION SCREEN SHOWED SUBSTAN	TIAL METAL SHAVING AND SMALL PIECES OF METAL AND (2) SMALL SILVER COLOR BALLS (SUSPECT BALL BEARING OF SOME SORT). THE E	NGINE WAS REMOVED FOR TEAR DOWN INSP AND REPAIR. ENGINE TEAR DOWN REVEALED DESTRUCTION OF BOTH INTAKE AND EXHAUST LIFTER	2	L	7	2 	4F			RT	A7EU    					 
	20081104			2008	11	4	2008FA0000738    	2	20080913	G	8500		ENGINE          			AMD   	FALC20	FALCON200   	2730150	EU  											MAKING METAL    	B			UO2R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	19	69EC					498				AFTER TAKEOFF, OVERSPEED WARNING LIGHT ILLUMINATED. RPM REDUCTION USING PROP GOVERNOR CONTROL NOT SUCCESSFUL & USED THRO	TTLE CONTROL TO REDUCE ENGINE RPM. LANDED WITHOUT INCIDENT. REPAIR STATION INSPECTED & DUPLICATED PROBLEM ON GROUND RUN.	 NO DISCREPANCIES EXCEPT AN EXTRUSION OF SMALL AREA TO THE TOP OF CRANKCASE ABOVE NR 2 CYLINDER (NO OIL LEAK NOTICED). B	ECAUSE OF THIS ABNORMALITY, REMOVED OIL FILTER & SUCTION SCREEN SHOWED SUBSTANTIAL METAL SHAVING & SMALL PIECES OF METAL	 AND 2 SMALL SILVER COLORED BALLS (SUSPECT BALL BEARING OF SOME SORT). ENGINE REMOVED FOR TEAR DOWN INSP & REPAIR. ENGIN	E TEAR DOWN REVEALED DESTRUCTION OF BOTH INTAKE & EXHAUST LIFTER BODIES OF NR 1 CYLINDER & EXTENSIVE DAMAGE OF ENGINE. A	2	L	7	2 	4F			RT	A7EU    					 
	20081113		CE  	2008	11	13	2008FA0000739    	1	20081103	G	3710		ADAPTER         			CESSNA	172   	172M        	2072418	CE  										VACUUM SYS	DAMAGED         	B				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	99	30830	5902 				17264138				AIRCRAFT HAD A FRESHLY OVERHAULED ENGINE INSTALLED AND WAS MAKING ITS FIRST FLIGHT.  DURING CRUISE, IN VFR CONDITIONS, T	HE PILOT NOTED A OVERHEATING TYPE OF ODOR AND THEN NOTED A MOMENTARY SMALL REDUCTION IN POWER AFTER WHICH POWER RETURNED	 TO NORMAL.  THE PILOT THEN NOTICED THAT BOTH GYROS BEGAN PROCESSING AND THE VACUUM GAUGE READ ZERO.  AIRCRAFT RETURNED 	WITHOUT FURTHER INCIDENT.  INVESTIGATION BY MAINTENANCE FOUND THAT THE VACUUM PUMP ADAPTER WAS DISCOLORED.  REMOVAL OF V	ACUUM PUMP FOUND THAT THE SPLINED SHAFT HAD MELTED AWAY AND ITS PARTICLES WERE CAUGHT BETWEEN PUMP AND ADAPTER.  MAINTEN	ANCE NOTED THAT THE OIL DISTRIBUTION HOLES BETWEEN THE ADAPTER AND THE ENGINE WERE ALIGNED PROPERLY.  NO IMMEDIATE CAUSE	1	H	7	1 	3O			NT	3A12    					 
	20081106		EA  	2008	11	6	2008FA0000740    	2	20081001	G	7414	AB382585	CONTACT         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					MAGNETO	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	7087J					2873				CONTACT ASSY, AS A NEW ASSY OPENS BEYOND THE MAXIMUM .024 INCH. THIS IS A REOCCURRING PROBLEM WITH BOTH THE LT AND THE R	T CONTACT ASSEMBLIES. CIRCUMSTANCES ARE WHEN THE POINTS ARE REPLACED. (K)					1	G	7	1 	3O	3	O		H10WE   	E286				 
	20081106		EU  	2008	11	6	2008FA0000741    	1	20081026	G	6322	MS210436	NUT             			HUGHES	369   	369FF       	4470709	EU  	ALLSN 	250C  	250C30      	03013	GL  					BLOWER	BACKED OUT      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	5185G					0009F				OIL COOLER BLOWER DRIVEN PULLEY RETAINING NUT IS BACKING OFF OF SHAFT DURING NORMAL US. NUT IS A STAINLESS STEEL, SILVER	 PLATED, ALL METAL SELF LOCKING TYPE NUT.  THIS WAS THE THIRD OCCURRENCE OF THIS TYPE FOR OUR UNIT AND WE ARE ALSO CAUSE	S THE SHAFT BEARING TO GO BAD WHICH DESTROYS THE OIL COOLER BELT.  THIS LEADS TO EXTREME ENGINE OIL AND MAIN TRANSMISSIO	N OIL TEMPERATURES. AFTER INVESTIGATING PNS WE FOUND THAT MFG HAS BEEN USING THIS TYPE OF NUT FOR A LONG TIME AND WE ARE	 UNSURE IF THE NUTS CURRENTLY BEING PRODUCED ARE SUBSTANDARD.		1	G	7	1 	3U	3	U		H3WE    	E1GL				 
	20081106		EA  	2008	11	6	2008FA0000742    	2	20080925	G	7414	4371	MAGNETO         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	CONTAMINATED    	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	452SM	5    				172S10528	L3343151E			DURING INSPECTION FOR SB 03-08 THE FIRST 5 HOUR INSPECTION FOUND OIL ON THE COIL TAB ON BOTH MAGNETOS AND CAM WEARING ON	 BOTH MAGNETOS FOR THE AMOUNT HOURS ON MAGNETOS. ALSO, FOUND EXCESSIVE AMOUNT OF OIL INSIDE DISTRIBUTOR FOR THE AMOUNT O	F HOURS ON MAGNETOS. THIS IS CAUSING THE CARBON DUST TO COLLECT AND BUILDUP INSIDE MAGNETOS. (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081107		SW  	2008	11	7	2008FA0000743    	1	20080929	G	5541	442283	SPAR            			GULSTM	112   	114         	7630314	SW  										RUDDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	65	4945W	603  				14267				SPAR IS CRACKED AND BROKEN OUT AT UPPER HINGE ATTACH POINT.  THIS SPAR WAS REPLACED WITH NEW 1-1-99 FOR SAME CONDITION. 	 THIS CONDITION WAS FOUND BY CLOSE EXAMINATION OF AREA DURING ANNUAL INSPECTION. WE ARE IN RECEIPT OF INFORMATION OF SAM	E FAILED CONDITION ON SN 14408.  RECOMMEND THAT DOUBLER BE INSTALLED TO STRENGTHEN SPAR IN THIS AREA.  (K)				1	L	7	1 	3O				A12SO   					 
	20081110		CE  	2008	11	10	2008FA0000745    	1	20080922	G	2820	AN8156D	CONNECTOR       			RAYTHN	B300  	B300RAYTHEON	7150007	CE  										RT AUX TANK	DISCONNECTED    	C				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SO	15	102FL					FL263				UPON ENGINE RUN-UP, OBSERVED FUEL DUMPING BUT RT HEATED FUEL VENT PROBE. UPON INVESTIGATION FOUND FUEL LINE DISCONNECTED	 INSIDE RT AUX TANK. FUEL LINE, PN 101-920000-9 FROM MOTIVE FLOW VALVE TO JET PUMP DISCONNECTED FROM UNION PN AN815-6D. 	FUEL LINE PN 101-920000-19, FOUND LOOSE ON UNION PN AN815-6D.  FUEL LINES FROM JET PUMP TO NACELLE TANK PN 101-920000-57	 AND 101-920000-43 FOUND LOOSE ON UNION PN AN815-8D. RECONNECTED AND TIGHTENED ALL LINES AND FITTINGS INSIDE RT FUEL AUX	 TANK. INSPECTION OF LT FUEL AUX TANK FOUND ALL LINES AND FITTINGS OK. (K)		2	L	7	2 	4T			RT	A24CE   					 
	20081107		NE  	2008	11	7	2008FA0000746    	2	20081015	G	7314		PUMP            			BOEING	727   	727200      	138407E	NM  	PWA   	JT8   	JT8D217C    	52053	NE  					FUEL SYS	MALFUNCTIONED   	A			I5PA	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			WP	13	705AA					22462	726206U			CRUISE NR 1 ENG STARTED TO SPOOL DOWN OTHER PARAMETERS ARE NORMAL, PERFORMED IN-FLIGHT START CHECKLIST SEVERAL TIMES INC	LUDING RESETTING SWITCHES, NO LIGHT OFF. ACFT DIVERTED AND THE CREW PERFORMED ENG INSPECTION AND START ON NR 1 ENG HIGH 	IGNITION SYS, ENGINE STARTED OK IN GROUND. START IGNITION NR 1 FROM HIGH-ENERGY FAIL IN FLIGHT POSITION. DEFERRED NR 1 E	NG IGNITION IAW MEL 74-1 AND 705 CONTINUED SERVICE.  MAINT REMOVED AND REPLACED NR 1 ENG FUEL PUMP IAW MM 73-11-1, PURGE	 FUEL SYSTEM, PS4, PT7, AND P AND D VALVE CHECK FOR MOISTURE. PERFORMED FULL POWER ENGINE RUN AND LEAK CHECK SYSTEM OPER	ATIONAL CHECK, OK. (K)	2	L	7	3 	4F	4	F	RT	A3WE    	E9NE				 
	20081121		CE  	2008	11	21	2008FA0000747    	1	20081106	G	3520	C3512000205	OXYGEN MASK     			CESSNA	500   	550         	2076604	CE  										CABIN	TORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	43SA	2500 				5500086				THREE OF THE DROP DOWN PASSENGER OXYGEN MASKS P/N C351-2000-205 OR CESSNA P/N 17504-61 WERE FOUND WITH TEARS IN THE FACE	 CUSHION NEXT TO THE INNER MASK HOUSING IN THE SAME AREA DESCRIBED IN AD 99-08-21.  HOWEVER THE ELASTOMERIC CURE DATES O	N THESE MASKS ARE THE 3RD QUARTER OF 1999, THE AD ONLY ADDRESSES MASKS WITH A CURE DATE FROM 3RD QUARTER 1993 TO 1ST QUA	RTER 1997.  THESE TEARS COULD LEAD TO LEAKAGE AND POSSIBLE INSUFFICIENT OXYGEN DELIVERY AS DESCRIBED IN THE ORIGINAL A/D	.		1	L	7	2 	4F				A22CE   					 
	20081110			2008	11	10	2008FA0000748    	1	20081101	G	2810	CB959	FUEL TANK       																		DAMAGED         	B			RYHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03										FUEL TANKS WERE FOUND TO HAVE SIGNIFICANT LEAKS IN AN AREA NOT CLOSE TO ANY SEAMS, WELDS, OR BOSSES. THERE WERE NO VISIB	LE DENTS, DINGS, SCRATCHES, GOUGES OR OTHER DAMAGE IN THE AREAS OF THE LEAKS. THE LEAK HOLES WERE MUCH SMALLER THAN THE 	DIAMETER OF A PIN AND WERE NOT VISUALLY DETECTABLE. TANKS WERE TAGGED UNAIRWORTHY.  FUEL TANKS WERE ALSO TAGGED UNAIRWOR	THY PENDING FURTHER TESTINGS AS A PRECAUTION.  (K)																 
	20081128		GL  	2008	11	28	2008FA0000750    	2	20081106	G	7200	44904	STIFFENER       	WILINT      							WILINT	FJ44  	FJ443A      	66006	GL  					LP TURBINE	SEPARATED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23		1858 			AU00307		141224			WHILE UNDERGOING A CHECK 3 MAINT INSP DURING EARLY NOVEMBER 2008, THE STIFFENING RING ON THE 1ST LOW PRESSURE TURBINE NO	ZZLE ON ENGINE WAS FOUND SEPARATED AND TRAPPED BETWEEN THE 1ST LP TURBINE NOZZLE AND THE HIGH PRESSURE TURBINE NOZZLE.  	NO SECONDARY DAMAGE WAS NOTED.  PROBABLE CAUSE IS A SUSPECT MANUFACTURING OPERATION.									4	F			E3GL				 
	20081126		EA  	2008	11	26	2008FA0000751    	2	20081024	G	7414	SS1001	BOOSTER         	SLICK       		HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360G1A   	41898	EA  					ZONE 100	EXPLODED        	D				E	H			ENGINE SHUTDOWN         	DEACTIVATE SYST/CIRCUITS			B	A		SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		TO	TAKEOFF        	1			SW	41	2014T	701  	50   			0313	L3373151A			START MAGNETO, START BOOSTER BOX PN SS1001 BLEW THE TOP PORTION APART. IT CAUGHT ON FIRE AND SMOKE WENT EVERYWHERE. INSP	ECTED HELICOPTER WHEN SMOKE CLEARED AND COULD NOT FIND THE PROBLEM. TURNED OFF THE FUEL AND BUMPED THE STARTER AND FOUND	 THE PROBLEM TO BE THE START BOX. WITHIN JUST BUMPING THE STARTER , HELICOPTER WAS COVERED IN SMOKE. I REMOVED AND REPLA	CED THE BOX AND INSPECTED ALL THE WIRING AND ALL IS WORKING JUST FINE NOW. BIGGEST PROBLEM I SEE IS THAT THE SLICK START	 BOX SETS TO CLOSE TO THE FUEL MAIN LINE, WITCH COULD OF LED TO A COMPLETE LOSS OF AIRCRAFT.		1	G	7	1 	3O	3	O	O	4H12    	1E10				 
	20081125		CE  	2008	11	25	2008FA0000752    	1	20081103	G	3320	CLE23602	LIGHT           			CESSNA	560   	560XL       	2076702	CE  										CABIN	BURNED OUT      	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	669TT	714  				5684				DURING POSTFLIGHT FOUND CABIN (LT) UPWASH, AND (RT) DOWNWASH LED LIGHT ELEMENTS INOP. INTIALLY TROUBLESHOOTING FOUND CIR	CUIT BREAKER 140 IN THE INTERIOR DC "J" BOX OPEN. ATTEMPTED TO RESET, BREAKER WOULD OPEN IMMEDIATLY WHEN THE CABIN LIGHT	 SWITCH WAS ACTIVATED ON. FURTHER TROUBLESHOOTING FOUND THAT THE LT AFT CABIN UPWASH LIGHT ELEMENT SHOWED EVIDENCE OF EX	CESSIVE HEAT APPROX IN THE MIDDLE OF  ELEMENT. REMOVED LIGHT ELEMENT AND INSTALLED SERVICEABLE O/H ELEMENT. OPS CHECK OF	 SYS PERFORMED, SYS CHECKS GOOD.  TECH SUPPORT SUGGESTS MOISTURE INGRESS AS THE CAUSE OF THE LIGHT ELEMENT FAILURE. DEFE	CTIVE PART WAS RETURNED TO MFG CPD.	2	L	7	2 	4F			RT	A22CE   					 
	20081125		SO  	2008	11	25	2008FA0000753    	2	20081107	G	7414		IMPULSE COUPLING								CONT  	O550  	IO550N      	17042	SO  					MAGNETO	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	502BZ	1021 			D05KA054		917755			WHILE REMOVING MAGNETO FOR EXCHANGE FOUND IMPULSE COUPLING INOPERABLE.  THIS IS THE SECOND LOW TIME MAGNETO OF THIS MODE	L FOUND WITH A BAD IMPULSE COUPLING.										3	O			E3SO				 
	20081125		EA  	2008	11	25	2008FA0000754    	2	20081111	G	7414	4371	MAGNETO         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	OUT OF POSITION 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	9360C	90   				287890401	L2454636A			EXCESSIVE TIMING DRIFT.  BOTH MAGS SET 25 DEGREES BTDC ON NR1 CYLINDER.  NEXT FIRING ORDER (NR 3 CYLINDER) IS OFF 6 DEGR	EES BETWEEN LT/RT MAG.  NEXT FIRING ORDER (NR2 CYLINDER) IS NORMAL.  LAST FIRING ORDER (NR4 CYLINDER) IS OFF 6 DEGREES B	ETWEEN LT/RT MAGS.  INITIAL SUSPECT IS CAM LOBE.  CARBON BRUSH INSPECTED IAW SB3-08.  BRUSH SHOWS POSSIBLE INDICATION OF	 (EARLY STAGE) UNDERCUT.  SLIGHT BRUSH RESIDUE EVIDENCED ON BEARING BAR.			1	L	7	1 	3O	3	O		2A13    	E286				 
	20081112		EU  	2008	11	12	2008FA0000755    	1	20080930	G	7603		JOINT           			PIAGIO	P180  	P180        	6960204	EU  										CONTROL CABLE	DAMAGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	23RF					1080				RT ENGINE POWER CONTROL CABLES FREEZING AT ALTITUDE. INSPECTED CABLE AND FOUND THE STAINLESS STEEL SLEEVE DISCONNECTED A	T JOINT TO FLEX SLEEVE. IT APPEARS TO BE A SILVER SOLDERED JOINT, AND SOLDER FAILED ALLOWING MOISTURE TO ENTER THE INTER	NAL OF CABLE AND FREEZE WHICH COULD CAUSE LOSS OF MOTION OF THE CONTROL CABLES AND CAUSE FUEL CONTROL CABLES NOT TO ACHI	EVE FULL TRAVEL, RESTRICTING ENGINE POWER.			1	H	7	2 	3O			RT	A59EU   					 
	20081125		CE  	2008	11	25	2008FA0000756    	1	20081112	G	7120	051313211	MOUNT           			CESSNA	175   	175         	2072502	CE  										ZONE 100	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	175UK					55829				DURING INSP, MECHANIC FOUND THE LT UPPER ENGINE MOUNT BRACKET, PN 0513132-11, CRACKED ALL THE WAY THROUGH. CRACK WAS AT 	THE OUTER RADIUS OF THE WASHER.					1	H	7	1 	3O			NT	3A17    					 
	20081112		SW  	2008	11	12	2008FA0000757    	1	20080718	G	5610		WINDOW          			ECLIPS	EA500 	ECLIPSEEA500	3350000	SW  										COCKPIT	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	61	136EA					000136				THERE WAS A POPPING NOISE COMING FRAOM THE VICINITY OF THE PILOTS WINDOW, WINDOW WAS REPLACED.						1	L	7	2 	4J			RT	A00002AC					 
	20081112		SW  	2008	11	12	2008FA0000758    	1	20080818	G	2621	FX002002	EXTINGUISHER    			ECLIPS	EA500 	ECLIPSEEA500	3350000	SW  										RT NACELLE	LEAKING         	C				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	61	575CC					000075				RT ENGINE FIRE EXTINGUISHER CARTRIDGE LEAKED THROUGH DISCHARGE NOZZLE AND EXPOSED THE ENGINE AND COMPONENTS TO HIGHLY CO	RROSIVE CHEMICAL. ENGINE REMOVED FOR CLEAN UP AND REPAIR BY MANUFACTURER.					1	L	7	2 	4J			RT	A00002AC					 
	20081112		SW  	2008	11	12	2008FA0000759    	1	20080911	G	5340		RETAINER        			ECLIPS	EA500 	ECLIPSEEA500	3350000	SW  										COCKPIT WINDOW	UNKNOWN         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	61	568EA					000168				A POPPING NOISE COMING FROM THE VICINITY OF THE CO PILOTS WINDOW. SIDE WINDOW RETAINERS WERE REPLACED.						1	L	7	2 	4J			RT	A00002AC					 
	20081125		SO  	2008	11	25	2008FA0000760    	2	20081112	G	8530	AEC631397	CYLINDER        			CESSNA	188   	188B        	2073007	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	78417					18801952T	1580856D	001465		FOUND ALL 6 CYLINDERS WERE CRACKED.  CYLINDER NR1 S/N 50422-12, CRACKED BETWEEN COOLING FIN 16 AND 17 (COUNTED DOWN FROM	 TOP) FROM THE INTAKE PORT ALL THE WAY AROUND THE CYLINDER, OVER THE TOP SPARK PLUG HOLE, TO THE EXHAUST PORT.  2 CRACKS	 ON THE INSIDE FROM THE TOP SPARK PLUG HOLE TO THE INTAKE SEAT AND THE INTAKE SEAT TO THE EXHAUST SEAT.  AN APPROX .1250	 X .2500 HOLE BY THE EXHAUST SEAT ALL THE WAY THROUGH THE HEAD.  THE OTHER 5 CYLINDERS (S/N 50741-13, 50974-19, 50960-01	, 50422-06, AND 50991-25) ARE CRACKED UNDER FIN 16 OR 17 ANYWHERE FROM 1INCH TO 6 INCH LONG ON THE OUTSIDE OF THE INTAKE	 PORT, APPROX MIDDLE SECTION OF THE HEAD (CRACKS RUN PARALLEL WITH COOLING FINS).	1	L	7	1 	3O	3	O		A9CE    	E3SO	5	C	P47GL	 
	20081126		SO  	2008	11	26	2008FA0000761    	1	20081113	G	5347	7745405	SEAT TRACK      			PIPER 	PA38  	PA38112     	7103812	SO  										ZONE 100	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2472D					3879A0327				PASSENGER SEAT WAS REMOVED FOR ANNUAL INSPECTION.  UPON VISUAL INSPECTION OF SEAT RAILS, A CRACK WAS DISCOVERED GOING TH	ROUGH THE ENTIRE RAIL.  THE SEAT RAIL MUST BE REPLACED IN ORDER TO FACILITATE SAFE FLIGHT.					1	L	7	1 	3O				A18SO   					 
	20081118		CE  	2008	11	18	2008FA0000762    	1	20081020	G	2721	S22952593	CHAIN           	CESSNA      		CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					RUDDER TRIM	BROKEN          	B			BGSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	169EC	288  				172RG0515	L2843836A			DURING A NON RELATED MAINTENANCE ACTION, THE MECHANIC NOTICED THE RUDDER TRIM WHEEL WAS MOVING WITH NO RESISTANCE. THE M	ECHANIC INSPECTED FURTHER AND FOUND THE CHAIN HAD SEPARATED AT ONE OF THE LINKS.  AFTER CLOSER EXAMINATION IT HAS BEEN F	OUND THAT SEVERAL OF THE LINK PINS ARE EITHER TOO SHORT OR WAS NOT PRESSED ENOUGH TO HOLD THE LINKS TOGETHER.  THE PART 	WAS ORDERED FROM MFG.  (K)			1	H	7	1 	3O	3	O		3A17    	E286				 
	20081118		CE  	2008	11	18	2008FA0000763    	1	20081008	G	2720	717	SOLENOID VALVE  			BEECH 	90    	C90         	1152913	CE  										RUDDER	STUCK           	B			E81R	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	03	261GB	5351 				LJ1119				INVESTIGATED PILOT REPORT OF RUDDER BOOST CONSTANTLY KICKING TO LEFT.  FOUND PN 717 LT SOLENOID VALVE STUCK IN OPEN POSI	TION.  ALSO FOUND (3) PN AN9181D RUDDER BOOST CONTROL SYSTEM CROSS FITTING CRACKED AND WATER IN SYSTEM.  PURGED WATER FR	OM SYSTEM AND REPLACED LT SOLENOID VALVE, CRACKED FITTINGS AND SYSTEM FILTER; OPERATIONS NORMAL.  SUSPTECT CONDENSATION 	OR OTHER SOURCE OF WATER INGESTION INTO SYSTEM THAT CAUSED FREEZING DAMAGE TO COMPONENTS.  (K)			1	L	7	2 	3T				3A20    					 
	20081118		CE  	2008	11	18	2008FA0000764    	1	20081021	G	2760	21EN96	SWITCH          			BEECH 	MU300 	400A        	1155402	CE  										SPEED BRAKE SYS	CORRODED        	B			E81R	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	03	48SE					RK48				INVESTIGATED PILOT REPORT OF UNCOMMANDED "SPEEDBRAKE EXTENDED" ANNUNCIATOR LIGHT ILLUMINATION IN FLIGHT.  FOUND HIGH RES	ISTANCE IN SPOILER MIXER ASSY.  SPEEDBRAKE RETRACT SWITCH ASSY, REPLACED S156 SWITCH WITH SUPERSEDING PN 21EN42-6 SWITCH	 ASSY.  SPEEDBRAKE SYSTEM OPERATIONS NORMAL, NO FAULTS INDICATED.  SUSPECT S156 SWITCH CONTACTS CORRODED OR PITTED FRO W	EAR AND/OR LONGTERM WATER/DIRT CONTAMINATION.  RECOMMEND SIMILAR SWITCHES ON BE 400 SERIES AIRCRAFT BE REPLACED WITH IMP	ROVED SWITCHES WITH BETTER SEALING CAPABILITIES BY RECOMMENDED SERVICE BULLETIN OR SIMILAR.  (K)		2	H	7	2 	4F			RT	A16SW   					 
	20081118			2008	11	18	2008FA0000765    	4	20081020	G	3457	13824120211	GPS             			SNIAS 	350   	AS350BA     	8680817	EU  										COCKPIT	OVERHEATED      	B			H0CR	A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	01	29FX					2085				DURING FLIGHT, THE TRIMBLE GPS OVERHEATED AND EMITTED SMOKE.  THE PILOT MADE A PRECAUTIONARY LANDING AND SECURED POWER T	O THE GPS BY REMOVING THE FUSE.  THE UNIT HAD BEEN INSTALLED SINCE 1996.  (K)					1	G	7	1 	3U			NC	H9EU    					 
	20081124		GL  	2008	11	24	2008FA0000766    	1	20080808	G	2752	EM41165	ACTUATOR        			AMTR  	LANCAR	LANCAIR320  	056300A	GL  										TE FLAP	FAILED          	C			TOWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	320LA					269				MULTIPLE FLAP ACTUATION FAILURES. (K)						1	L	7	1 	3O			RT	EXPA1L71					 
	20081124		CE  	2008	11	24	2008FA0000769    	1	20081010	G	2710	1260505315	CONTROL CABLE   			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520*      	17032	SO  					TR AILERON	WORN            	B			TF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6523N	3369 				21063081				DURING ANNUAL INSP, THE RT AILERON RETURN CABLE WAS FOUND WORN BEYOND LIMITS BY THE WHITE PLASTIC PULLEY NEAR THE LEADIN	G EDGE AT THE WING ROOT.  (K)					1	H	7	1 	3O	3	O		3A21    	E5CE				 
	20081120		CE  	2008	11	20	2008FA0000770    	1	20081026	G	2720	441921933	RUDDER PEDAL    			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					COCKPIT	JAMMED          	B			CNQR	K				NONE                    				O			OTHER                     			DE	DESCENT        	1			CE	01	370QS					6800099				ON ACFT DEPARTURE, THE RUDDER PEDALS JAMMED ON THE COCKPIT SIDE PANELS ON THE TAKEOFF.  AN EMERGENCY WAS DECLARED AND TH	E ACFT LANDED UNEVENTFULLY.  DURING THE PREVIOUS MAINT VISIT, THE RUDDER WAS REPLACED WITH A RENTAL UNIT, THE RUDDER WAS	 PROPERLY INSTALLED AND DOCUMENTED AND RIG AND TRAVEL CHECKS WERE GOOD. THE ACFT FLEW AN OPERATIONAL CHECK FLIGHT AFTER 	MAINT WITH NO REPORTED ISSUES.  THE SIDE PANELS HAVE BEEN PROPERLY SECURED AND CLEARANCE IS SATISFACTORY.  A SCR (SERVIC	E CONDITION REPORT) HAS BEEN SUBMITTED TO ENGINEERING FOR REVIEW TO CHANGE SECURING METHOD FROM VELCRO TO A FASTENER TYP	E INSTALLATION.  (K)	2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
	20081120		CE  	2008	11	20	2008FA0000771    	1	20081026	G	2720		RUDDER PEDAL    			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					COCKPIT	JAMMED          	B			CNQR	O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CE	07	370QS					6800099				ON ACFT DEPARTURE, THE RUDDER PEDALS JAMMED ON THE COCKPIT SIDE PANELS ON THE TAKEOFF.  AN EMERGENCY WAS DECLARED AND TH	E ACFT LANDED UNEVENTFULLY.  DURING THE PREVIOUS MAINT VISIT, THE RUDDER WAS REPLACED WITH A RENTAL UNIT, THE RUDDER WAS	 PROPERLY INSTALLED AND DOCUMENTED AND RIG AND TRAVEL CHECKS WERE GOOD. THE ACFT FLEW AN OPERATIONAL CHECK FLIGHT AFTER 	MAINT WITH NO REPORTED ISSUES.  THE SIDE PANELS HAVE BEEN PROPERLY SECURED AND CLEARANCE IS SATISFACTORY.  A SCR (SERVIC	E CONDITION REPORT) HAS BEEN SUBMITTED TO ENGINEERING FOR REVIEW TO CHANGE SECURING METHOD FROM VELCRO TO A FASTENER TYP	E INSTALLATION.  (K)	2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
	20081120		CE  	2008	11	20	2008FA0000772    	1	20081002	G	2750	67183281	CONTROLLER      			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	03047	GL  					TE FLAP	FAILED          	B			CNQR	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CE	07	78SL					7500238				FLAPS HARD FAILED DURING FLIGHT.  FOUND THAT THE FLAP CONTROLLER HARD FAILED DURING COLD SOAKING.  REPLACED FLAP CONTROL	LER AND ACCOMPLISHED SATISFACTORY FLAP FUNCTIONAL CHECK WITH NO DEFECTS NOTED.  RETURNED ACFT TO SERVICE. (K)					2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
	20081120		SO  	2008	11	20	2008FA0000773    	2	20080929	G	8530	65315	CYLINDER        			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	5307Q	1081 				15073207	21411272A			NR 4 CYLINDER FOUND CRACK AT BARREL BETWEEN COOLING FINS.  CRACK WAS APPROX 300 DEGREES AROUND CYLINDER CIRCUMFERENCE.  	SYMPTOMS INCLUDED ROUGH RUNNING, LARGE OIL LEAK AND SMOKE.  CATASTROPHIC FAILURE WAS EMANATE AND WOULD HAVE CAUSED COMPL	ETE LOSS OF ENGINE POWER.  (K)				1	H	7	1 	3O	3	O		3A19    	E252				 
	20081120		EU  	2008	11	20	2008FA0000774    	1	20081031	G	5210	709010401101	TRIM TAB        			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6B37A     	52179	NE  					MAIN ROTOR BLADE	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	315PD					14035	PU0041			UPON POST FLIGHT IT WAS NOTICED THE MAIN ROTOR BLADE TRIM TAB WAS SERIOUSLY DELAMINATED AND SEPARATED IN FLIGHT. THIS PR	OBLEM HAS OCCURRED NUMEROUS TIMES IN THE PAST.  SOME OCCASIONS REQUIRED THE BLADE TO BE REMOVED AND SENT BACK TO THE MFG	 FOR REPAIR.  AS IN THIS CASE, OTHER TIMES THE BLADE WAS ABLE TO BE REPAIRED AT OUR FACILITY IAW MM.  MFG IS AWARE OF TH	IS PROBLEM AND STILL HAS NOT CORRECTED IT.  PROBABLE CAUSE IS THE BONDING MATERIAL AND/OR THE BONDING PROCEDURE.  (K)			1	G	7	1 	3U	4	U		H7EU    	E4EA				 
	20081120		EA  	2008	11	20	2008FA0000775    	2	20081027	G	7322	383493	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	5339M	2362 				172S9359	L3084051A			PN 383943 PLUG FOUND HANGING BY SAFETY WIRE WHEN TROUBLESHOOTING LACK OF POWER FROM ENGINE.  THREADS IN COVER MISSING.  	THIS SERVO WAS NOT INCLUDED IN AD2008-08-14 DUE TO MFG DATE OF UNIT.  THE SERVO WAS ORIGINAL EQUIPMENT ON A 2003, 172S, 	WITH A TT OF 2462.0 HOURS AND HAD NOT BEEN REPAIRED OR O/H.  PLUG GASKET WAS MISSING. (K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081125		EA  	2008	11	25	2008FA0000776    	2	20081024	G	8530	AEL75838	GUIDE           			BELL  	47    	47G4A       	1181031	SW  	LYC   	O540  	VO540B1B3   	41532	EA  					NR 1 CYLINDER	WORN            	G			PFIG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	24HM					7688	L245043			DURING INVESTIGATION OF AN ACCIDENT IN WHICH ACFT LOST POWER AND WAS FORCED TO LAND THE FOLLOWING WAS DISCOVERED: COMPRE	SSION CHECK REVEALED THE NR 1 CYL WAS LEAKING PAST THE EXHAUST VALVE. (COMPRESSION 45/80).  EXAMINATION OF THE CYLINDER 	REVEALED THE EXHAUST GUIDE WAS EXTREMELY WORN AND CRACKED IN 4 PLACES.  VALVE OD .496 INCH GUIDE ID .540 INCH, .044 INCH	 CLEARANCE.  IT WAS FURTHER DISCOVERED THAT THE VALVE WAS PN SL-16740 NIMONIC VALVE GUIDE. THIS VALVE REQUIRES THE USE O	F A HIGH CHROME CONTENT NI-RESIST VALVE GUIDE.  ECI VALVE GUIDE AEL 75838 WAS FOUND INSTALLED.  THIS IS A NI-RESIST VALV	E GUIDE.  ECI VALVE GUIDE AEL 75838 WAS FOUND INSTALLED.  THIS IS A NI-RESIST GUIDE.  HOWEVER IT DOES NOT HAVE THE CHROM	1	G	7	1 	3O	3	O		2H3     	E304				 
	20081120		CE  	2008	11	20	2008FA0000777    	1	20081024	G	2820		FUEL LINE       			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					FUEL SYSTEM	CORRODED        	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	07	340SU	3808 				340A0979				THE FUEL CROSSFEED LINE LT TANK TO RT ENGINE, HAD CORRODED TO THE POINT OF LEAKAGE.  THE CORRODED AREA WAS UNDER THE CAB	IN FLOOR BEHIND THE CO-PILOT SEAT.  THE DUCTWORK FOR THE CABIN VENTILATION SYSTEM LAYS ON THE LINE THIS LOCATION.  THE C	ORROSION WAS LIMITED TO THE AREA OF CONTACT.  PIN HOLES HAD DEVELOPED ALLOWING A SMALL QUANTITY OF FUEL TO LEAK, NOT ENO	UGH TO DRIP, BUT ENOUGH TO SATURATE THE DUCT WORK AND PRODUCE A STRONG ODOR IN THE CABIN.  THE VENTILATION DUCT MUST BE 	MOVED FOR VISUAL INSPECTION.  IN ADDITION, WHEN THE LINE WAS REMOVED, THERE IS EVIDENCE OF ABRASION FROM CONTROL CABLES 	AT THE OTBD PORTION OF THE LINE.  THIS NEEDS TO BE INSPECTED AT THE NEXT OPPORTUNITY.  (K)	1	L	7	2 	3O	3	O		3A25    	E8CE				 
	20081120		CE  	2008	11	20	2008FA0000778    	1	20081029	G	5511	65320104	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000779    	1	20081029	G	5511	65320125	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000780    	1	20081029	G	5511	65320124	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000781    	1	20081029	G	5511	65320134	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000782    	1	20081029	G	5511	65320144	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000783    	1	20081029	G	5511	65320104	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000784    	1	20081029	G	5511	65320114	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000785    	1	20081029	G	5511	65320124	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000786    	1	20081029	G	5511	65320135	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000787    	1	20081029	G	5511	65320134	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000788    	1	20081029	G	5511	65320145	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000789    	1	20081029	G	5511	65320144	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000790    	1	20081029	G	5511	65320154	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	371QS					5600471				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 5 CRACKED RIBS ON THE RT SIDE AND 8 CRACKED RIBS ON THE LT SIDE WE	RE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFTE	R REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARRALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATEDIN AREAS NOT NORMALLY	 INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000791    	1	20081029	G	5511	65320104	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000792    	1	20081029	G	5511	65320114	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HLES BUT MOST OF THE CRACKS CONTINUED P	AST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY I	NSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000793    	1	20081029	G	5511	65320125	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000794    	1	20081029	G	5511	65320124	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000795    	1	20081029	G	5511	65320135	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000796    	1	20081029	G	5511	65320134	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000797    	1	20081029	G	5511	65320145	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATEDIN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000798    	1	20081029	G	5511	65320154	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000799    	1	20081029	G	5511	65320104	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000800    	1	20081029	G	5511	65320114	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000801    	1	20081029	G	5511	65320125	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000802    	1	20081029	G	5511	65320124	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000803    	1	20081029	G	5511	65320123	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000804    	1	20081029	G	5511	65320135	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000805    	1	20081029	G	5511	65320134	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000806    	1	20081029	G	5511	65320133	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000807    	1	20081029	G	5511	65320145	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000808    	1	20081029	G	5511	65320144	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000809    	1	20081029	G	5511	65320143	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000810    	1	20081029	G	5511	65320163	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000811    	1	20081029	G	5511	65320174	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS					5600329				WHILE PERFORMING THE PHASE 1-5 INSP, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STABILIZERS.	  AFTER REMOVAL OF THE TOP SKINS ON BOTH STABILIZERS, 8 CRACKED RIBS ON THE RT SIDE AND 13 CRACKED RIBS ON THE LT SIDE W	ERE FOUND.  ALL OF THE CRACKS WERE FOUND IN THE LOWER PORTION OF THE FLANGED AREAS OF THE RIBS IN THE CUT-OUT AREA.  AFT	ER REMOVAL OF THE RIVETS, SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED 	PAST THE RIVET HOLES.  THE CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY 	INSPECTED AND ACCESS IS VERY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000812    	1	20081029	G	5511	65320104	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000813    	1	20081029	G	5511	65320125	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000814    	1	20081029	G	5511	65320124	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000815    	1	20081029	G	5511	65320135	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000816    	1	20081029	G	5511	65320134	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000817    	1	20081029	G	5511	65320145	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000818    	1	20081029	G	5511	65320144	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000819    	1	20081029	G	5511	65320154	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000820    	1	20081029	G	5511	65320164	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000821    	1	20081029	G	5511	65320193	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000822    	1	20081029	G	5511	65320144	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000823    	1	20081029	G	5511	65320114	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000824    	1	20081029	G	5511	65320124	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000825    	1	20081029	G	5511	65320124	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000826    	1	20081029	G	5511	65320135	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000827    	1	20081029	G	5511	65320134	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000828    	1	20081029	G	5511	65320145	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000829    	1	20081029	G	5511		RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000830    	1	20081029	G	5511	65320154	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000831    	1	20081029	G	5511	65320164	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081120		CE  	2008	11	20	2008FA0000832    	1	20081029	G	5511	65320174	RIB             			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZ STAB	CRACKED         	B			JQ0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	363QS					5600536				WHILE PERFORMING PHASE 1-4 INSPECTIONS, CRACKS WERE NOTICED IN SEVERAL RIBS LOCATED INSIDE THE LT AND RT HORIZ STAB.  AF	TER REMOVAL OF THE TOP SKINS ON BOTH STAB, 10 CRACKED RIBS ON THE RT SIDE AND 11 CRACKS ON THE LT SIDE WERE FOUND.  ALL 	OF THE CRACKS WAS FOUND IN THE LWR PORTION OF FLANGED AREAS OF THE RIB IN THE CUT-OUT AREA.  AFTER REMOVAL OF THE RIBS, 	SOME OF THE CRACKS WERE FOUND TO BE GOING TO THE RIVET HOLES BUT MOST OF THE CRACKS CONTINUED PAST THE RIVET HOLES.  THE	 CRACKS WERE PARALLEL TO THE EDGE OF THE RIBS.  THE CRACKS WERE LOCATED IN AREAS NOT NORMALLY INSPECTED AND ACCESS IS VE	RY LIMITED.  (K)	2	L	7	2 	4F			RT	A22CE   					 
	20081124		EA  	2008	11	24	2008FA0000833    	2	20081101	G	7414	M3008	DISTRIBUTOR GEAR	SLICK       		CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					MAGNETO	DESTROYED       	D			DF2S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	4260Q	1186 			04070369	17260160				CONTACT PIN ON THE DISTRIBUTOR GEAR COMES LOOSE AND IS UNUSEABLE.  PLASTIC HOLDING IT ON IS CRACKED.  (K)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081126		GL  	2008	11	26	2008FA0000834    	2	20081106	G	7250	72165	TURBINE NOZZLE  								WILINT	FJ44  	FJ44        	66000	GL  					ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09		1858 					141224			WHILE UNDER GOING A CHECK 3 MAINTENANCE INSPECTION,  THE STIFFENING RING ON THE 1ST LOW PRESSURE TURBINE NOZZLE ON THIS 	ENGINE WAS FOUND SEPARATED AND TRAPPED BETWEEN THE 1ST LP TURBINE NOZZLE AND THE HIGH PRESSURE TURBINE NOZZLE.  NO PROBA	BLE CAUSE IS A SUSPECT MFG OPERATION.  HELD FOR INVESTIGATION. (K)									4	F			E3GL				 
	20081125		GL  	2008	11	25	2008FA0000835    	2	20080930	G	7313	23031938	DIAPHRAGM       								ALLSN 	250C  	250C20B     	03013	GL  					NOZZLE	CRACKED         	C			HEFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01		1568 					CAT34079			FLOURESCENT PENTRANT INSPECTION PRODUCED INDICATIONS AT 2 LOCATIONS ALONG BRAZING WHERE DIAPHRAGM AND OUTER RING ARE JOI	NED.  INDICATIONS ARE APPROXIMATELY 1.60 AND 2.50 INCHES LONG, APPROX 180 DEGREES APART.  VOIDS IN BRAZING ARE ALSO PRES	ENT AT 2 LOCATIONS.  (K)									3	U			E4CE				 
	20081125		CE  	2008	11	25	2008FA0000836    	1	20081120	G	2750		FLAP SYSTEM     			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ZONE 600	FAILED          	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			SW	99						17259899	L3814327A			ON FINAL APPROACH THE PILOT DECIDED TO EXECUTE A GO AROUND AND AS HE BROUGHT UP THE FLAPS TO THE 20 DEGREE SETTING THE R	T FLAP INBD ROLLER SUPPORT JAMMED IN THE FLAP TRACK ASSY AND THE FLAP RETRACTED CROOKED AND JAMMED AGAINST THE RT AILERO	N LEAVING THE RT AILERON STUCK IN THE UP POSITION AND CAUSING AN ASYMMETRICAL FLAP CONDITION WHICH CAUSED THE AIRPLANE T	O PULL TO THE RT.  WITH FULL LT PRESSURE ON THE YOKE AND WITH RUDDER THE PILOT WAS ABLE TO CONTROL THE AIRPLANE. THE PIL	OT WAS ABLE TO TURN LT AND WITHOUT FURTHER INCIDENT FLY THE PATTERN AND LAND THE AIRPLANE SAFELY.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081201		NM  	2008	12	1	2008FA0000838    	1	20081121	G	3610	7732873	PRECOOLER       			BOEING	767   	767222      	1385122	NM  										ZONE 400	FRACTURED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	767VA	77387	77387			21870				NR1 PYLON PRECOOLER CRACKED IN SEVERAL PLACES.  REMOVED AND REPLACED NR1 ENG PRECOOLER IAW MM 36-11-15. WORK PERFORMED O	N NR 35501 S/O 599197.					2	L	7	2 	4F			RT	A1NM    					 
	20081201		EU  	2008	12	1	2008FA0000839    	1	20081122	G	7700	NE00000133101	SENSOR          			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE1250299  		EU  					CRANKSHAFT	DIRTY           	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SW	99	490TS	244  				42AC090	020201763			FADEC CONTROLLED POWERPLANT/ HAD UNCOMMANDED POWER REDUCTION TO 75 PERCENT (3 SEPARATE WRITE-UPS) ACCOMPANIED BY MINOR E	NGINE SURGING AT VARIOUS TIMES DURING NORMAL CRUISE FLIGHT. MFG FIX WAS RE-DESIGNED FADEC SOFTWARE, THAT DID NOT ALLEVIA	TE THE PROBLEM. WHILE PERFORMING A CLUTCH PLATE INSPECTION THE AREA WAS CLEANED AS WELL AS THE CRANKSHAFT POSITION SENSO	RS, WHICH IS ONE OF THE FADECS SENSORY INPUTS. THIS ACTION SEEMED TO RESOLVE THE AFOREMENTIONED PROBLEMS. TO DATE THERE	 IS APPROX 23 HOURS OF ENGINE OPERATION TIME WITH NO REPEAT OF THE ISSUE. OTHER OPERATORS HAVE DESCRIBED HAVING THE SAME	 TYPE OF PROBLEM.	1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
	20081202		SW  	2008	12	2	2008FA0000840    	1	20081124	G	2400	MS902982	GROUND STUD     			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360*    	17025	SO  					AIRFRAME	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	13	305P	2847 				250524				AIRFRAME GROUND PLUG IN HAS NEVER BEEN CONNECTED TO AIRFRAME GROUND. BASE OF RECEPTACLE WAS INSULATED FROM AIRFRAME GROU	ND BY PRIMER ON METAL ANGLE. WE FOUND COMPLETE ISOLATION FROM GROUND POINT TO FUEL FILLER OPENING, NO GROUND ON OUR FUEL	ING OPERATIONS FOR PAST 3 YEARS. MFG SHOULD CHECK CONTINUITY ON AIRFRAME GROUND PORT AT MFG SINCE NO OTHER TIME IN LIFE 	OF ACFT IS IT REQUIRED TO CHECK.			1	L	7	1 	3O	3	O		2A3     	E9CE				 
	20081202		GL  	2008	12	2	2008FA0000841    	1	20081124	G	5210		LATCH           			DIAMON	DA40  	DA40        	2990002	GL  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCC2Y	HCC2YR1     	GL  	PAX DOOR	DISENGAGED      	P				B	A			EMER. DESCENT           	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	661DS	1050 				40600	L3241251A	CH39369B		AT 10500 FT IN CRUISE FLIGHT, GOT AN AUDIBLE "DING" ON THE G1000 WARNING AND THEN A LIGHT SAYING THAT A DOOR WAS OPEN. B	ACK DOOR HAD COME OPEN IN FLIGHT.  THE DOOR HAD BEEN SHUT AND THERE HAD BEEN NO WARNING DURING PRE-FLIGHT CHECK AND RUN-	UP.  WAS IN THE RT SEAT AND COULD NOT REACH THE DOOR UNTIL I UNDONE MY SEATBELT.  TRIED TO SHUT THE DOOR, BUT DUE THE DE	SIGN OF THE HANDLE, THERE IS NO WAY TO SHUT THE DOOR.  THE SAFETY LATCH WAS ABOUT TO LET GO AND I HELD ONTO THE HANDLE A	S LONG AS I COULD.  IT FINALLY GOT INTO THE AIR SCREAM AND WAS JERKED OUT OF MY HAND AND THEN THE DOOR DEPARTED THE AIRC	RAFT.  DECLARED AN EMERGENCY AND LANDED.	1	L	7	1 	3O	3	O	NT	A47CE   	E1CE	5	C	P920	 
	20081202		SW  	2008	12	2	2008FA0000842    	1	20081124	G	2897		GROUND WIRE     			BELL  	206   	206B3       	1181506	SW  										BOOST PUMP	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	304PD	6486 				4525				MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 	IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH	. GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681	-101.  OPS NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP.			1	G	7	1 	3U				H2SW    					 
	20081202		SO  	2008	12	2	2008FA0000843    	1	20081110	G	5414		COWLING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					ZONE 400	BROKEN          	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			SO	19	2772P	6938 	6905 			3240456				AFTER LIFTOFF, AT APPROX 250 TO 300 FEET AGL THE RT SIDE OF THE UPPER ENGINE COWLING CAME LOOSE AND BROKE OFF AT APPROX 	THE MIDDLE LT PORTION OF THE COWLING, FALLING TO THE GROUND.  THE ACFT HAD UNDERGONE A 100 HOUR INSP ON  THE ENGINE AT 6	905.8 HRS. OWNER STATED NO ADDITIONAL MAINT SINCE THAT TIME.				1	L	7	1 	3O	3	O		A3SO    	1E4				 
	20081202		SW  	2008	12	2	2008FA0000844    	1	20081124	G	2897		GROUND WIRE     			BELL  	206   	206B3       	1181506	SW  										BOOST PUMP	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	305PD	2853 				4586				MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 	IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH	. GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681	-101. OPERATION NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP.			1	G	7	1 	3U				H2SW    					 
	20081202		SW  	2008	12	2	2008FA0000845    	1	20081124	G	2897		GROUND WIRE     			BELL  	206   	206B3       	1181506	SW  										BOOST PUMP	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	306PD					4588				MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 	IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH	. GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681	-101. OPERATION NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP.			1	G	7	1 	3U				H2SW    					 
	20081201		SW  	2008	12	1	2008FA0000846    	1	20081124	G	2897		GROUND WIRE     			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20J     	03013	GL  					BOOST PUMP	MISSING         	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			WP	07	306PD	1990 				4588				MFG HAS REMOVED A GROUND WIRE FROM BOTH ELECTRIC BOOST PUMPS. GROUND HAS BEEN ON EARLIER MODELS, REMOVED SINCE SN: 4205 	IAW WIRING DIAGRAMS. CAUTION LIGHTS FOR BOOST PUMPS NOT OPERATIONAL SINCE NO GROUND AVAILABLE TO BASE OF PRESSURE SWITCH	. GROUND WIRE INSTALLED FROM MOTOR HOUSING TO BASE OF BOOST PUMP. MM SHOWS GROUND WIRE TO BASE OF BOOST PUMP 206-062-681	-101. OPS NORMAL AFTER GROUND ROUTED TO BASE OF BOOST PUMP.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081202		CE  	2008	12	2	2008FA0000847    	1	20081125	G	8011	S539800M015	SPRING          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					STARTER ADAPTER	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	5716V	14   	14   		CAS2234	TC990	272745R			STARTER ADAPTER P/N 635050-A4, STARTER SPRING FAILED.  STARTER ADAPTER OVERHAULED, RETURNED TO SERVICE AFTER OVERHAUL. P	ART SOLD, STARTER ADAPTER INSPECTED AND RETAGGED AND SOLD TO MFG. MAINT INSTALLED STARTER ADAPTER AND SPRING FAILED 14 H	OURS LATER.				1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
	20081202		EA  	2008	12	2	2008FA0000848    	2	20081119	G	7310	STD2048ORLW18733	HOSE            			CESSNA	182   	182         	2072702	CE  	LYC   	O540  	TIO540AK1A  		EA  					FUEL SYSTEM	DETERIORATED    	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			NM	09	72758	554  				T18208004	L1088361A			ENGINE LOST RPM AND PARTIAL POWER ON GO-AROUND FROM REJECTED LANDING.  ACFT THEN FLEW NORMAL PATTERN AND LANDED WITHOUT 	INCIDENT.  GROUND RUN-UP SHOWED NO ABNORMALITIES.  MAINT REMOVED INJECTOR NOZZLES.  NR 2 CYL NOZZLE WAS PLUGGED AND CONT	AMINANTS FOUND IN SEVERAL OTHER INJECTORS.  THE CONTAMINANTS APPEARED TO BE FLAKES FROM THE INSIDE OF AIR BLEED HOSES TO	 THE INJECTOR NOZZLES.  THE HOSES ARE HARDENED BY HEAT AND SHOW CRACKING; THEY ARE CHIPPED WHERE THEY SLIDE ONTO THE NOZ	ZLE TUBES.  WE INSTALLED NEW HOSES.  PERHAPS HOSE P/N LW-18737 SHOULD BE REPLACED AT 500 HOUR INTERVALS.		1	H	7	1 	3O	3	O	NT	3A13    					 
	20081201		SW  	2008	12	1	2008FA0000849    	1	20081101	G	2435	30B4521A	STARTER GEN     			NAMER 	T28C  	T28C        	6402509	SW  										ENGINE	FAILED          	B			XB2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	39FS					624480				STARTER GEN PREVIOUSLY HAD A FIELD FAILURE-COMPLETE MELT DOWN AFTER APPROX 12 FLIGHTS AFTER OVERHAUL.  IT WAS REPAIRED U	NDER WARRANTY AND REINSTALLED.  AFTER APPROX 4 FLIGHTS IT WOULD NOT CONSISTENTLY CARRY THE LOAD.  ACFT REGULATION/CHARGI	NG SYST CHECKED AND FOUND CORRECT.  THE INSP COVER ON THE GENERATOR WAS REMOVED AND DAMAGE TO THE COMMUTATOR WAS FOUND P	ROBABLY DUE TO THE PREVIOUS FAILURE.  INSP OF 1 SET OF BRUSHES REVEALED GROOVED FACES AND THE LACK OF PROPER BRUSH RUN A	T OVERHAUL.  AS STATED THIS IS 2ND FAILURE OF THIS ITEM IN A VERY SHORT TIME, THESE FAILURES ARE OBVIOUSLY DUE TO THE LA	CK OF PROPER PROCEDURES/ WORKMANSHIP BEING FOLLOWED.  (K)	1	L	7	1 	4R			RT	EXPA1L71					 
	20081201			2008	12	1	2008FA0000850    	4	20081024	G	2565		PIN             			BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					EVAC SLIDE	INSTALLED       	B			M4QR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	19	673BF	43   				23402				A SLIDE DEPLOYMENT OF THE RT AFT ENTRY DOOR OF THE ACFT WAS ATTEMPTED IN CONJUNCTION WITH A DITCHING DEMONSTRATION IN SU	PPORT OF OUR FAR PART 125 CONFORMITY ASSESSMENT BY FSDO - 25.  THE SLIDE DID NOT EXTRACT FROM THE DOOR BUSTLE AS THE DOO	R WAS OPENED.  UPON INVESTIGATION OF THE CAUSE OF THE FAILURE, IT WAS FOUND THAT THE GIRT BAR WAS NOT PROPERLY INSERTED 	INTO THE GIRT BAR CARRIER OF THE SLIDE AS CALLED OUT IN AMM 25-66-01, PAGE 405, STEP (15). THIS CONDITION WAS CORRECTED 	AND THE DOOR WAS CLOSED TO ATTEMPT SLIDE DEPLOYMENT AGAIN.  ON THE SECOND ATTEMPT, THE SLIDE PACK DID RELEASE FROM THE D	OOR AND DROPPED PROPERLY, HOWEVER IT DID NOT INFLATE.  THE IN-CABIN FA OPERATING THE DOOR ATTEMPTED TO MANUALLY INFLATE 	2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
	20081210		CE  	2008	12	10	2008FA0000851    	1	20081023	G	3260	12707332	WARNING SYSTEM  			CESSNA	210   	210N        	2073453	CE  										LANDING GEAR	MALFUNCTIONED   	B				H				DEACTIVATE SYST/CIRCUITS				N			FALSE WARNING             			CR	CRUISE         	1			SW	99	6621A	78   				21063559	821099R			WHILE FLYING THROUGH RAIN IN IFR CONDITIONS, THE LANDING GEAR NOT DOWN/LOCKED WARNING HORN SOUNDED FALSELY EVEN THOUGH T	HROTTLE WAS NOT RETARDED TO DESCENT CONFIGURATION.  AIRCREW PULLED WARNING HORN CIRCUIT BREAKER TO TEMPORARILY CANCEL TH	E HORN WHICH ALSO DEACTIVATES THE NORMAL FUNCTION OF THE STALL/GEAR WARNING SYSTEM.  THE HORN IS VERY LOUD INTERFERING W	ITH ATC COMMUNICATIONS DURING A CRITICAL PHASE OF FLIGHT.  TROUBLESHOOTING REVEALED THE THROTTLE SWITCH INPUT ON THE DUA	L WARNING UNIT IS HYPERSENSITIVE TO A HIGH RESISTANCE GROUND, I.E.  MOISTURE ACCUMULATION AT THE THROTTLE SWITCH TERMINA	L.	1	H	7	1 	3O				3A21    					 
	20081210		SO  	2008	12	10	2008FA0000852    	2	20081129	G	8550	ES48109	OIL FILTER      			CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300D       	17022	SO  					ENGINE	RUPTURED        	P				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SW	99	7830T	2    	2    			47430				ON 11/26/2008, APPROXIMATELY 1 MINUTE AFTER START-UP THE OIL FILTER RUPTURED RESULTING IN MASSIVE LOSS OF ENGINE OIL.  T	HE OIL FILTER WAS THE LAST OF FOUR THAT WERE PURCHASED ON 10/05/2006.  THE ENGINE WAS SHUT DOWN UPON NOTICE OF LOW OIL P	RESSURE AND HAS BEEN DETERMINED TO BE UNHARMED BY THE LOCAL AP MECHANIC.				1	H	7	1 	3O	3	O		3A12    	E253				 
	20081210		CE  	2008	12	10	2008FA0000853    	1	20081130	G	2421	ASG120001	ALTERNATOR      			CESSNA	303   	T303        	2073820	CE  										ENGINE	SHORTED         	D				H	D			DEACTIVATE SYST/CIRCUITS	RETURN TO BLOCK         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			SW	99	303ET	149  				T30300036	246242	840184		HAVE HAD MULTIPLE FAILURES, BOTH IN FLIGHT AND DURING MAINTENANCE GROUND OPERATIONS.  HOURS ON FAILED ALTERNATORS RANGE 	FROM AS LOW AS 30 TO A MAXIMUM OF 220 HOURS TIME IN SERVICE.  THE ONE COMMON FACTOR IN ALL FAILURES HAS BEEN THE DISCOVE	RY OF LOOSE HEX HEAD CASE BOLTS INSTALLED AND SAFETY WIRED BY MANUFACTURER.  THIS PROBLEM IS NOT RESTRICTED TO ONE SIDE 	ONLY, BOTH ENGINES DRIVE THE SAME ALTERNATOR WITH SAME PART NUMBER.			1	L	7	2 	3O				A34CE   					 
	20081219		GL  	2008	12	19	2008FA0000854    	2	20081201	G	7200	23038229	SPUR GEAR       			BELL  	206   	OH58A       	1181579	SW  	ALLSN 	250C  	250C20C     	03013	GL  					ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	306HP					7120794	AE405466			GAS PRODUCER TRAIN IDLER SPUR GEARSHAFT PN: 23038229.  SHEARED IN HALF, PRODUCING METAL IN OIL.  WHEN TECHNICIAN DISASSE	MBLED GEARBOX FOUND THAT GEARSHAFT WAS THE SOURCE OF THE METAL					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081219			2008	12	19	2008FA0000855    	2	20081201	G	7210	23038229	SPUR GEAR       			BELL  	206   	OH58A       	1181579	SW  										GEARBOX	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	306HP	1954 	162  			7120794				GAS PRODUCER TRAIN IDLER SPUR GEARSHAFT PN: 23038229. SHEARED IN HALF, PRODUCING METAL IN OIL.  WHEN TECHNICIAN DISASSEM	BLED GEARBOX FOUND THAT GEARSHAFT WAS THE SOURCE OF THE METAL					1	G	7	1 	3U				H2SW    					 
	20081202		CE  	2008	12	2	2008FA0000856    	1	20081124	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  										LANDING GEAR	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8252T	184  				CE1545				PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE UP POSITION.  THE GEAR FAILED TO RETRACT, 3-4 MINUTES LATER THE PI	LOT REPORTED THE GEAR CAME UP ON ITS OWN.  PILOT THEN PUT THE GEAR IN THE DOWN POSITION AND RETURNED TO BASE.  PROBABLE 	CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE.  (K)				1	L	7	1 	3O				3A15    					 
	20081203		EA  	2008	12	3	2008FA0000857    	2	20080314	G	7414		SHAFT           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					MAGNETO	BROKEN          	B			ZF7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9126M	110  			07071657	2816104	RL1306439A			ROTATING MAGNET SHAFT BROKE IN HALF.  BROKE DIRECTLY BELOW WHERE THE ROTOR CAM GOES.  (K)						1	L	7	1 	3O	3	O		2A13    	E274				 
	20081202		GL  	2008	12	2	2008FA0000858    	2	20081118	G	7412	106149504	EXCITER         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					POWERPLANT	INTERMITTENT    	B			BJFR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	23	739NM					51124				ENGINE HAD AN INTERMITTENT DELAYED LIGHTOFF CAUSING HOT STARTS.  REPLACING THE IGNITION EXCITER CORRECTED THE PROBLEM. T	HE DEFECTIVE EXCITER WAS FOUND TO HAVE A LOOSE STUD WHERE THE INPUT VOLTAGE IS APPLIED.  SUSPECT THIS WAS CAUSING A LOW 	OUTPUT VOLTAGE.  IT APPEARS THE NUT ON THE STUD WAS OVERTORQUED DURING INSTALLATION, CAUSING THE STUD TO LOOSEN.  (K)				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081202		CE  	2008	12	2	2008FA0000859    	1	20081113	G	3211		SUPPORT         			CESSNA	414   	414A        	2075907	CE  										TRUNNION	CRACKED         	B			E5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	901BA	6946 				414A0232				ON THE FWD TRUNNION SUPPORT, A CRACK WAS LOCATED ON THE LT AND RT SIDES. EDDY CURRENT INSP USED.  (K)						1	L	7	2 	3O				A7CE    					 
	20081203		SO  	2008	12	3	2008FA0000860    	1	20081118	G	3240	16405700	BRAKE DISC      			PIPER 	PA23  	PA23250     	7102308	SO  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	63954	238  				277854085				THE DISC WAS FOUND DURING ROUTINE MAINTENANCE TO HAVE A RADIAL CRACK EXTENDING FROM APPROX .5 INCH FROM THE OUTER CIRCUM	FERENCE TO OUTER EDGE AND ABOUT HALF WAY THROUGH THE THICKNESS OF THE DISK. (K)					1	L	7	2 	3O				1A10    					 
	20081203		GL  	2008	12	3	2008FA0000861    	1	20081117	G	8011	14924LS	STARTER         			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360M1A    		NE  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	203US					40903	L3393551E			STARTER HOUSING BROKE AT FRONT CASTING BREAKING OFF FRONT MOTOR SHAFT SUPPORT BEARING WHICH ALLOWED STARTER SHAFT TO DRO	P DOWN PREVENTING POSITIVE ENGAGEMENT OF STARTER TO FLY WHEEL.  CONVERSATION WITH AIRCRAFT MFG NOTED THIS IS NOT AN ISOL	ATED INCIDENT AND THERE ARE DEFECTS IN THE FRONT CASTINGS.  (K)				1	L	7	1 	3O	3	O	NT	A47CE   	1E10				 
	20081202		CE  	2008	12	2	2008FA0000862    	1	20081114	G	5743	10112002584	BRACKET         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  					RT MLG SUPPORT	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	40R					BC07				A 1.4 INCH LONG CRACK WAS FOUND IN THE RT MLG DRAG BRACE SUPPORT BRACKET DURING INSPECTION.  DURING THE REMOVAL OF THE P	ART (2) ADDITIONAL CRACKS 1.4 INCH LONG WERE FOUND AROUND 4 FASTENERS WHERE THE BRACKET ATTACHES TO THE MAIN SPAR WEB.  	WHEN INSTALLED, THE AREA AROUND THESE 4 FASTENERS IS OBSCURED BY THE MLG DRAG BRACE FWD ATTACH FITTING (PN 50-120201-5).	  THE PART WAS REPLACED WITH A NEW BRACKET.  NO CRACKS WERE FOUND N THE SPAR WEB.  SUSPECT CRACKS CAUSED BY FATIGUE AND 	OR HARD LANDINGS.  (K)		1	L	7	2 	4T	3	T		A24CE   	E2NE				 
	20081203		EA  	2008	12	3	2008FA0000863    	1	20081110	G	6320	269A510351	PINION GEAR     			SCWZER	269   	269D        	8059501	EA  	ALLSN 	250C  	250C20W     		NE  					TRANSMISSION	WORN            	D			BS2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	297BJ				S0005	0029	CAE845042			DURING SHUT-DOWN, PILOTS REPORTED CLUNKING NOISE.  UPON FURTHER INSPECTION, NOISE WAS LOCATED AT UPPER PULLEY SPRAG CLUT	CH AREA.  REMOVED UPPER PULLEY AND FOUND M/R TRANSMISSION INPUT PINION (PN:269A5103-51) WORN EXCESSIVELY DUE TO LOOSE AF	T PINION NUT.  PROBABLE CAUSE OF AFT PINION NUT LOOSENING IS SB DB-019 (CORROSION PROTECTION OF INPUT PINION SPLINES).  	POSSIBLE EXCESSIVE APPLICATION OF ZINC-CHROMATE PRIMER TO INPUT PINION CAUSED IMPROPER CLAMP-UP DURING TORQUING PROCEDUR	E.  (K)		1	G	7	1 	3U	3	U	0	4H12    	E4CE				 
	20081203		CE  	2008	12	3	2008FA0000864    	1	20081108	G	3233	15232003	ACTUATOR        			CESSNA	500   	560CESSNA   	2076750	CE  										NLG	LEAKING         	B			FZPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	45KB					5600191				ON NOV 6, THE ACFT EXPERIENCED FOR THE THIRD TIME, LANDING GEAR RETRACTION PROBLEMS.  IT WAS FLOWN TO REPAIR STATION FOR	 LANDING GEAR MAINTENANCE.  THE ACFT WAS JACKED, AND A GEAR RETRACT CHECK WAS ABLE TO DUPLICATE THE INFLIGHT PROBLEM.  T	ROUBLESHOOTING REVEALED THAT THE NOSE GEAR ACTUATOR WAS LEAKING INTERNALLY, FILLING THE NITROGEN EMERGENCY EXTENSION SYS	TEM WITH HYD FLUID.  THIS RESULTED IN A HYDRAULIC LOCK DURING THE NORMAL LANDING GEAR RETRACTION CYCLE, THUS PREVENTING 	ONE OR MORE MAIN LANDING GEAR FROM ACHIEVING AN UP AND LOCKED POSITION.  APPROX 1.5 PINTS OF HYD FLUID WERE DRAINED FROM	 THE EMERGENCY EXTENSION LINES AND COMPONENTS. ADDITIONALLY, THE EMERGENCY EXTENSION BREATHER CHECK VALVE PN P48-389 HAD	2	L	7	2 	4F			RT	A22CE   					 
	20081203		CE  	2008	12	3	2008FA0000865    	1	20080920	G	6220	368200119	ROD             			BEECH 	33    	F33A        	1151425	CE  										NOSE GEAR	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6431X	2333 				CE1005				ON LANDING, PILOT OBSERVED THREE GREEN LIGHTS.  ON TOUCHDOWN AND ROLL OUT NOSE GEAR COLLAPSED INTO NOSE GEAR WHEEL WELL.	  UPON INVESTIGATION GEAR TRANSMISSION WAS DOWN AND LOCKED.  NOSE GEAR ROD END BENT FWD SIDE OF AFT RETRACT ROD.  NOSE G	EAR ROD END CAN BE ACCESSED IN WHEEL WELL AFT RT SIDE ATTACHED TO KEEL UNDER SHIELD.  THIS IS A GOOD PLACE TO LOOK AT HA	RD LANDINGS AND DURING ANNUAL INSPECTIONS.  PILOT INTERVIEWED AND SAID HE DID NOT HAVE HARD LANDING OR PORPOISE ACFT.  P	N OF ROD IS 36-820011-9, PN FOR ROD END IS ANDE5-323.  (K)		1	L	7	1 	3O				3A15    					 
	20081203		CE  	2008	12	3	2008FA0000866    	1	20081117	G	7120	26510088	MOUNT           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					ENGINE	CRACKED         	B			MT9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	9750B	12988				208B0100	PCE17240			THE CENTER ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS.  (K)						1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081202		CE  	2008	12	2	2008FA0000867    	1	20081117	G	7120	26510127	MOUNT           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					LT ENGINE	CRACKED         	B			MT9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	9750B					208B0100				THE LT ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS.  (K)						1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081202		SO  	2008	12	2	2008FA0000868    	1	20081121	G	5340	67271800	BRACKET         			PIPER 	PA28  	PA28R201    	7102816	SO  										NLG ACTUATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	4142N	16129				2837012				NOSE GEAR ACTUATOR AFT ATTACH POINT CRACKED.  PROBABLE CAUSE IS TIME IN SERVICE.  CHANGE AT A REASONABLE TIME.  (K)						1	L	7	1 	3O				2A13    					 
	20081202		SO  	2008	12	2	2008FA0000869    	1	20081029	G	5340	67271800	BRACKET         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG ACTUATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	4155G					2837017				NOSE GEAR ACTUATOR AFT ATTACH POINT CRACKED.  PROBABLE CAUSE IS TIME IN SERVICE.  CHANGE AT A REASONABLE TIME.  (K)						1	L	7	1 	3O	3	O		2A13    	1E10				 
	20081203			2008	12	3	2008FA0000870    	1	20081028	G	8011	774960A4	STARTER         																	ENGINE	MISMANUFACTURED 	D			SI3R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	63		425  								FOUND BAFFLES INSTALLED INCORRECTLY, INCORRECT HOUSING INSTALLED AND VARIOUS INTERNAL PARTS.  (K)																			 
	20081203		CE  	2008	12	3	2008FA0000871    	1	20081101	G	5100		SPAR            			BEECH 	18    	H18         	1151012	CE  	PWA   	R985  	R985*       	52008	NE  					UNKNOWN	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	6GJ					BA633				HAVE JUST HAD THE SPAR X-RAY ACCOMPLISHED IAW AD75-27-09 R2.  UPON REVIEW OF THE X-RAYS IT WAS DETERMINED THAT THERE WAS	 A CRACK.  IT SEEMS THIS CRACK OF A VERY SIMILAR ONE WAS PREVIOUSLY REPAIRED AND THAT REPAIR IS IN QUESTION AS WELL.  (K	)				1	L	7	2 	3R	3	R		A765    	5E1				 
	20081202		EA  	2008	12	2	2008FA0000874    	2	20081118	G	7414	M3820	DISTRIBUTOR     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MAGNETO	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	63954	881  				277854085				SUBJECT PART APPEARS TO HAVE NOT RETAINED ITS LOWER BEARING THAT SUPPORTS THE DISTRIBUTOR GEAR.  THE PART WAS FOUND TO B	E BURNED AND THE BEARING HOLE MISSING THE BEARING AND ROUNDED OUT WHICH CAUSED THE MAGNETO TO FAIL AND PREVENTED ENGINE 	STARTUP.  JUST PRIOR TO THIS, ENGINE STARTUP HAD BEEN DIFFICULT, HOWEVER, MAG DROP AND PERFORMANCE WERE NORMAL.  (K)				1	L	7	2 	3O	3	O		1A10    	1E4				 
	20081203		SO  	2008	12	3	2008FA0000875    	1	20081118	G	3240	16405700	BRAKE DISC      			PIPER 	PA23  	PA23250     	7102308	SO  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	63954	277  				277854085				THE DISC WAS FOUND DURING ROUTINE MAINTENANCE TO HAVE A RADIAL CRACK EXTENDING FROM APPROX .75 INCH FROM THE OUTER CIRCU	MFERENCE TO OUTER EDGE AND ABOUT HALF WAY THROUGH THE THICKNESS OF THE DISC.  (K)					1	L	7	2 	3O				1A10    					 
	20081202		CE  	2008	12	2	2008FA0000876    	1	20081117	G	3240	6364106	BRAKE CABLE     			CESSNA	525   	525B        	2076616	CE  										LT BRAKE	FAILED          	B			JVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	92MA					525B0048				LET ACFT SIT OVER NIGHT WITH PARKING BRAKE APPLIED AND FOUND BRAKE SYS TO STILL HAVE 700 PSI IN BRAKE SYS.  RELEASED PAR	KING BRAKE AND FOUND THAT THE LT BRAKE STILL HAD 160 PSI RESIDUAL PRESSURE AND RT SIDE HAD ZERO RESIDUAL PRESSURE.  VERI	FIED RT WHEEL ASSY WOULD ROTATE, CHECK LT SIDE AND LT WHEEL ASSY WOULD NOT ROTATE.  INSPECTED INSIDE PORTION OF BRAKE ME	TERING VALVE IN CABIN AND NOTICED THAT THE LT ACTUATION CABLE CLEVIS END COULD GET HOOKED ON EDGE OF CABLE BALL END.  WH	EN THAT HAPPENS 160 PSI REMAINS ON LT BRAKE.  WHEN CABLE IS POSITIONED PROPERLY LT BRAKE HAS NO RESIDUAL PRESSURE ON GAU	GE AND LT WHEEL ROTATES.  OBTAINED NEW AFT BRAKE CABLES FROM MFG AND MODIFIED IAW ENGINEERING CO NR 525-1495.  REMOVED O	1	L	7	2 	4F			RT	A1WI    					 
	20081203			2008	12	3	2008FA0000877    	4	20081120	G	2360		GROUND STUD     			CESSNA	510   	510         	2076617	CE  	PWC   	PW615 	PW615FA     	52282	NE  					RT WING	LOOSE           	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	551WH					5100055				ADJACENT TO RT WING ACCESS PANEL 623DB THERE IS A GROUNDING POINT TO GROUND THE ACFT DURING FUELING OR WHILE PERFORMING 	MAINTENANCE.  IN AN ATTEMPT TO GROUND TO ACFT IN ORDER TO PERFORM MAINT, WE FOUND THE GROUNDING JACK MISSING.  PANEL 632	DB WAS REMOVED AND UPON FURTHER INSP THE PARTS WERE FOUND FLOATING AROUND INSIDE THIS AY WHICH ALSO HOUSES THE AILERON C	ONTROL SECTOR.  SOME TYPE OF SAFETY SHOULD BE INCLUDED ON GROUNDING JACK TO PREVENT IT FROM COMING APART AND POTENTIALLY	 JAMMING THE AILERON.  (K)		1	L	7	2 	4F	4	F	RT	A00014WI	E00073EN				 
	20081217		SW  	2008	12	17	2008FA0000878    	1	20081127	G	3220		TUBE            			MOONEY	M20   	M20F        	5870214	SW  										NLG	BROKEN          	G				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SO	11	6829V	3000 				220012				PILOT STATED THAT HE HEARD A LOUD SOUND  DURING THE TAKE OFF ROLL OFF OF A GRASS STRIP AND THE ACFT BEGAN TO "HANDLE DIF	FERENTLY".  HE CONTINUED TO ACCELERATE BRIEFLY AND THEN DECIDED TO ABORT THE TAKE-OFF.  INCIDENT INVESTIGATION FOUND ACF	T ON ITS NOSE WITH THE NOSE LANDING GEAR FOLDED BACK UNDERNEATH THE ACFT.  INSPECTION REVEALED THAT THE TUBING OF THE NL	G LEG ASSEMBLY WAS BROKEN.  THERE WERE POSSIBLE STRESS FRACTURES AT THE WELS POINTS ON BOTH SIDES OF THE STRUCTURE.			1	L	7	1 	3O				2A3     					 
	20090107		SW  	2009	1	7	2008FA0000879    	1	20081127	G	3220	540004501	LEG ASSY        			MOONEY	M20   	M20F        	5870214	SW  										NLG	BROKEN          	D				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			SO	11	V6829	3000 				220012				PILOT STATED THAT HE HEARD A LOUD NOISE DURING TAKE-OFF AND THAT THE AIRCRAFT BEGAN TO "HANDLE DIFFERENTLY." HE CONTINUE	D TO ACCELERATE BRIEFLY, LIFTED OFF AND THEN DECIDED TO ABORT THE TAKEOFF.  THE ACFT CAME TO REST ON ITS NOSE WITH THE N	OSE L/G FOLDED BACK BENEATH THE ACFT. INSP OF THE NOSE GEAR REVEALED THAT THE NLG LEG TUBING HAD BROKEN AT THE WELD POIN	TS ON THE UPPER ENDS OF THE TUBING. CLOSER INVESTIGATION SHOWED POSSIBLE FATIGUE CRACKS AT THE FWD PORTION OF THE WELDED	 JOINTS.		1	L	7	1 	3O				2A3     					 
	20090106		GL  	2009	1	6	2008FA0000880    	1	20081122	G	7931	12635002	SENSOR          			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					OIL SYSTEM	DEFECTIVE       	G				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			SO	19	212LV	678  	678  			1547	360009			SENSOR PRODUCED A FALSE HIGH OIL PRESSURE INDICATION DURING ACFT APPROACH TO AIRPORT. PROBABLE CAUSE WAS INTERNAL FAILUR	E, RECOMMENDATIONS TO PREVENT RECURRENCE ARE UNAVAILABLE, AS THE FREQUENCY OF THIS TYPE OF OCCURRENCE HAS BEEN VERY LOW.					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
	20090106		SO  	2009	1	6	2008FA0000881    	2	20081209	G	7414	4310	MAGNETO         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					LEFT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	293DC	22   	22   			C0193	824561R			MAGNETO, PN 4310, SN 08063188. DELIVERED NEW WITH APPLICABLE SB, SB3-08A. AFTER 21.6 HOURS COMPLIANCE WITH SB3-08A FOUND	 PART FAILED.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
	20090107		SW  	2009	1	7	2008FA0000882    	1	20081209	G	2710	473501	BELLCRANK       			GULSTM	112   	112A        	7630302	SW  										ZONE 500	MISREPAIRED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	1420J	1560 	1560 			420				EXCESSIVE AILERONS T/E FREE PLAY. SUSPECTED AIL SYS CUMULATIVE WEAR. UPON FURTHER CLOSE VISUAL INSP, FOUND AILERONS BELL	CRANK ASSY, PIVOT BRG HSG SECURED TO BELLCRANK PLATE WITH (3 EACH) BLIND FASTENERS. PROTRUDING HEAD FASTENERS WERE FOUND	 LOOSE AND EXHIBITING BLACK POWDERY RESIDUE AT FASTENER'S PROTRUDING HEAD PERIMETER, SUGGESTING BRINELLING IS OCCURRING 	ABOUT UPSET FASTENER HOLLOW SHANK OD AND BELLCRANK PLATE FASTENER HOLE SURFACE. ALL SUBJECT FASTENER'S DRIVE STEEL PINS 	WERE FOUND NOT TO HAVE LIBERATED FROM FASTENER HOLLOW SHANK ID.  REPLACED PIVOT BEARING HOUSING ASSY P/N MS20218-1 DUE W	ORN AND REINSTALLED/SECURED SAME WITH SOLID AD RIVETS. COMMANDER IPC PAGE 2-195 ITEMS 25, 27 BELLCRANK ASSY PIVOT BEARIN	1	L	7	1 	3O				A12SO   					 
	20090107		EA  	2009	1	7	2008FA0000884    	2	20081210	G	7322	229164	DISCHARGE TUBE  			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					FUEL PUMP	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	64204	669  	669  			75534				DURING 100 HR INSP, FOUND THE PUMP DISCHARGE TUBE ON A MA-4SPA LOOSE. THIS IS THE THIRD SUCH FIND. OTHER ACFT HAVE HAD T	HE PUMP DISCHARGE TUBE MISSING AND FOUND AT THE BOTTOM OF THE CARB AIRBOX.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20090107		CE  	2009	1	7	2008FA0000885    	1	20081211	G	3250	66426438	JAM-NUT         			CESSNA	560   	560XL       	2076702	CE  										STEERING BUNGEE	LOOSE           	D				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SO	13	669TT	740  				560XL5684				DURING ALL FLIGHT REGIMES (CLIMB/CRUISE/DESCENT) CREW FELT RESISTANCE WHEN LT RUDDER PEDAL WAS DEPRESSED. NO CHANGE IN F	EEL WITH LANDING GEAR POSITION (UP OR DOWN). ON GROUND RESISTANCE COULD NOT BE FELT, HOWEVER ACFT WOULD PULL LT WHILE TA	XIING. INITIAL FINDINGS REVEALED THE JAM NUT ON THE NOSE STEERING BUNGEE ASSY HAD BACKED OFF AND THE CLEVIS END OF THE B	UNGEE HAD TURNED INTERNALLY CAUSING THE OVERALL LENGTH TO INCREASE. NOT KNOWING WHAT IF ANY INTERNAL DAMAGE WAS DONE TO 	THE SPRING, THE DECISION WAS MADE TO REPLACE THE NOSE STEERING BUNGEE WITH A NEW UNIT. THE BUNGEE WAS INSTALLED AND THE 	AND THE STEERING SYS WAS RIGGED IAW AMM. ACFT WAS RELEASED FOR TEST FLIGHT, NO RESISTANCE WAS FELT IN THE RUDDER, AND DU	2	L	7	2 	4F			RT	A22CE   					 
	20090106		NE  	2009	1	6	2008FA0000886    	2	20081111	G	8530		CYLINDER        			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540J2B   	 	NE  	HARTZL	HCC2Y	HCC2Y*      	GL  	ENGINE	SEPARATED       	D				K				NONE                    				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			EA	09	801JK		787  			318012014	L528061A	FH998		PILOT NOTED REDUCTION OF PWR, THEN VIBRATION IN CRUISE FLIGHT. VISUAL INSP REVEALED NR1 CYL INTAKE TUBE SEPARATED FROM S	UMP INLET AND WEDGED APPROX 1 INCH AFT OF INLET.  FUEL INJECTOR LINE BROKE AT INJECTOR. BOTTOM (2) CYL HOLD DOWN STUDS B	ROKE AND (1) BOTTOM, (1) TOP HOLD DOWN NUTS BACKED OFF. SUSPECT CYL HEAD SEPARATION.				1	L	7	1 	3O	3	O	RT	A20SO   	E14EA	5	C	P920	 
	20081217			2008	12	17	2008FA0000887    	4	20081028	G	2211	GFC700	AUTOPILOT SYS   			CESSNA	510   	510         	2076617	CE  											MALFUNCTIONED   	P				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			AP	APPROACH       	1			SW	99	510AZ	20   				510124				WHEN A DISCREPENCY BETWEEN THE NAVDATA DATABASE & ACTUAL IMPLEMENTATION OF A LOCALIZER NAVAID, GFC700 WILL NOT INTERCEPT	 & TRACK LOCALIZER SIGNAL CORRECTLY.  IT EITHER FLIES THROUGH COURSE OR WILL ACTIVATE LOC MODE & IMMEDIATELY TURN OFF CO	URSE.  AFCS APPEARS TO REFERENCE LOCALIZER COURSE FROM DATABASE RATHER THAN SELECTED COURSE ON HSI.  FIRST DISCOVERED ON	 ASE LOC DME A APPROACH LAST APRIL.  NAVDATA HAD INCORRECT COURSE OF 120 FOR I-PKN LOCALIZER.  I-PKN TUNED, HSI WOULD AU	TO-SET COURSE TO 120.  THE PILOT CAN TURN THE NEEDLE TO THE CORRECT COURSE OF 300, AND THE HSI WILL PROVIDE CORRECT SENS	ING.  AUTOPILOT WILL NOT CAPTURE THAT COURSE & WILL FLY RIGHT THROUGH LOCALIZER TOWARD TERRAIN.  MANUFACTURERS AND FAA/N	1	L	7	2 	4F			RT	A00014WI					 
	20081219		CE  	2008	12	19	2008FA0000888    	1	20081215	G	2751	DT2RA7	SWITCH          			BEECH 	90    	C90         	1152913	CE  										TE FLAPS	BENT            	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	964G	7692 				LJ1007				THE UP TRAVEL SWITCH ON THE RT FLAP FAILED TO TRIP UPON FLAP RETRACTION.  THIS CAUSED THE FLAP MOTOR TO CONTINUE TO RUN 	ALTHOUGH THE FLAP WAS ALREADY FULLY RETRACTED.  THE MOTOR OVERHEATED AND STARTED GENERATING SMOKE.  THE ACFT WAS ON THE 	GROUND, TAXIING FOR TAKEOFF WHEN THIS WAS DISCOVERED.  THE ACFT RETURNED TO THE RAMP.  UPON INSPECTION BY MX STAFF IT WA	S DISCOVERED THAT THE ARM ON THE FLAP UP TRAVEL SWITCH WAS BENT (CAUSE UNKNOWN.)  THIS PREVENTED THE SWITCH FROM CLOSING	.  A CAREFUL EXAMINATION OF THE AREA COULD NOT REVEAL WHAT CAUSED THE ARM TO BEND.  SPECULATION IS THAT PERHAPS IT WAS R	ELATED TO ICE OR FOD DEBRIS.	1	L	7	2 	3T				3A20    					 
	20081230		EU  	2008	12	30	2008FA0000889    	1	20081119	G	6520	4639306038	PINION GEAR     			BOLKMS	105   	BO105LSA3   	5626020	EU  										TAIL ROTOR DRIVE	DEFORMED        	W			ZF6Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	315LS					2033				THE MAIN TRANSMISSION WAS DELIVERED FOR OVERHAUL.  THERE WAS NO NOTICE ABOUT AN INCIDENT OR A CHIP WARNING.  CHIP DETECT	OR AND OIL FILTER WERE CLEAN.  AT THE BEGINNING OF THE DISASSEMBLY, MECHANIC NOTED THAT THE TAILROTOR DRIVE DIDNT MOVE 	WHEN THE INPUT FLANGE WAS TURNED.  AFTER REMOVING THE UPPER HOUSING, A SEVERE DAMAGE OF THE TAIL ROTOR DRIVE PINION AND 	THE ASSOCIATED ROLLER BEARINGS WAS DETECTED.  THE BEARING WAS CRACKED AND THE TEETH OF THE PINION WERE SEVERELY DEFORMED	. THERE WERE MANY METAL CHIPS INSIDE THE GEARBOX.  (K)		1	G	7	2 	3U				H3AU    					 
	20081222		EU  	2008	12	22	2008FA0000890    	1	20081119	G	6500	4639306006	BEARING         			BOLKMS	105   	BO105LSA3   	5626020	EU  										TAIL ROTOR DRIVE	CRACKED         	W			ZF6Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	315LS	603  				2033				MAIN TRANSMISSION WAS DELIVERED FOR O/H. THERE WAS NO NOTICE ABOUT AN INCIDENT OR A CHIP WARNING.  CHIP DETECTOR AND OIL	 FILTER WERE CLEAN.  AT THE BEGINNING OF THE DISASSEMBLY, THE MECHANIC NOTED THAT THE TAILROTOR DRIVE DID NOT MOVE WHEN 	THE INPUT FLANGE WAS TURNED.  AFTER REMOVING THE UPPER HOUSING, A SEVERE DAMAGE OF THE TAIL ROTOR DRIVE PINION AND THE A	SSOCIATED ROLLER BEARINGS WERE DETECTED.  THE BEARING WAS CRACKED, AND THE TEETH OF THE PINION WERE SEVERELY DEFORMED.  	THERE WERE MANY METAL CHIPS INSIDE THE GEARBOX. (K)		1	G	7	2 	3U				H3AU    					 
	20081229		EU  	2008	12	29	2008FA0000891    	1	20081111	G	6310		COUPLING        			AEROSP	AS355 	AS355N      	8680818	EU  	TMECA 	ARRIUS	ARRIUS1A    		NE  					MAINTRANSMISSION	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	05	766AM					5601	21252126			ENGINE TO MAIN TRANS COUPLINGS FOUND TO BE INCORRECTLY ASSEMBLED.  THS WAS FOUND DURING A PRE-FLIGHT INSP.  THE COUPLING	S HAVE NOW BEEN ASSEMBLED CORRECTLY.  (K)					1	G	7	2 	3U	3	U	RT	H11GU   	E34NE				 
	20081230		CE  	2008	12	30	2008FA0000892    	1	20081001	G	2510		CLEVIS PIN      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					PILOT SEAT	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	75743					17267920				CLEVIS PIN THAT SUPPORTS BACK OF PILOTS SEAT WORN OVER .2500 THRU.  THIS PIN SLIDES IN A CURVED PORTION OF THE LOWER FRA	ME OF THE SEAT.  PROBLEM PARTS ARE CLEVIS PINS THAT SUPPORT THE SEAT BACK ON NR (2), (BELLCRANK).  THE BELLCRANK IS WELL	 WORN IN THE CURVED SECTION AND FILING INTO THE CLEVIS PIN.  IF THIS PIN FAILS, THE BACK-REST OF THE SEAT WILL PARTIALLY	 DROP OFF OR POSSIBLY COMPLETELY DROP OFF WITH OBVIOUS RESULTS.  MY SOLUTION WILL BE TO ROUND-OFF THE CURVE IN THE BACK 	OF THE BELLCRANK, SMOOTH IT WELL AND MAKE A STEEL ROLLER TO FIT INTO THE AREA OF THE CLEVIS PIN WHERE THE BELLCRANK WEAR	S ON IT.   JUST PERIODICALLY REPLACING THE CLEVIS PIN SHOULD SUFFICE UNLESS THE COARSE WEARING IN THE BELLCRANK IS OBSER	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20090107		NE  	2009	1	7	2008FA0000893    	2	20081217	G	7314	2PR600CWT	PUMP            			DOUG  	DC3   	C47         	3021461	WP  	PWA   	R1830 	R183092     	52020	NE  					LT ENGINE FUEL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	19	982Z	163  	163  			12947	438796			LT ENG FUEL PUMP DEVELOPED LEAK THROUGH THE BLEED HOLE IN A PLUG INSTALLED ON THE PRESSURE ADJUSTMENT PORTION OF THE PUM	P.  SYS WAS PRESSURIZED BY THE ELECTRIC FUEL PRESSURE BOOST PUMP AND A LEAK WAS DETERMINED TO BE APPROX (1) DROP PER SEC	OND AT A PRESSURE OF 18 PSI.				2	L	7	2 	4R	4	R		A669    	5E4				 
	20090106		SO  	2009	1	6	2008FA0000894    	2	20081215	G	7314	6467683A1	PUMP            			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	SHEARED         	E			WNHA	C				ABORTED TAKEOFF         				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			WP	25	5340Y	2    	2    			21064173	289648			ON SECOND TEST FLIGHT AFTER FACTORY REBUILT ENG INSTALLATION, ENG QUIT DURING TAKEOFF, JUST AFTER LIFTOFF, ALTITUDE LESS	 THAN 5 FT AGL. PILOT LANDED ACFT AND ROLLED OUT WITHOUT FURTHER INCIDENT. DURING THIS EVENT, PILOT REPORTED THAT AT TAK	EOFF INITIATION, POWER SETTINGS WERE " NORMAL, SMOOTH, AND HEALTHY." AT ACFT ROTATION (65-70 KNOTS), PILOT REPORTED MANI	FOLD PRESSURE AND FUEL FLOW DECREASED STEADILY AS ENGINE FALTERED, THEN QUIT COMPLETELY.  TOWED ACFT TO MAINT AREA. ENG 	PROMPTLY RESTARTED BUT QUICKLY FALTERED. WITH PROMPT USE OF AUXILIARY FUEL PUMP ENGINE WAS ABLE TO KEEP RUNNING. INSPECT	ED ENG AND FOUND ENG DRIVEN FUEL PUMP DRIVE SHAFT SHEARED. CURRENTLY IN CONTACT WITH MFG ABOUT THE INCIDENT.	1	H	7	1 	3O	3	O		3A21    	E8CE				 
	20090107		NM  	2009	1	7	2008FA0000895    	1	20081212	G	6310	A1902	BELT            	ROBSIN      		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					CLUTCH ASSY	DEFECTIVE       	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	23	558LA	1968 				3153	L3771936A			THE PILOT REPORTED A CLUTCH LIGHT COMING ON FOR MORE THAN 5 SECONDS, FOLLOWED THE PROCEDURES IN THE POH AND MADE A PRECA	UTIONARY LANDING. UPON VISUAL INSP IT WAS DEFECTED THAT ONE OF THE DRIVE BELTS IN THE CLUTCH SYS HAD FAILED AND CAUSED T	HE CLUTCH ACTUATOR TO ENGAGE CAUSING THE CLUTCH LIGHT TO ILLUMINATE.  THERE WERE NO DAMAGES TO THE ROTORCRAFT OR ANY INJ	URIES TO THE PILOTS. DRIVE BELTS WHERE REPLACED AND THE ROTORCRAFT WAS RETURNED TO SERVICED.			1	G	7	1 	3O	3	O		H10WE   	E286				 
	20090106		CE  	2009	1	6	2008FA0000896    	1	20081201	G	3010	671440211	TUBE            			CESSNA	750   	750         	2076810	CE  										ANTI-ICE SYSTEM	MISMANUFACTURED 	C			NOZR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	23	9NG	4141 				7500213				LT WING INBD HEATED LEADING EDGE AIR DISTRIBUTION TUBE PN 6714402-11 HAS AN INCOMPLETE WELD ON THE PERIPHERY OF THE FITT	ING.  HAD ANIT-ICE TUBE PN 671440211 WELDED IAW DWG 6714402 DWG 001.  REINSTALLED L/E AND SEALED SEAMS.  (K)					2	L	7	2 	4J			RT	T00007WI					 
	20090107		SW  	2009	1	7	2008FA0000897    	1	20081214	G	6210	206011135005	BOLT            	BELL        		BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	DEBONDED        	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	23	739NM	12938			A298	51124				MAIN ROTOR BLADE BOLT LWR PLUG, PN 206-011-137-001, FELL OUT ON ENG SHUTDOWN WHEN ROTOR RPM DROPPED BELOW 40 PERCENT. TH	IS ALLOWED LEAD BALANCE WEIGHTS TO ALSO FALL OUT OF BOLT. THIS PLUG IS BONDED INTO THE BOLT AT MFG AND APPEARS TO NOT HA	VE HAD ADEQUATE ADHESIVE APPLIED.				1	G	7	1 	3U				H2SW    					 
	20090105		CE  	2009	1	5	2008FA0000898    	1	20081222	G	5311		FRAME           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	244LJ	4361 				35A244				WHILE INSPECTING THE LT AFT FUEL TANK STRUCTURE, DUE TO LIGHTENING DAMAGE EVENT,  FOUND THE FOAM INSULATION WATER SOAKED	, AND CAUSING SERIOUS  CORROSION IN OUTER FLANGE OF AFT PRESSURE BULKHEAD AND SURROUNDING STRUCTURE. THE  HOLE IN THE LT	 OUTER PRESSURE BULKHEAD FLANGE, WHERE HOT AIR PIPE PENETRATES FLANGE HAD SEVERE INTERGRANULAR CORROSION OCCURRING ,  AN	D AREA WAS VERY WET.			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
	20090106		EA  	2009	1	6	2008FA0000899    	2	20081016	G	8520	13B21431	CRANKSHAFT      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	BROKEN          	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	6478P					15285025				THE ENGINE WAS REMOVED DUE TO ABNORMAL NOISE AND ROUGHNESS, UPON TEARDOWN INSP, FOUND THE CRANKSHAFT BROKEN IN TWO AT TH	E CENTER MAIN BEARING AREA.  THE CTR MAIN BRG SHOWED DISTRESS, BUT DID NOT INDICATE ANY LACK OF LUBRICATION.  THE CRANKC	ASE HAD SLIGHT DAMAGE IN THE BEARING RETAINING AREA.  THIS ENGINE HAD BEEN FACTORY OVERHAULED ON 7/14/06, AND PRESENTLY 	HAS 961.3 HOURS SINCE OVERHAUL.  THE LOG BOOK DID NOT INDICATE ANY PROP STRIKE OR PROPELLER CHANGE.  (K)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
	20090105		CE  	2009	1	5	2008FA0000900    	1	20081009	G	3233	99121204	ACTUATOR        			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NOSE GEAR	BYPASSING       	B			BGSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	3FA					5600023				HYD LOW LEVEL LIGHT CAME ON AFTER TAKEOFF AND REMAINED ON UNTIL FLAPS AND GEAR WERE SELECTED UP AND LOCKED.  REPLACED NO	SE GEAR ACTUATOR DUE TO INTERNALLY BYPASSING INTO THE EMERGENCY SIDE FOR GEAR EXTENSION.  SENT NOSE GEAR ACTUATOR OUT FO	R OVERHAUL AND INSTALLED AN OVERHAULED ACTUATOR.  (K)				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
	20090106		CE  	2009	1	6	2008FA0000901    	1	20081202	G	3230	390814101007	DAMPER          			RAYTHN	390   	390         	7150030	CE  										BUMPER MISSING	WRONG PART      	B			E81R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	100WE					RB45				INVESTIGATED PILOT REPORT OF MLG DOORS NOT CLOSING INDICATION FOLLOWING GEAR RETRACTION.  FOUND RUBBER BUMPER MISSING FR	OM LT MAIN GEAR UPLOCK DAMPER ASSY,  LT MAIN GEAR UPLOCK DAMPER ASSY CAUSING LT MN GEAR UPLOCK HOOK NOT TO RESET AND ENG	AGE ROLLER FOLLOWING GEAR RETRACTION DUE TO EXCESSIVE UP-TRAVEL OF LT MAIN GEAR.  REPLACED LT MAIN GEAR UPLOCK DAMPER WI	TH SERVICEABLE, SUPERSEDING PN 3908141010013 DAMPER ASSY.  LANDING GEAR RETRACTION/ EXTENSION OPERATIONS NORMAL.			1	L	7	2 	3F			RT	A00010WI					 
	20090102		WP  	2009	1	2	2008FA0000902    	1	20081208	G	7500	369H8407	TUBE            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					BLEED AIR	UNSERVICEABLE   	B			BS2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	8617F	272  				570128D	CAE830481			THIS DEFECT WAS DETECTED DURING TROUBLESHOOTING FOR AN ENGINE PWR PROBLEM.  THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CO	NJUCTION WITH AN STC FROM ENG PWR PROBLEM.  THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CONJUNCTION WITH AN STC, PC SAFETY	 VALVE KIT SE5511NM.  AFTER THE DEFECT WAS DETECTED, THE KIT FOR SAFETY VALVES WAS REMOVED AND THE ORIGINAL HARD LINE WA	S RE-INSTALLED.  THE STC KIT WILL NOT FIT IN THE ENGINE COMPARTMENT WITHOUT THE USE OF THE FLEX BLEED AIR TUBE.  THESE T	UBE ASSY ARE VERY SENSITIVE TO BREAKAGE AFTER THEY HAVE TAKEN A SET.  (K)		1	G	7	1 	3U	3	U		H3WE    	E4CE				 
	20090105		CE  	2009	1	5	2008FA0000903    	1	20081208	G	3244	850108PR	TUBE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TIRE	LEAKING         	C			MT9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1120N					208B0386	PCE19211	980220		THE PILOT REPORTED A FLAT TIRE.  MAINT FOUND AN INNER-TUBE LEAKING WITH NO APPARENT DAMAGE TO THE TIRE.  THE TUBE WAS RE	PLACED WITH A NEW TUBE.  SIX DAYS LATER THE SAME PILOT IN CHARGE OF THE SAME ACFT REPORTED THE SAME TIRE FLAT.  MX AGAIN	 FOUND THE INNER TUBE FLAT WITH NO APPARENT SIGNS OF DAMAGE TO THE TIRE.  A THROUGH INSP OF THE INNER-TUBE SHOWED PIECES	 OF WHAT APPEAR TO BE PAPER TOWEL EMBEDDED INTO THE RUBBER.  THE FIRST TUBE WAS THEN INSPECTED WHICH SHOWED THE SAME MAT	ERIAL EMBEDDED INTO IT.  AN INSPECTION OF NEW STOCK SPARE INNER TUBES OF THIS TYPE THAT HAD NEVER BEEN ISSUED OUT, FOUND	 THE SAME MATERIAL EMBEDDED IN THEM ALONG WITH, IN SOME CASES, PIECES OF HARD MATERIAL.  (K)	1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20090106		NE  	2009	1	6	2008FA0000904    	2	20081209	G	7250	30606266	TURBINE BLADES  			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					NR 2 ENGINE	DAMAGED         	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	373RS					0259				THE THIRD STAGE LP TURBINE DISK ON NR 2 ENG HAD A BLADE (PN 30606901) BREAK IN FLIGHT DAMAGING THE EXHAUST NOZZLE AND TH	E AFTER BODY OF THE ENG.  THE BLADES OF THE TURBINE DISK HAD A 2500 HOUR MPI REQUIRED EDDY CURRENT INSP COMPLETED AT 245	8.6 TSN AND 1979 CSN.  THE NEXT INSP APPEARS TO BE DUE IN 216.5 HRS.  (K)				2	L	7	3 	4F	4	F		A46EU   	E1NM				 
	20090106		SO  	2009	1	6	2008FA0000905    	2	20081201	G	8530	ECC712CN	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	333ZX					TH1739				NR 1 CYL FAILED, HEAD SEPARATED FROM BARREL.  ALL CYL, WERE OVERHAULED,  5/12/2004,  817.5 HRS AGO.  (K)						1	L	7	2 	3O	3	O		3A16    	E3SO				 
	20090106		EU  	2009	1	6	2008FA0000906    	1	20081122	G	8120		SEAL            	GARRTT      		SOCATA	TB20  	TB21        	8680697	EU  	LYC   	O540  	TIO540AB1A  	41533	EA  					TURBOCHARGER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	2802W				SCR0175	1137	L921061A			PILOT REPORTED THAT ENGINE LOST OIL PRESSURE AT AN ALTITUDE OF 8000 FT ABOUT 14 MILES WEST OF MUNICIPAL AIRPORT.  HE WAS	 ABLE TO MAKE AIRPORT AND SHUTDOWN THE ENGINE AFTER COMING TO A STOP ON THE RUNWAY.  REPORTED THAT WHEN THE ACFT LEFT, T	HE OIL WAS CHECKED AND WAS INDICATING 10 QTS. ON THE DIPSTICK.  THE ENGINE WAS EXAMINED WITH A REP FROM FAA PRESENT.  IT	 WAS DETERMINED AFTER EXAMINING THE TURBOCHARGER AREA THAT THE INTERNAL SEALS TO TURBO MUST HAVE FAILED, CAUSING OIL TO 	ENTER BOTH INTAKE SYS AND HOT SIDE OF TURBO.  SCAVENGE PORT OF TURBO WAS INSPECTED AND FOUND TO BE UNOBSTRUCTED.  OIL WA	S DRAINED FROM SUMP, YIELD WAS 1.5 QTS.  (K)	1	L	7	1 	3O	3	O	RT	A51EU   	E14EA				 
	20090106		SO  	2009	1	6	2008FA0000907    	2	20081208	G	8530	539491	CYLINDER        			BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	IO470K      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	653P	295  				CD991	818526R	652989		ANNUAL INSP REVEALED A LARGE QUANITY OF VERY BLACK OIL RUNNING DOWN THE ENGINE MOUNT LEG AND AIRFRAME STRUCTURE.  FURTHE	R INVESTIGATION FOUND THE LEAK TO ORIGINATE AT THE HEAD TO BARREL CONNECTIONS OF CYLINDERS NR 1, AND NR 3.  COMPRESSION 	CHECK USING AN INPUT PRESSURE OF 80 PSI AND LEAK DETECTING SOLUTION SHOWED AIR TO BE LEAKING FROM THE CYLINDER HEAD TO B	ARREL CONNECTION.  CYLINDERS WERE REMOVED AND INSPECTED BUT IT COULD NOT BE CONFIRMED IF CRACK EXISTED OR IF LEAK WAS TH	ROUGH THE THREADS.  THE LOW TIME ON NEW MFG CYLINDERS INDICATES THAT THE PROBLEM COULD BE IN THE MFG PROCESS.  NOTE: ENG	INE WAS REBUILT / ZERO TIMED USING NEW CYLINCERS ON 5/20/2001.  (K)	1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P880	 
	20090107		SO  	2009	1	7	2008FA0000908    	2	20080810	G	8520	510384	CONNECTING ROD  			PIPER 	J3    	J3C65       	7100510	SO  	CONT  	C90   	C908F       	17009	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	42080					14307	4077788			NR 1 CONNECTING ROD FAILED IN FLT, OFF-AIRPORT LANDING AND SUBSTANTIAL DAMAGE.   CONNECTING ROD FAILED SLIGHTLY ABOVE CR	ANKSHAFT; ROD CAP STILL BOLTED & SAFETIED TO DAMAGED & SEPARATED LOWER PORTION OF CONNECTING ROD.  DAMAGE TO CRANKCASE, 	CRANKSHAFT, & ADDITIONAL INTERNAL ENGINE COMPONENTS SUGGEST A FAILED/ SPUN NR 1 ROD BEARING, RESULTING IN A LOSS OF LUBR	ICATION TO NR 1 CONNECTING ROD. EXCESSIVE HEAT BUILDUP, AND SUBSEQUENT SEIZURE TO THE CRANKSHAFT JOURNAL AND ROD FAILURE	.   THE OIL SCREEN MINIMAL CONTAMINATION, INDICATING A SHORT OPERATING TIME BETWEEN PART FAILURE AND ENGINE SHUTDOWN.  E	NG EXHAUST WAS CLEAN AND THERE WAS NO EVIDENCE OF EXTERNAL OIL LEAKAGE ON THE ENG; REGARDLESS, OIL QUANTITY IN THE ACFT 	1	H	7	1 	3O	3	O		A691    	E252				 
	20090106		GL  	2009	1	6	2008FA0000909    	2	20080825	G	7261	23038229	SEPARATOR       								ALLSN 	250C  	T63A720     	03002	GL  					AIR/OIL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99							AE405466			CUSTOMER HAD CHIP LIGHT INDICATING METAL GENERATION IN ENG.  INVESTIGATION/ DISASSEMBLY REVEALED THE AIR OIL SEPARATOR G	EAR WAS BROKEN AT  GEARFACE TO SHAFT LOCATION (WHERE THE 16 DRILLED HOLES CONVERGE AT GEAR CTR). THIS IS THE 4TH OR 5TH 	AIR OIL SEPARATOR GEAR I`VE SEEN BROKEN LIKE THIS IN 7-8 YEARS.  WHEN THE GEAR BREAKS, IT GENERATES METAL BUT DOESN`T FA	IL IN OPERATION, BUT THEN THE GEARBOX IS OPENED THE GEAR COMES OUT IN TWO PIECES. (THE GEAR IS SUPPORTED BY A BEARING ON	 EITHER END AND IN OPERATION THE BROKEN GEAR IS HELD TOGETHER BY THE SANDWICH FIT CREATED BY THE GEARBOX IT OPERATES IN)	.  THE PROBABLE CAUSE FOR THE REPEATED FAILURES IS POSSIBLY THE DESIGN.  THE GEAR HAS 16 HOLES DRILLED INTO IT AND THEY 						3	U			E4CE				 
	20090107		CE  	2009	1	7	2008FA0000910    	1	20081226	G	7120	AN721	BOLT            			CESSNA	500   	550         	2076604	CE  										ENGINE MOUNT	INCORRECT       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	649WM	500  				42030				DURING UNSCHEDULED MAINT THE ENG WAS REMOVED FROM THE MOUNTS, (1) ENG MOUNT HAD THE HELICOIL PULL OUT OF THE CASTING NEC	ESSITATING REPLACEMENT OF THE MOUNT. IT WAS ALSO DISCOVERED THAT ALL OF THE ENGINE MOUNT BOLTS WERE OF THE INCORRECT PN.	  ALL OF THE BOLTS INSTALLED (AN7-21) WERE DRILLED FOR COTTER PINS RATHER THAN THE BOLTS (AN7-21A) NOT DRILLED FOR A COT	TER PIN THAT ARE CALLED OUT IN THE PARTS BOOK. THERE WERE NO LOG ENTRIES FOUND INDICATING THAT THE ENG HAD BEEN REMOVED 	SINCE INSTALLATION AT THE FACTORY.		1	L	7	2 	4F				A22CE   					 
	20090106		CE  	2009	1	6	2008FA0000911    	1	20081201	G	3230	HMX5FG	ROD END         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					LT MLG	CRACKED         	C				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			GL	17	77RG	12579				310R0636				PILOT REPORTED NO LT GEAR DOWN LIGHT AND ALSO HEARD A LOUD BANG WHEN GEAR WAS RETRACTED.  PILOT DID SEVERAL FLYBYS FOR M	ECHANICS ON GROUND, GEAR APPEARED TO BE DOWN.  PILOT LANDED WITHOUT INCIDENT AND STOPPED ON RUNWAY. GEAR WAS NOT COMPLET	ELY LOCKED.  GEAR WAS SECURED AND ACFT WAS TAXIED TO MAINT.  WHEN PLACED ON JACKS, THE ROD END (HEIM END) ON THE IB LT M	AIN GEAR PUSH PULL TUBE WAS FOUND TO HAVE THE BALL PULLED OUT OF THE ROD END.  ROD END APPEARED TO HAVE A SMALL CRACKED 	WHERE IT FAILED.  NOTE: ACFT HAD BEEN LANDED GEAR UP JAN O2.  (K)		1	L	7	2 	3O	3	O		3A10    	E5CE				 
	20090106		CE  	2009	1	6	2008FA0000912    	1	20081201	G	7400		IGNITION SYS    			CESSNA	182   	182C        	2072708	CE  	CONT  	O470  	O470L       	17026	SO  					EGNINE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	8595T					52495	6944670LR			ENG RUNS ROUGH. ENG MISFIRES. HISTORY: 2/25/2004; TACH 487.1 - REPLACED LT AND RT MAGNETOS.  ACFT RUN UP CHECKED OUT OK.	  4/26/2004 TACH 508 - CHECKED TIMING.  05/11/2005 (NO TACH) - TROUBLESHOOTING ROUGH ENGINE.  REMOVED INTAKE MANIFOLD AN	D FLAT SAND FLANGES AND REMOVE DENTS.  REPLACE ALL INTAKE FLANGE GASKETS AND HOSES.  PRESSURE TEST INTAKE MANIFOLD.  REM	OVE AND REPAIR MA4-5 CARB.  RUNUP OK.  8/16/2007 TACH 542.7 - CHECK MAG TO ENG TIMING.  RUN-UP AND LEAK CHECK OK.  SOLUT	ION; TACH 573.8 USED DAIL INDICATOR AND FOUND THAT UTILIZING TIMING MARKS RESULTS IN 20+ DEGREE RETARDED IGNITION.  USED	 DIAL INDICATOR TO SET PROPER TIMING AND ENGINES PERFORMS AS IT SHOULD.  (K)	1	H	7	1 	3O	3	O	NT	3A13    	E273				 
	20090102		EU  	2009	1	2	2008FA0000917    	1	20081217	G	2435		BEARING         			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					STARTER GEN	UNSERVICEABLE   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	451F				1781	1124				PILOT COMPLAINED OF A SEVERE ENGINE VIBRATION AND HOWLING NOISE EMANATING FROM THE ENGINE AREA, DURING ALL PHASES OF ENG	INE OPERATION.  THE STARTER WAS REPLACED AND THE VIBRATION CEASED.  (K)					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
	20090106		NE  	2009	1	6	2008FA0000918    	2	20081215	G	7414	103827991	MAGNETO         			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6D  	41828	NE  					ENGINE	MALFUNCTIONED   	B			C41R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	13	201TC					240173	L1710951AC			STARTED THE ACFT NORMALLY, TAXIED FROM HANGAR TO THE SELF-SERVE FUEL PUMP AND SHUTDOWN.  FUELED ACFT.  ATTEMPTED TO STAR	T THE ACFT AFTER FUELING.  THE ENG TURNED OVER NORMALLY, BUT DID NOT FIRE.  TROUBLESHOOTING REVEALED NO SPARK OUTPUT FRO	M THE MAGNETO.  SENT MAGNETO OUT FOR REPAIR MAGNETO SHOP DETERMINED THE MAGNET HAD SLIPPED ON THE SHAFT.  A NEW MAGNETO 	WAS INSTALLED IN THE ACFT.  ENGINE TT: 5345.1; TSO 132.6.  THIS MAGNETO WAS INSTALLED AT THE ENGINE OVERHAUL AS AN OVERH	AULED EXCHANGE UNIT.  PROBABLE CAUSE/ RECOMMENDATIONS TO PREVENT RECURRENCE; NO ADDITIONAL INSP REQUIREMENTS ARE RECOMME	NDED. A FAILURE SO SOON AFTER OVERHAUL SUGGESTS A DEFECT IN THE PARTS OR A FAILURE IN THE OVERHAUL PROCESS.  THE LARGEST	1	L	7	1 	3O	3	O		2A3     	1E10				 
	20090107		CE  	2009	1	7	2008FA0000919    	1	20081210	G	5711	52221003	SPAR            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	141MC	10940				402B0547				DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR.  THE MAIN GEAR IS ATTACHED AT THE OTBD END.  THE CRAC	KS WERE AT THE 11, 2, 5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LE	NGTH WITH THE 2 LOWER HOLES  CONTINUING INTO THE ACCESS HOLE.  CRACKS WERE ALSO AT THE 7 AND 5 O, CLOCK POSITIONS OF THE	 LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WITH A RIGN AND NUT PLATES ON THE OPPOSITE SIDE.  THESE CRACKS WEN	T THROUGH THE SCREW HOLES AND EXTENDED UP T 2+ INCHES.  THE CRACKS WERE OBSERVED 2671 HOURS AFTER THE MAIN SPAR CAP MODI	FICATION.  SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OBSERVED IN 5 OF 8 ACFT.  ALL HAVE THE MOD.  IT IS NOT KNOWN IF TH	1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
	20090106		CE  	2009	1	6	2008FA0000920    	1	20081216	G	3233	12810016	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	D			JU8S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	9423D	1940 				172RG0285				ON 7/08/2008, RT MLG NOT FULLY RETRACTED REPORTED BY ATC.  THE PILOTS NOTICED THE RT MLG WAS NOT FULLY RETRACTED.  THE L	ANDING GEAR WAS THEN EXTENDED, A DOWN AND LOCKED IND FOR GEAR WAS REPORTED.  THE RT MLG ACTUATOR BODY (DATE STAMP OF AUG	 21, 2001.) WAS FOUND CRACKED AT THE FWD BOLT HOLE ATTACH POINT.  THE CRACK ALLOWED THE ACTUATOR SECTOR GEAR AND PISTON 	TO BECOME MISALIGNED.  ACTUATOR SECTOR GEAR PN 988200202 AND PISTON ASSY PN 98820041 WERE FOUND TO BE DAMAGED.  THIS ACT	UATOR BODY WAS REPLACED WITH A NEW PART IAW SEB 01-2 R1 ON 10-11-2001 AT AN TT OF 5180.2.  IT WOULD BE POSSIBLE FOR THIS	 DAMAGE TO PREVENT THE GEAR FROM TRAVELING TO THE FULL DOWN AND LOCKED POSITION RESULTING IN LOSS OF ACFT CONTROL DURING	1	H	7	1 	3O				3A17    					 
	20090106		CE  	2009	1	6	2008FA0000921    	1	20081210	G	5711	522210003	SPAR            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	402CA	12660				402B0842				DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR.  THE MAIN GEAR IS ATTACHED AT THE OTBD END.  THE CRAC	KS WERE AT THE 11, 2, 5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LE	NGTH.  CRACKS WERE ALSO AT THE 7 AND 5 O`CLOCK POSITIONS OF THE LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WIT	H A RING AND NUT PLATES OF THE OPPOSITE SIDE.  THESE CRACKS WENT THROUGH THE SCREW HOLES AND EXTENDED UP TO 1.5 INCH.  T	HE CRACKS WERE OBSERVED 1600 HOURS AFTER THE MAIN SPAR CAP MODIFICATIONS.  SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OB	SERVED IN 5 OF 8 ACFT.  ALL HAVE THE MOD.  IT IS NOT KNOWN IF THERE IS ANY CORROLATION.  (K)	1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
	20090106		CE  	2009	1	6	2008FA0000922    	1	20081210	G	5711	52221003	SPAR            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	106GP	16296				402B1235				DURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR.  THE MAIN GEAR IS ATTACHED AT THE OTBD END.  THE CRAC	KS WERE AT THE 11,2,5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENG	TH.  CRACKS WERE ALSO AT THE 7 O`CLOCK POSITIONS OF THE LARGE ACCESS HOLE TO WHICH A COVER PLATE IS ATTACHED WITH A RING	 AND NUT PLATES ON THE OPPOSITE SIDE.  THIS CRACK WENT THROUGH THE SCREW HOLE AND EXTENDED 1 INCH. THE CRACKS WERE OBSER	VED 930 HOURS AFTER THE MAIN SPAR CAP MODIFICATION.  SIMILAR CRACKS OF VARYING DEGREE HAVE BEEN OBSERVED IN 5 OF 8 ACFT.	  ALL HAVE THE MOD.  IT IS NOT KNOW IF THERE IS ANY CORROLATION.  (K)	1	L	7	2 	3O	3	O		A7CE    	E8CE				 
	20090106		EU  	2009	1	6	2008FA0000923    	1	20081212	G	3222	25UN561	AXLE            			BRAERO	DH125 	HS125700A   	4230170	EU  										NLG	WORN            	B			X42R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	483FG	521  				257094				CONTINUOUS NOSE GEAR VIBRATIONS UPON LANDING.  TEARDOWN AND INSPECTION OF NOSE GEAR AXLE BARREL ASSY REVEALED THE NOSE A	XLE TO BE WORN BEYOND LIMITATIONS.  (2) .005" GROOVES WORN INTO AXLE.  (1) ON EACH SIDE WHERE THE AXLE BARREL COVER PLAT	E SEALS ARE LOCATED.  NO WEAR IS PERMITTED AS PER THE OVERHAUL MANUAL.  (K)				2	L	7	2 	4F				A3EU    					 
	20090102		CE  	2009	1	2	2008FA0000924    	1	20081201	G	2710	500000066	CONTROL CABLE   			CESSNA	421   	421B        	2076014	CE  										LT AILERON CABLE	FRAYED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13						68494				TT ON CABLES UNKNOWN SUSPECT ORIGINAL.  FOUND LT AFT AILERON CABLE FRAYED AT WING STATION 58.94 THE PULLEY WAS FROZEN.  	INSPECTED REST OF SYSTEM NO DEFECTS FOUND.  ON REPLACEMENT OF CABLE FOUND WAS ALSO FRAYED AT WING STA 87.29.  THE PULLEY	S AT THIS STATION WERE TURNING FREELY.  WHEN INSTALLING NEW CABLE NOTICED THE FWD AILERON CABLE WITH BROKEN STRANDS ALSO	 AT WING STATION 87.29, ALSO REQUIRING CABLE REPLACEMENT.  SUGGEST THAT EVERYONE BE REMINDED OF THIS LOCATION AND OF WIN	G STATION 106.79 AS THESE ACCESS PANELS ARE IN WHEEL WELL WITH THE PULLEYS OFF TO THE SIDE AND DOWN THEY ARE A HARD AREA	 TO INSPECT, AND THE AILEREONS HAD TO BE MOVED TO THE TRAVEL LIMITS TO BE COMPLETELY INSPECTED, AS THE CABLES WERE BROKE	1	L	7	2 	3O				A7CE    					 
	20090107		CE  	2009	1	7	2008FA0000925    	1	20081215	G	2820	6017001079	VENT LINE       			BEECH 	58    	58          	1152740	CE  										RT WING	LEAKING         	B			EHHR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	584RF	1933 				TH2012				FOUND RT WING FUEL VENT CONSTANTLY LEAKING FUEL.  OPENED RT WING TIP FILLER CAP AND BLEW AIR THROUGH THE VENT SYSTEM AND	 BUBBLES WERE SEEN IN THE LOWER END OF THE FUEL TANK WHERE THE VENT TUBE PASSES THROUGH THE FUEL TANK BULKHEAD.  USED AC	FT MM TO FABRICATE A HOLE IN FUEL CELL TO GAIN ACCESS TO THE LEAKING TUBE AND APPLIED PRO SEAL TO SEAL THE TUBE TO THE B	USHING WHERE THE LEAK WAS OBSERVED.  (K)			1	L	7	2 	3O				3A16    					 
	20090102		CE  	2009	1	2	2008FA0000926    	1	20081201	G	2710	500000067	CONTROL CABLE   			CESSNA	421   	421B        	2076014	CE  										LT AILERON	FRAYED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13						68494				TT ON CABLES UNKNOWN SUSPECT ORIGINAL. FOUND LT AFT AILERON CABLE FRAYED AT WING STA 59 THE PULLEY WAS FROZEN.  INSPECTE	D REST OF SYSTEM NO DEFECTS FOUND. ON REPLACEMENT OF CABLE FOUND WAS ALSO FRAYED AT WING STA 87.29. THE PULLEYS AT THIS 	STATION WERE TURNING FREELY.  WHEN INSTALLING NEW CABLE NOTICED THE FWD AILERON CABLE WITH BROKEN STRANDS ALSOAT WING ST	ATION 87.29, ALSO REQUIRING CABLE REPLACEMENT.  SUGGEST THAT EVERYONE BE REMINDED OF THIS LOCATION AND OF WING STA 106.7	9 AS THESE ACCESS PANELS ARE IN WHEEL WELL WITH THE PULLEYS OFF TO THE SIDE AND DOWN THEY ARE A HARD AREA TO INSPECT, AN	D THE AILERONS HAD TO BE MOVED TO THE TRAVEL LIMITS TO BE COMPLETELY INSPECTED, AS THE CABLES WERE BROKEN IN SMALL LOCAL	1	L	7	2 	3O				A7CE    					 
	20090120		SO  	2009	1	20	2008FA0000927    	2	20081201	G	8500	S1053E16T	HOSE            			CESSNA	150   	A150K       	2071824	CE  	CONT  	O200  	O200*       	17020	SO  					AIR INTAKE	CONTAMINATED    	D				A				UNSCHED LANDING         				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		CL	CLIMB          	1			AL	05	8450M					A15000150				BEGAN NORMAL LANDING CHECK LIST INCLUDING CHECKING CARB HEAT.  AFTER PULLING CARB HEAT ON, ENGINE DIED.  TURNED OFF CARB	 HEAT & ENGINE RESTARTED ON ITS OWN WITHOUT PILOT INPUTS.  CONTINUED PATTERN & GRADUALLY REAPPLIED CARB HEAT ON BASE AND	 FINAL.  ON SHORT FINAL ENGINE DIED & PILOT GLIDED TO A SAFE TOUCHDOWN.  ABLE TO RESTART ENGINE & TAXI BACK TO PARKING W	ITHOUT INCIDENT.  FOUND THE SCAT HOSE COMING FROM FRONT BAFFLE DOWN TO FRONT OF EXHAUST SHROUD HAD FILLED WITH WATER.			1	H	7	1 	3O	3	O		3A19    	E252				 
	20090106		EA  	2009	1	6	2008FA0000928    	2	20081230	G	7414	66LC35SDNP	MAGNETO         			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					RIGHT	DAMAGED         	B				O				OTHER                   				O			OTHER                     			UK	UNKNOWN        	1			NM	07	5880K	594  				T20608581	L12173			RT MAGNETO INTERMITTENT, MAGNETO STAYED HOT AND SOME TIMES IT WILL NOT HAVE ANY CURRENT GOING THROUGH.  IF PROPELLER WAS	 MOVE IT WILL FIRE RT UP, AFTER REMOVED RT MAGNETO AND OPENED FOUND THAT THAT COIL HAS MELTED MOST OF THE GEARS AND CASI	NG.				1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
	20090106		CE  	2009	1	6	2009F00002       	1	20081221	G	5610	10138402522	WINDSHIELD      			BEECH 	90    	C90         	1152913	CE  										COCKPIT	CRACKED         	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CE	01	736EA					LJ1478				ACFT LEVELED OFF AT 20,000 FT AFTER APPROX 45 MIN OF FLIGHT, THERE WAS A SUDDEN BANG, AND CO-PILOTS WINDSHIELD INNER PAN	E SPIDER WEB CRACKED.  FLT CREW DIVERTED TO NEAREST AIRPORT AND LANDED WITHOUT FURTHER INCIDENT.					1	L	7	2 	3T				3A20    					 
	20090107		CE  	2009	1	7	2009FA0000000    	1	20081208	G	3250	66429438	BUNGEE CYLINDER 			CESSNA	560   	560XL       	2076702	CE  										MLG	MALFUNCTIONED   	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	669TT	740  				5684				DURING TAXI, ACFT PULLS TO LT UNCOMMANDED. ALSO INFLIGHT CREW HEARD A RUBBING NOISE FROM THE LT RUDDER PEDAL. CREW ALSO 	MENTIONED IN FLIGHT THE RUDDER PEDALS FEEL LIKE THERE IS SOMETHING RUBBING.  FOUND JAM NUT ON STEERING BUNGEE HAD LOOSEN	ED, ALLOWING THE ROD END TO EXTEND ON THE PUSH ROD. REPLACED STEERING BUNGEE WITH NEW UNIT AND RE-RIGGED THE NOSE STEERI	NG. IN THE MAINT PROCEDURE 32-50-00 THERE IS NO MENTION OF SECURING THIS ADJUSTMENT (ROD END BEARING, JAM NUT, PUSH ROD)	 SUCH AS LOCK TITE 732, OR POSSIBLY EVEN BETTER A WAY TO SAFETY THE JAM NUT. REPLACEMENT OF BUNGEE AND RIGGING THE NOSE 	STEERING FIXED THE PROBLEM.  WORK WAS ACCOMPLISHED AT THE MFG SERVICE CENTER.	2	L	7	2 	4F			RT	A22CE   					 
	20090108		SW  	2009	1	8	2009FA0000002    	1	20081218	G	3233	EM411514	ACTUATOR        			ECLIPS	EA500 	ECLIPSEEA500	3350000	SW  										RT MLG	FAULTY          	C				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			SO	19	929KD	134  				000240				DURING CLIMB THE RT MLG FAILED TO FULLY RETRACT.  GEAR INTRANSIT INDICATED.  ON SELECTION OF LANDING GEAR DOWN, RT MLG F	AILED TO EXTEND.  ALTERNATE GEAR EXTENSION USED AND GEAR EXTENDED FULLY AND "DOWN AND LOCKED" INDICATED.  NORMAL LANDING	 ACCOMPLISHED.  ON JACKS THE RT MLG WOULD ONLY RETRACT ABOUT 45 DEGREES AND WOULD NOT EXTEND FULLY WHEN SELECTED.  RT ML	G ACTUATOR REPLACED AND SYSTEM FUNCTION TESTED NORMAL.			1	L	7	2 	4J			RT	A00002AC					 
	20090120		SO  	2009	1	20	2009FA0000004    	2	20081210	G	8520		BOLT            			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  					ENGINE	FAILED          	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			GL	15	9426K					21060572	506240			DURING CLIMB TO CRUISE ENGINE MADE A LOUD NOISE AND QUIT RUNNING, ENGINE REMAINED WINDMILLING TO LANDING.  VISUAL INSP R	EVEALED NR 3 CYLINDER ROD BOLT MISSING, ROD CAP EXITED ENG THRU UPPER CASE, NO EVIDENCE OF OIL STARVATION.					1	H	7	1 	3O	3	O		3A21    	E8CE				 
	20090120		CE  	2009	1	20	2009FA0000005    	1	20081223	G	2910	S217840095A	HOSE            			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					HYD SYSTEM	BURST           	B				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			SO	05	732UR	3658 				21061789				RT NLG DOOR ACTUATOR HOSE FAILED CAUSING COMPLETE HYD FLUID LOSS . RESULTING IN LT MAIN GEAR NOT ABLE TO BE FULLY EXTEND	ED TO DOWN AND LOCKED POSITION.  ACFT MADE EMERGENCY LANDING WITH LT MAIN GEAR PARTIALLY EXTENDED.  MINOR DAMAGE.  FAILE	D HOSE APPEARS TO BE ORIGINAL INSTALLED NEW IN 1977.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
	20090130		CE  	2009	1	30	2009FA0000007    	1	20081215	G	3233	35810080602	ACTUATOR        			BEECH 	35    	A35         	1151504	CE  										MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	15	473AB		368  			D1578				INTERNAL FAILURE WITHIN LANDING GEAR ACTUATOR GEARBOX. GEAR WOULD NOT CYCLE DOWN BY NORMAL OR EMERGENCY EXTENSION. EMERG	ENCY HANDLE WOULD NOT ENGAGE. COMPONENT WAS OVERHAULED IN 1983.					1	L	7	1 	3O				A777    					 
	20090120		NE  	2009	1	20	2009FA0000012    	2	20081230	G	7321	2123M55P04	ECU             			AIRBUS	320   	A320214     	3930316	EU  	CFMINT	CFM56 	CFM565B4P   	 	NE  					NR 2 ENGINE	FAULTY          	C			VQIA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	15	632VA					3155	577893			FLIGHT 515 LAX TO JFK.  DURING CRUISE 3 ECAM WARNINGS, THRUST LEVER FAULT, CTL VALVE FAULT, AND ENG2 FADEC A FAULT.  AN 	ASSOCIATED LAND ASAP AMBER ECAM ADVISORY MSG ALSO APPEARED.  CREW ADVISED DISPATCH THAT THEY WERE DIVERTING TO LAS.  MX 	FOLLOWED THE TSM FOR THE FAULTS AND FOUND ENGINE 2 CHANNEL A NOT REPORTING DURING ECU TEST.  THE ECU WAS REPLACED AND OP	S CHECKED OK PER AMM 73-21-60.  IAW THE OPERATORS RECORDS, ALL AIRWORTHINESS DIRECTIVES, SERVICE BULLETINS, STC`S AND PM	A`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REGULATORY REQUIREMENTS.  THE ACFT WAS RELOCA	TED BACK TO SFO.  N632VA DEPARTED LAS AT 0741Z AND ARRIVED SFO AT 0842Z.  NO FAULTS NOTED.	2	L	7	2 	4F	4	F	RT	A28NM   	E38NE				 
	20090120		EU  	2009	1	20	2009FA0000013    	1	20081217	G	6120		CONTROL CABLE   			STBROS	SD3   	SD360       	8100606	EU  										RT PROPELLER	BROKEN          	C			TXHA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	808KR					SH3734				THE ACFT RT PROP CABLE BROKE.  ACFT RETURNED TO HONOLULU STATION FOR INSPECTION AND REPAIR.						2	H	7	2 	4T				A41EU   					 
	20090129		CE  	2009	1	29	2009FA0000014    	1	20081210	G	3260		ARM             			CESSNA	414   	414         	2075908	CE  										DOWNLOCK	BROKEN          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			GL	19	52CS					4140615				ON LANDING, THE PILOT SELECTED THE GEAR DOWN AND NEVER GOT A GREEN DOWN AND LOCK LIGHT IN THE CABIN FOR THE RT MAIN GEAR	.  THE GEAR DOWNLOCK MICRO-SWITCH ACTUATOR ARM WAS BROKEN AND WOULD NOT ACTUATE THE MICRO-SWITCH.  THESE ACTUATOR ARMS S	EEM TO GET WEAK OVER TIME.  THERE WAS NO OTHER REASON FOR THE ARM TO FAIL.  (K)				1	L	7	2 	3O			RT	A7CE    					 
	20090130		CE  	2009	1	30	2009FA0000015    	1	20081230	G	3240	632750012	TUBE            			CESSNA	525   	525         	2076601	CE  										BRAKE SYS	BROKEN          	B			AWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	793CJ	4959 				5250021				DURING AN INSP, DOC 10, LANDING GEAR PNEUMATIC BRAKE SYS FUNCTIONAL CHECK ONE OF THE LINES IN THE RT LANDING GEAR WELL B	LEW.  FURTHER INVESTIGATION FOUND THAT THE 6327500-12 TUBE ASSY BROKE OFF AT THE FLARE ON THE INBD END OF THE TUBE ASSY.	  INSP OF THE SAME LINE ON THE LT SIDE FOUND NO DEFECTS.  (K)				1	L	7	2 	4F			RT	A1WI    					 
	20090129		SO  	2009	1	29	2009FA0000016    	2	20081217	G	8550	652969	PAN             			CESSNA	414   	414A        	2075907	CE  	CONT  	O550  	TSIO550A    	41516	SO  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	15	414PS					414A0056	800653			OIL LEAK CAME FROM CRACK IN OIL PAN.  CAUSE UNKNOWN.  ENG TSMOH 95 HRS.   CRACK/ FITTING WITH HOSE ATTACHED FOR REMOTE O	IL DRAIN.  (K)					1	L	7	2 	3O	3	O		A7CE    	E5SO				 
	20090130		WP  	2009	1	30	2009FA0000017    	1	20081223	G	7820	C16932	MUFFLER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  										EXHAUST SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	1425K	676  				10153				MUFFLER CAN BLOW OUT AT TAIL PIPE CONNECTION AND COLLECTOR FAILURES, BULGES AND BLOW OUTS.  WEAK MATERIAL, USE THICKER A	ND BETTER MATERIAL.  PEOPLE ARE GETTING SICK AND/OR BAD HEADACHES.  CO DETECTORS ARE SOUNDING OFF IF YOU HAVE ONE.  (K)					1	G	7	1 	3O				H11NM   					 
	20090128		WP  	2009	1	28	2009FA0000018    	1	20081223	G	7810	C1695	COLLECTOR       			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					IB AREA 3 TO 1	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	417PK	497  				11480				EXHAUST COLLECTORS 3 TO 1 TYPE.  BULGES AND BLOW OUTS.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20090128		CE  	2009	1	28	2009FA0000020    	1	20081224	G	3260	45A3951141	UPLOCK HOOK     			BEECH 	MU300 	400A        	1155402	CE  										NLG	DISENGAGED      	B			E81R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	03	175QS	15   								AFTER DEPARTING, FLIGHT CREW OBSERVED RED LANDING GEAR UNSAFE LIGHT IN LANDING GEAR CONTROL HANDLE ILLUMINATED AFTER LAN	DING GEAR RETRACTION.  RETURNED TO DEPARTURE.  FOUND NLG UPLOCK HOOK NOT ENGAGING NOSE GEAR STRUT ASSY AS REQUIRED IAW M	M 32-30-00.  LANDING GEAR RETRACT/ EXTENSION SYS FUNCTION CHECKS IAW MM 32-00-00 OK.  SUSPECT ADJUSTMENT CHANGED SLIGHTL	Y FROM AS-BUILT RIGGING DUE TO COMPONENTS WEARING IN, HAVE NOTED SIMILAR CONDITION PREVIOUSLY ON OTHER LOW-TIME ACFT.  (	K)		2	H	7	2 	4F			RT	A16SW   					 
	20090129		SO  	2009	1	29	2009FA0000021    	1	20081022	G	3230	SE0521903XXX	BEARING         			GULSTM	G1159 	GIV         	3980115	SO  										NLG	LOOSE           	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	19	972MS					1285				WHILE TAXIING ACFT, CREW REPORTED POPPING SOUND COMING FROM NOSE WHEEL WELL AND DURING RT TURNS.  FOUND NLG DRAG BRACE U	PPER ATTACH VERTICAL BEARING AT FS 119, FINGER TIGHT.  INSPECTED OTHER ACFT AND FOUND SAME OCCURRENCE.  SB 157 HAS BEEN 	COMPLIED WITH ON 3/09/2004.				2	L	7	2 	4F			RT	A12EA   					 
	20090130		EU  	2009	1	30	2009FA0000022    	1	20081027	G	7921	MS210435	NUT             			HUGHES	369   	369FF       	4470709	EU  	ALLSN 	250C  	250C30      	03013	GL  					COOLER BLOWER	BACKED OUT      	B			GI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	5185G					0009F				OIL COOLER BLOWER DRIVEN PULLEY RETAINING NUT IS BACKING OFF OF SHAFT DURING NORMAL USE.  NUT IS A STAINLESS STEEL, SILV	ER PLATED, ALL METAL SELF LOCKING TYPE NUT.  THIS WAS THE 3RD OCCURRENCE OF THIS TYPE FOR OUR UNIT AND WE ARE ALSO AWARE	 OF ONE OTHER INCIDENT TO ANOTHER COMPANY.  WHEN THE NUT BACKS OFF IT CAUSES THE SHAFT BEARING TO GO BAD WHICH DESTROYS 	THE OIL COOLER BELT.  THIS LEADS TO EXTREME ENGINE OIL AND MAIN TRANSMISSION OIL TEMPERATURES.  AFTER INVESTIGATING PN, 	WE FOUND THAT MFG HAS BEEN USING THIS TYPE NUT FOR A LONG TIMEAND WERE UNSURE IF THE NUT CURRENTLY BEING PRODUCED ARE SU	BSTANDARD.  UNIT WAS O/H. THE O/H FACILITY HAS BEEN INFORMED OF THESE INCIDENTS AND THEY ARE CURRENTLY INVESTIGATING THE	1	G	7	1 	3U	3	U		H3WE    	E1GL				 
	20090129		EA  	2009	1	29	2009FA0000024    	2	20081204	G	7322	25765463	SERVO           			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	137P					2060804	L3271948E	80VSA1		FUEL SERVO LEAKED WHILE ACFT WAS PARKED OVERNIGHT.  THE MIXTURE WAS IN CUT OFF POSITION.  FLIGHT MANUAL, SEC 4, NORMAL P	ROCEDURES PAGE 4-23 SECURING ACFT NR 10 STATES: FUEL SELECTOR VALVE RT OR LT TO PREVENT CROSS FEEDING.  IF THE FUEL SELE	CTOR VALVE WAS TURNED TO OFF, THIS WOULD HAVE PREVENTED.  THERE IS A POTENTIAL FOR FUEL TO ENTER ENGINE CYLINDERS AND OI	L SUMP IF THE FUEL SERVO MIXTURE CUT OFF LEAKS USING FLIGHT MANUAL PROCEDURES.  NEED TO ADDRESS: FLIGHT MANUAL PROCEDURE	S TO FUEL SELECTOR VALVE OFF.  (K)		1	H	7	1 	3O	3	O	RT	A4CE    	1E4	5	C	P58GL	 
	20090130		CE  	2009	1	30	2009FA0000026    	1	20081224	G	3600	AA3216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  						LOW PRESSURE    	B			VJ3R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	8242T	19   				CE1610	830201R			PILOT REPORTED INSTRUMENT AIR PRESSURE LOW AT IDLE ON RUN UP.  ON TROUBLESHOOTING, THE MECHANIC DETERMINED THE AIR PUMP 	WAS NOT PRODUCING ENOUGH PRESSURE AT IDLE.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.  (K)					1	L	7	1 	3O	3	O		3A15    	E5CE				 
	20090130		GL  	2009	1	30	2009FA0000027    	1	20081219	G	7797	14251001	WIRE HARNESS    			CIRRUS	SR    	SR22        	2130001	GL  										ENG COMPARTMENT	CHAFED          	B			YEBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	961AG					0255				FOUND THE BLACK PLASTIC WIRE LOOM THAT HOUSES THE MAP WIRING HARNESS FWD OF THE BAFFLE TO HAVE CHAFED THROUGH THE WIRE I	NSULATION OF THE WIRES IN SEVERAL LOCATIONS.  THIS IS CAUSED BY THE WIRE HARNESS BEING ABLE TO MOVE INSIDE THE LOOM AND 	THE LOOM BEING MADE FROM A HARDER MATERIAL THAN THE  WIRE INSULATION.  INSTALL NEW WIRE HARNESS AND REMOVE THE PLASTIC L	OOM.  SECURE WIRES AS NEEDED.  (K)			1	L	7	1 	3O			NT	A00009CH					 
	20090130		EA  	2009	1	30	2009FA0000028    	2	20081205	G	8520	11B200611SH	CRANKCASE       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149G	4622 	872  			2843191	L3630836A			FOUND LT FRONT CRANKCASE CRACKED DURING ROUTINE MX.  (K)						1	L	7	1 	3O	3	O		2A13    	E286				 
	20090130		EA  	2009	1	30	2009FA0000029    	2	20081206	G	8520	11B200615H1	CRANKCASE       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4148P	6916 	789  			2843177	L3616236A			FOUND LT FRONT CRANKCASE CRACKED DURING ROUTINE MX.  (K)						1	L	7	1 	3O	3	O		2A13    	E286				 
	20090130		CE  	2009	1	30	2009FA0000030    	1	20081228	G	2497		CIRCUIT BREAKER 			LEAR  	55    	55LEAR      	5170702	CE  										MAIN BUSS	MALFUNCTIONED   	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CE	03	242RB					55B132				ACFT DEPARTED, ENROUTE WITH 2 PASSENGERS, 2 HOURS INTO FLIGHT, JUST PRIOR TO INITIAL DESCENT, ACFT EXPERIENCED A COMPLET	E ELECTRICAL FAILURE AND LOSS OF PRESSURIZATION AT FL430.  FLIGHT CREW REGAINED CONTROL OF PRESSURIZATION AROUND FL330 A	ND RESTORED PWR TO NR 1 COMM RADIO.  ACFT DIVERTED AND MADE A VISUAL NO-FLAP APPROACH & LANDING.  ACFT OVERRAN RUNWAY AP	PROX 50 FT INTO MUD.  NO PASSENGERS OR CREW WERE INJURED AND ACFT HAD MINOR DAMAGE.  AFTER INITAL INSP, SUSPECT LT MAIN 	BUSS C/B ISSUE BUT UNABLE TO CONFIRM THIS TO BE THE PROBLEM AT THIS TIME.  ADDITIONAL INSP AND MAINT NEEDED TO CONFIRM C	/B OVERLOAD.  (K)	2	L	7	2 	4F				A10CE   					 
	20090205		SO  	2009	2	5	2009FA0000036    	2	20081013	G	7414	105005563	MAGNETO         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	FAILED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			GL	09	651BS	235  				1711	360237	FP4833B		FLIGHT CREW REPORTED ENGINE SPUTTERED DURING INITIAL CLIMB.  UPON INTERNAL VISUAL INSP OF LT MAGNETO, FOUND BROKEN MAGNE	TO SHAFT BELOW DRIVE GEAR.  ALUMINUM MAGNET CASTING FAILED AT STEEL SHAFT MATING JOINT.  ROTATION OF STEEL SHAFT IN ALUM	INUM CASTING YIELDED EXCESSIVELY RETARDED TIMING.  MAGNETO WAS "FACTORY NEW" WITH 235.4 HOURS TT AND HAS NOT BEEN OPENED	 PRIOR TO THIS EVENT.  A REPLACEMENT "FACTORY NEW" MAGNETO OF THE SAME TYPE WAS INSTALLED TO RESOLVE THE PROBLEM.  PREVI	OUSLY ON 9/9/2008 AT 1112.0 HOURS AIRCRAFT TOTAL TIME, THE RIGHT MAGNETO WAS FOUND TO HAVE FAILED DURING RUN-UP CHECKS W	ITH THE SAME FAILURE MODE.	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA	 
	20090205		SO  	2009	2	5	2009FA0000037    	2	20081218	G	7414	105005563	MAGNETO         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	FAILED          	D				D				RETURN TO BLOCK         				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			GL	09	70RB	351  				1653	360157	FP4526B		LT MAGNETO FAILED TO SUSTAIN ENG OPS DURING GROUND RUN-UP CHECK.  UPON INTERNAL VISUAL INSP, FOUND BROKEN MAGNETO SHAFT 	BELOW DRIVE GEAR.  ALUMINUM MAGNET CASTING FAILED AT STEEL SHAFT MATING JOINT.  ROTATION OF STEEL SHAFT IN ALUMINUM CAST	ING YIELDED EXCESSIVELY RETARDED TIMING.  MAGNETO WAS "FACTORY NEW" WITH 350.9 HOURS TT AND HAS NOT BEEN OPENED PRIOR TO	 THIS EVENT.  A REPLACEMENT "FACTORY NEW" MAGNETO OF THE SAME TYPE WAS INSTALLED TO RESOLVE THE PROBLEM. FOR PRECAUTIONA	RY REASONS, THE RT MAGNETO WAS OPENED AND FOUND TO HAVE THE SAME CRACK BEGINNING.  IT WAS ALSO REPLACED WITH A "FACTORY 	NEW" MAGNETO OF THE SAME TYPE.	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA	 
	20090205			2009	2	5	2009FA0000050    	2	20081229	G	7414	M3458	ROTOR           																	MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02		1059 			98100916					THE PILOT REPORTED THAT ON CHECKING THE RT MAGNETO THERE WAS AN EXCESSIVE RPM DROP BUT THAT THE ENGINE STILL OPERATED SM	OOTHLY ON THAT MAGNETO. UPON DISASSEMBLY OF THE MAG IT WAS FOUND THAT ONE LEG OF THE CAM SLOT ON THE ROTOR SHAFT WAS COM	PLETELY BROKEN OFF AT THE BOTTOM OF THE SLOT.  (K)																	 
2008031300047	20080313	00047	SO  	2008	3	13	21808            	1	20080218	G	4910	1159AC30551103	DUCT            			GULSTM	G1159 	GIV         	3980115	SO  										APU INLET	CRACKED         	E			CLWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	589HM	6464 				1153				A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).						2	L	7	2 	4F			RT	A12EA   					 
2008031300045	20080313	00045	SO  	2008	3	13	218081153        	1	20080218	G	4910	1159AC30551103	DUCT            			GULSTM	G1159 	GIV         	3980115	SO  										APU INLET	CRACKED         	E			CLWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	589HM	6464 				1153				A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).						2	L	7	2 	4F			RT	A12EA   					 
2008020400103	20080204	00103	EA  	2008	2	4	22497            	2	20080131	G	8530	AEL14995	RETAINER        	ECI         		PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O360  	O360C4P     	42289	EA  					PUSH ROD	BROKEN          	B			WS9R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	8780D					186308	L4080536E			ENGINE WAS DISASSEMBLED AND INSPECTED FOR PROP STRIKE INSPECTION.  DURING TEST CELL OPERATION THE TECHNICIAN NOTICED AN 	OIL LEAK AT THE NR4 CYLINDER.  FURTHER INSPECTION REVEALED THAT THE PUSH ROD TUBE RETAINER BROKE INSIDE THE ROCKER COVER	 CAUSING THE TUBE AND SEAL TO FALL OUT OF POSITION.				1	H	7	1 	3O	3	O		1A2     	E286				 
	20080520		CE  	2008	5	20	2568             	1	20080501	G	3240	215286	BRAKE ASSY      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT MLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	19	330DK					5500266				RT MLG BRAKE LOCK UP DURING TAXI.  AN INSP BY MAINT HAS DETERMINED THAT THE BRAKE STATOR CAME APART AND LOCKED UP THE BR	AKE. THE C/A GIVEN WAS FOR THE REMOVAL AND REPLACEMENT OF THE OF THE RT WHEEL AND TIRE ASSY AND BRAKE.  A GEAR SWING WAS	 ALSO PERFORMED IAW MM 32-00.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008041400014	20080414	00014	EU  	2008	4	14	325              	1	20080325	G	3233	D52177	HOLDER          	MESSIER     		AMD   	FALC20	FALCON200   	2730150	EU  										ACTUATOR	BROKEN          	B			GQRR	O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			SW	05					DRI76878					THE PACKING HOLDER BROKE IN 2 PIECES CAUSING HYDRAULIC FLUID LOSS.  THIS PART HAD BEEN MODIFIED IAW SB F200-110 TO PREVE	NT FUTURE FAILURES.  THIS IS THE SECOND PACKING HOLDER FOUND TO BE BROKEN AFTER MODIFICATION. BOTH PARTS WERE MODIFIED A	ND IDENTIFIED SDR IAW THE SB.				2	L	7	2 	4F			RT	A7EU    					 
2008020400107	20080204	00107		2008	2	4	43385883         	4	20080129	G	3460	8220868044	FMC             			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  						MALFUNCTIONED   	C				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			EA	23	808BL					258634				UNCOMMANDED 360 DEGREE TURN AS COMMANDED BY THE FMS.  SB 0057-05 DATED DECEMBER 21, 2005 DELETING A WAYPOINT MAY CAUSE T	HE FMS TO INSERT AND FLY AN UNINTENDED TURN.  KNOWN PROBLEM WITH OPTIONAL SOLUTION FOR FMS6000 NO SOLUTION FOR FMS5000 I	NSTALLED IN AC.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2008040200014	20080402	00014		2008	4	2	433858831        	4	20080129	G	3461	8220891008	FMC             			BEECH 	MU300 	400A        	1155402	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  						FAULTED         	C				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			EA	23	808BL					RK367				UNCOMMANDED 360 DEGREE TURN AS COMMANDED BY THE FMS.  REF SB 0057-05 DATED DECEMBER 21, 2005 DELETING A WAYPOINT MAY CAU	SE THE FMS TO INSERT AND FLY AN UNINTENDED TURN.  KNOWN PROBLEM WITH OPTIONAL SOLUTION FOR FMS6000 INSTALLED IN AC, NO S	OLUTION FOR FMS5000 INSTALLED IN AC.				2	H	7	2 	4F	4	F	RT	A16SW   	E6WE				 
	20080710		EU  	2008	7	10	5APR577Y1        	1	20080515	G	3242	244755	BRAKE DISC      	BFGOODRICH  		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RT MLG	BROKEN          	B			5APR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	591AF	1174 	1174 		0137	591	PR0454	KX164		DURING AN ANNUAL INSPECTION THE RIGHT MAIN WHEEL WAS REMOVED TO REPACK THE WHEEL BEARINGS WHEN IT WAS DISCOVERED THAT TH	E OUTBOARD BRAKE DISK ON THE RIGHT BRAKE WAS BROKEN INTO TWO PIECES.  THE BRAKE ASSEMBLY WAS REMOVED AND REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080710		EU  	2008	7	10	5APR577Y2        	1	20080515	G	3242	244755	BRAKE DISC      	BFGOODRICH  		PILATS	PC12  	PC1247      	7090552	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT MLG	BROKEN          	B			5APR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	729AF	1566 			0599	729	PR0603	KX359		DURING ANNUAL INSPECTION THE LEFT MAIN WHEEL WAS REMOVED TO REPACK THE BEARINGS AND THE TWO OUTBOARD BRAKE DISCS ON THE 	LEFT BRAKE WERE FOUND TO BE BROKEN.  REMOVED AND REPLACED BRAKE ASSEMBLY.					1	L	7	1 	4T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080710		EU  	2008	7	10	5APR577Y3        	1	20080515	G	3242	244755	BRAKE DISC      	BFGOODRICH  		PILATS	PC12  	PC1247      	7090552	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RT MLG	BROKEN          	B			5APR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	65	729AF	1566 			0593	729	PR0603	KX359		DURING ANNUAL INSPECTION RIGHT MAIN WHEEL WAS REMOVED TO REPACK BEARINGS AND THE MIDDLE BRAKE DISC WAS FOUND TO BE BROKE	N.  REMOVED AND REPLACED BRAKE ASSEMBLY.					1	L	7	1 	4T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008041400016	20080414	00016	CE  	2008	4	14	6001LENG         	1	20080327	G	5415	555415046810	ATTACH ANGLE    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6001L	10071				5500169				ENGINE NACELLE ATTACHING FITTING ANGLE REMOVED FOR CORROSION. PARTS ARE CADMIUM PLATED, BUT NOT PAINTED. ALSO DISCOVERY 	IMPROPER DRILL HOLES AND RIVET SET DAMAGE AROUND SEVERAL HOLES.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008050800053	20080508	00053	CE  	2008	5	8	6001LOXYGEN      	1	20080423	G	3510	176174	OXYGEN BOTTLE   			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NOSE	LEAKING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6001L					5500169				INSTALLED REPAIRED EMERGENCY OXYGEN BOTTLE IN AC AND SERVICED.  WHEN BOTTLE WAS TURN ON WAS FOUND TO LEAK FROM ON-OFF VA	LVE.  UNIT WAS REPAIRED ON JANUARY 21,2008.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20080717		CE  	2008	7	17	772AF            	1	20080603	G	3610	13022	CHECK VALVE     			BEECH 	200   	B200        	1152922	CE  										BLEEDD AIR SYS	DEFECTIVE       	B			VIBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	772AF	5763 				BB1001				FLAPPERS IN BLEED AIR INLET CHECK VALVE CAME LOOSE AND CHAFED THE INSIDE OF THE HOUSING.  ONE FLAPPER CHAFED A HOLE THRO	UGH THE HOUSING.					1	L	7	2 	4T				A24CE   					 
	20080902		CE  	2008	9	2	842008N341CS     	1	20080730	G	3240		BRAKE           			CESSNA	500   	550         	2076604	CE  										MLG	CONTAMINATED    	C				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			EA	63	341CS					5501106				THE LOW BRAKE PRESSURE AND ANTI-SKID INOP ANNUNCIATORS ILLUMINATED IN FLIGHT.  AN EMERGENCY WAS DECLARED.  DURING LANDIN	G ROLL OUT BRAKE PRESSURE CAME BACK AND LIGHTS EXTINGUISHED.  THE BRAKES WERE BLED, A SMALL AMOUNT OF AIR NOTED.  OPERAT	IONAL CHECK OK.  ACFT MADE THREE TAKEOFFS AND LANDINGS WITH NO DEFECTS NOTED.  ACFT RETURNED TO SERVICE.  (S)				1	L	7	2 	4F				A22CE   					 
2008022500006	20080225	00006	SW  	2008	2	25	901012008        	1	20080217	G	5210	S16206327957	DOOR            			SKRSKY	S58T  	S58T        	8141800	SW  	PWA   	PT6T  	PT6T6       	52045	EA  					MAIN	DEPARTED        	L				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			GL	23	901CH	15313	15313			581464				DURING POSTFLIGHT INSP, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSP OF AC FOUND NO DAMAGE OR MISSING CO	MPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED TO AIRFRAME, DOOR M	OUNTING, STRUCTURE AND DOOR OPERATION.  AC WAS RETURNED TO SERVICE.				2	G	7	1 	4U	4	U	NC	1H11    	E22EA				 
2008031900266	20080319	00266	SW  	2008	3	19	9010208          	1	20080217	G	5210	S16206327957	DOOR            			SKRSKY	S58T  	S58T        	8141800	SW  	PWA   	PT6T  	PT6T6       	52045	EA  					ZONE 800	DEPARTED        	L				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			GL	23	901CH	15313	15313			581464				DURING POSTFLIGHT INSPECTION, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSPECTION OF AIRCRAFT FOUND NO DA	MAGE OR MISSING COMPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED T	O AIRFRAME, DOOR MOUNTING, STRUCTURE AND DOOR OPERATION. AIRCRAFT WAS RETURNED TO SERVICE.				2	G	7	1 	4U	4	U	NC	1H11    	E22EA				 
2008030600249	20080306	00249	SW  	2008	3	6	901CHI0208       	1	20080221	G	5210	S16206327957	DOOR            			SKRSKY	S58T  	S58T        	8141800	SW  	PWA   	PT6T  	PT6T6       	52045	EA  						DEPARTED        	L				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			GL	23	901CH	15313	15313			581464				DURING POSTFLIGHT INSPECTION, AFTER LANDING, MAINT DISCOVERED CABIN DOOR WAS MISSING. INSP OF AC FOUND NO DAMAGE OR MISS	ING COMPONENTS OTHER THAN DOOR. REPLACEMENT DOOR WAS INSTALLED AND OPS CHECKED WITH NO DISCREPANCIES NOTED TO AIRFRAME, 	DOOR MOUNTING, STRUCTURE, AND DOOR OPERATION. AIRCRAFT WAS RETURNED TO SERVICE.				2	G	7	1 	4U	4	U	NC	1H11    	E22EA				 
	20080520		CE  	2008	5	20	90XR042708       	1	20080427	G	2910	AS62306H0073	LINE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					HYDRAULIC SYS	CHAFED          	E			T6FA	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			GL	09	90XR	342  				2090				DURING CRUSE FLIGHT THE PILOTS NOTED THAT MAIN HYDRAULIC SYSTEM LOST PRESSURE.  INITIATED AN UNSCHEDULED LANDING.  AFTER	 INSPECTION, THE LT ENGINE DRIVEN HYDRAULIC PRESSURE PUMP LINE WAS LEAKING.  THE PRESSURE LINE AND BOTH HYDRAULIC PUMPS 	WERE REPLACED, WITH NEW PARTS, IAW THE MM.				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
	20081209		WP  	2008	12	9	AALA200810280    	1	20081112	G	5320		INTERCOSTAL     			DOUG  	DC9   	DC983       	3022083	WP  										ZONE 100	CRACKED         	A			AALA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21	9401W					53137				INTERCOSTAL CRACKED IN CEILING OF MID CARGO.  REPLACED INTERCOSTAL.						2	L	7	2 	4F			RT	A6WE    					 
	20080903		NM  	2008	9	3	ABXR080225       	1	20080729	G	5330		SKIN            			BOEING	767   	767223      	1385123	NM  										BS 615 S34R	DAMAGED         	C			ABXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	761CX					22318				SCREW AND COUNTERSINK WASHER INSTALLED IN FUSELAGE SKIN OVER PREVIOUSLY BLENDED AREA AT APPROX STA 615 LONGERON STRINGER	 34 RT.  DAMAGED AREA COMPLIED WITH ON PREVIOUS REPAIR.  (S)					2	L	7	2 	4F			RT	A1NM    					 
	20080903		NM  	2008	9	3	ABXR080226       	1	20080731	G	5330	146T35111	SKIN            			BOEING	767   	767223      	1385123	NM  										BS 1510 S35-36L	DAMAGED         	C			ABXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	761CX					22318				APPROX 6 INCH CREASE AT STA 1510, LONGERON STRINGER 36-35 LT, BELOW BULK CARGO DOOR IS OUT OF LIMITS.  REPAIRED SKIN IAW	 B767-200 SRM 53-60-1.  (S)					2	L	7	2 	4F			RT	A1NM    					 
	20080903		NM  	2008	9	3	ABXR080228       	1	20080801	G	5330	143T35211	SKIN            			BOEING	767   	767223      	1385123	NM  										BS 544 S30-31L	DENTED          	C			ABXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	761CX					22318				OUTWARD DENT STA 544, STRINGER 31-30 LT REQUIRES REPAIR.  REPAIRED AREA IAW B767 SRM 53-00-01, FIGURE 201.  (S)						2	L	7	2 	4F			RT	A1NM    					 
2008040400016	20080404	00016	EA  	2008	4	4	ACOR032408001    	2	20080324	G	7322	383493	PLUG            	PREAIR      	RSA5        	CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SERVO	LOOSE           	B			ACOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	2162Y	1618 			70402806	172S9529	L3118151A			FUEL SERVO REGULATOR HEX PLUG LOOSE ON NON AFFECTED SERVO RSA-5 S/N 70402806.  DATA REFERENCED AD 2008-06-51 E, SB 08-73	-01, AND PRECISION SB PRS-107. SERVO HAS NOT BEEN NEW, REBUILT, OVERHAULED, OR REPAIRED ON OR SINCE AUGUST 22, 2006.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008040400017	20080404	00017	EA  	2008	4	4	ACOR032508001    	2	20080325	G	7322	383493	PLUG            	PREAIR      	RSA10ED1    	CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					FUEL SERVO	LOOSE           	B			ACOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	39	377HA	604  			70259806	T20608499	L1183961A			FUEL SERVO REGULATOR HEX PLUG LOOSE ON NON AFFECTED SERVO RSA-10 S/N 70259806. DATA REFERENCED AD 2008-06-51 E, SB 08-73	-01, AND PRECISION SB PRS-107. SERVO HAS NOT BEEN NEW, REBUILT, OVERHAULED, OR REPAIRED ON OR SINCE AUGUST 22, 2006					1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2008041000201	20080410	00201	CE  	2008	4	10	AMCR200800001    	1	20080331	G	7312	79646	HEATING ELEMENT 			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RT ENGINE	FAILED          	B			AMCR	O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			GL	09	279DV	636  				070	141148			PILOT REPORTED T2 HEATER FAIL ON RT ENGINE. FOUND T2 PROBE BAD.						1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2008040400009	20080404	00009	CE  	2008	4	4	B3OR20080079     	1	20080318	G	3233	991206313	ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	OUT OF POSITION 	B			B3OR	D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			SW	03	26621		8    			5500593				AIRCREW REPORTED LANDING GEAR WARNING HORN SOUNDED AND GEAR-IN-TRANSIT INDICATOR ILLUMINATED AS AIRCRAFT WAS BEING TOWED	 OVER A BUMP (HANGAR THRESHOLD).  SCHEDULED FLIGHT WAS CANCELLED.  MAINTENANCE CREW WAS ABLE TO DUPLICATE EVENT BY SLIGH	T ACCELERATION OF TOW VEHICLE AND OBSERVED NOSE GEAR DOWN AND LOCKED INDICATOR ALSO EXTINGUISHED IN CONJUNCTION WITH THE	 OTHER REPORTED INDICATIONS.  THE ACTUATOR DEFLECTION TEST IN THE AIRFRAME MM WAS ACCOMPLISHED TO DETERMINE THE SERVICEA	BILITY OF THE ACTUATOR'S INTERNAL DOWNLOCK MECHANISM WITH SATISFACTORY RESULTS.  DOWNLOCK INDICATOR SWITCH ADJUSTMENT CO	ULD NOT BE VERIFIED DUE TO AN ABSENCE OF REQUIRED TESTING EQUIPMENT.  THE RECENTLY OVERHAULED ACTUATOR WAS REMOVED FOR R	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008040200009	20080402	00009	NE  	2008	4	2	B3OR2008030      	2	20080125	G	7321	0164548240	FCU             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	LEAKING         	B			B3OR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5204J		176  			3118	9318			FUEL CONTROL UNIT IS LEAKING FUEL FROM A DIAPHRAM BREATHER HOLE IN THE CASING.  THE LEAKING HOLE IS LOCATED BELOW AND SL	IGHTLY IB OF THE PRESSURE REDUCING VALVE ATTACHED TO THE FCU.FUEL LEAK WAS INITIALLY OBSERVED AS A SEEP, PROGRESSING T	O A LOW PRESSURE STEADY TRICKLE THROUGHOUT MULTIPLE ENGINE RUNS.  ALL OTHER FUEL CONTROL FUNCTIONS WERE OPERATING NORMAL	LY.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008040300038	20080403	00038	EU  	2008	4	3	B3OR2008046      	1	20080213	G	2910	704A44831141	SERVO CONTROL   			SNIAS 	350   	AS350B2     	8680813	EU  										LT HYD SYSTEM	LEAKING         	B			B3OR	K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			SW	03	5204J	5313 	2137 			3118				ON A ROUTINE PREFLIGHT INSPECTION, THE LT HYDRAULIC ROLL CONTROL SERVO WAS DISCOVERED TO BE LEAKING HYDRAULIC FLUID AT T	HE PISTON SHAFT SEAL.  THE LEAK COULD NOT BE DUPLICATED DURING GROUND TESTING WITH A HYDRAULIC POWER CART IAW THE MM INS	TRUCTIONS.  SUBSEQUENT FLIGHT TESTING REVEALED THE LEAK PERSISTING WITH A LEAK RATE SUSPECTED TO BE SLIGHTLY OUT OF LIMI	TS.  OF PARTICULAR NOTE: THE LEAK COULD ONLY BE DUPLICATED WHILE ACTUAL FLIGHT LOADS WERE INDUCED. ASIDE FROM THE LEAK, 	THE HYDRAULIC SERVO WAS REPORTED TO BE FUNCTIONING NORMALLY.  UNIT WAS REPLACED.		1	G	7	1 	3U				H9EU    					 
	20081124		NM  	2008	11	24	B62R20081106002  	1	20081106	G	5411	313W181338113813	SPAR            			BOEING	777   	777236      	1385220	NM  										NR 2 PYLON	CORRODED        	B			B62R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	702BA	35345				27108				NR 2 ENG PYLON STRUT, AFT FAIRING HEAT SHIELD LOWER SPAR STRUCTURE, PITTING CORROSION FOUND THROUGHOUT SPAR STRUCTURE, C	HORDS, FRAMES 3, 4 & 5.  EVIDENCE OF PITTING CORROSION AND HEAT DAMAGE ON LOWER SIDE OF WEBS.  REF 54-51-71 PG 6.  POSSI	BLE CAUSE WAS AFT FAIRING HEAT SHIELD THERMAL BLANKETS 1 THRU 6 WERE TORN AND WATER LOGGED, SEALS DAMAGED AND STRUT DRAI	N CLOGGED.  REF AMM 54-54-01 PG 426, 54-54-03 PG 406 AND 54-55-01.  AD 2002-07-07 AND SB 777-54A0017 ARE RELATED TO THIS	 BUT HAVE NOT BEEN ACCOMPLISHED.  COMPLIANCE WITH AD WILL CORRECT CONDITION.  NOTE:  STRUT DRAIN WAS CLOGGED.  PRIMARY F	IRE SEAL DAMAGED.  HEAT SHIELD SEAL DAMAGED.  SECONDARY FLUID SEAL DAMAGED.  PARTS WILL REQUIRE REPAIR OR REPLACEMENT.	2	L	7	2 	4F			RT	T00001SE					 
	20081124		NM  	2008	11	24	B62R20081107003  	1	20081107	G	5411	313W3813X	FRAME           			BOEING	777   	777236      	1385220	NM  										PYLON	CRACKED         	B			B62R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	702BA	35345				27108				NR 1 & NR 2 ENG PYLON, STRUT AFT FAIRING HEAT SHIELD SPAR STRUCTURE, NR 5 FRAME P/N 313W3813-X HAS A 4.50 INCH CRACK ON 	THE LOWER AFT INBD CORNER.  CRACK IS IN THE SAME LOCATION ON BOTH NR 1 & NR 2 ENG PYLON FRAMES.  NR 2 ENG PYLON FRAMES N	R 1 THRU NR 4, P/N'S 313W1813-X & 313W3813-X HAVE EVIDENCE OF HEAT DAMAGE AND SURFACE CORROSION.  REF SRM 54-51-71 FIGUR	E 4.  POSSIBLE CAUSE WAS AFT FAIRING HEAT SHIELD THERMAL BLANKETS NR 1 THRU NR 6 (NR 2 ENG PYLON) AND NR 6 (NR 1 ENG PYL	ON) WERE TORN AND WATER LOGGED.  REF AMM 54-54-01 PG 426, 54-54-03 PG 406 AND 54-55-01 PG 623.  AD 2002-07-07 AND SB 777	-54A0017 ARE RELATED TO THIS BUT HAVE NOT BEEN ACCOMPLISHED.  COMPLIANCE WITH AD WILL CORRECT CONDITION.	2	L	7	2 	4F			RT	T00001SE					 
	20081121		NM  	2008	11	21	B62R20081121001  	1	20081106	G	5320	149W1129111037	INTERCOSTAL     			BOEING	777   	777236      	1385220	NM  										FUSELAGE	CORRODED        	B			B62R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	702BA	35345				27108				SECTION 43 WING TO BODY FAIRING STRUCTURE LT SIDE.  INTERCOSTALS THAT SUPPORT THE FWD WING TO BODY FAIRINGS HAVE MODERAT	E TO SEVERE CORROSION.  SURFACE, PITTING, GALVANIC AND EXFOLIATION CORROSION ARE EVIDENT ON THE UPPER AND LOWER FLANGES 	COMMON TO THE NUT PLATES.  THERE IS EVIDENCE OF MOISTURE AND STANDING WATER IN THE AREA FROM STA 888 TO STA 1040 LT SIDE	.  SOME INTERCOSTALS WILL REQUIRE REPAIR OR REPLACEMENT.  REF SRM 53-30-71-01-1.			2	L	7	2 	4F			RT	T00001SE					 
2008022500241	20080225	00241		2008	2	25	CA080101001      	4	20080101	G	3418	501177003	ACTUATOR        			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348C5B1   	30052	NE  					STICK PUSHER	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) ONLY ON LANDING WHEN THE PILOTS HAVE FLARED THE NOSE UP AND THE MLG HITS THE GROUND DOES THE ELEVATOR SEEM TO LOCK	 UP PREVENTING THE PILOTS FROM PRESSING THE NOSE DOWN TO LAND.  TOOK THE COVER OFF THE REMOVED STICK PUSHER ACTUATOR AND	 FOUND : 1) NOTICE THE TEETH MARKS AT THE SUPPORT POST NEXT TO THE GEAR. 2) SET SCREW WHICH IS STUCK TO THE MOTOR, THIS 	IS WHAT WE HEARD WHEN SHAKING THE UNIT.  3) THE SCREW WHICH WAS BOUNCING AROUND INSIDE THE BOX, LOOKS LIKE AT SOME POINT	 IT WAS JAMMED BETWEEN THE DRIVE GEAR AND SUPPORT POST AS EVIDENCED BY TEETH MARKS ON THE SUPPORT POST. (TC NR 200801010	01)	2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008022500250	20080225	00250	EA  	2008	2	25	CA080102001      	1	20080101	G	2750	601R930507	FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	UNSERVICEABLE   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) ON APPROACH, GOING THROUGH 6500FT AT 200KTS, FLAP FAIL MESSAGE ILUMINATED WHEN SELECTED FROM 0 TO 8 DEGREES. FLAPS	 DID NOT MOVE, REMAINED AT 0 DEGREES. FLAPLESS LANDING CARRIED OUT WITHOUT FURTHER INCIDENT. NOTE: NO SKEW DETECTION LIG	HTS WERE ILLUMINATED. FAULT CODES RETRIEVED AND HAVE DETERMINED THAT THE NR1 FECU IS AT FAULT. FECU CHANGED IAW THE AMM 	27-51-0. RIG AND FUNCTION CHECKS CARRIED OUT, NO FURTHER MESSAGES OR CODES. AIRCAFT RETURNED TO SERVICE AND NO FURTHER I	SSUES NOTED. (TC NR 20080102001)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500252	20080225	00252	CE  	2008	2	25	CA080102002      	1	20080101	G	5753	3516505035	BRACKET         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	TE FLAPS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6626 								(CAN) FLAPS REMOVED TO INSPECT FLAP BRACKETS (HINGES) TO PREVENT A POSSIBLE FAILURE ( REFERENCE SDR 20071025007). BOTH O	B FLAPS WERE WORN IN THE SAME LOCATION THAT FAILED OTHER AC. ON BOTH OB FLAPS, THE OB HINGE, IB BRACKETS P/N: 35165050-3	5 (LT) AND 35-165050-34 (RT), AND THE IB HINGE, OB BRACKET P/N: 35-165050-30 (LT) AND 35-165050-31 (RT). (TC NR 20080102	002)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2008022500256	20080225	00256	EA  	2008	2	25	CA080102006      	1	20080101	G	5610	NP13932114	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) (RT WINDSHIELD SHATTERED IN FLIGHT).  THE WINDSHIELD WAS REMOVED AND REPLACED.   WINDSHIELD, (RT) P/N OFF: 601R330	33-14 P/N ON: NP-139321-14 S/N OFF: 02277H7295 S/N ON: 07212H4821 (TC NR 20080102006)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500263	20080225	00263	SW  	2008	2	25	CA080103007      	1	20080103	G	6720	NAS130410	BOLT            	BELL        	206001044   	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					T/R PEDAL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION OF THE AIRCRAFT IT WAS NOTED THAT THE (1) OF THE (3) BOLTS WAS BROKEN AND THE OTHERS SHOWED SIGNS OF	 CORROSION ALL (3) BOLTS WHERE REPLACED WITH NEW. (TC NR 20080103007)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008022500265	20080225	00265	EA  	2008	2	25	CA080104001      	1	20080103	G	2750	855D10096	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CREW FLYING AT LEVEL 340 FOR 30 TO 40 MIN AND THE FLAP FAIL CAME ON WITH NO SELECTION, FLAPS AT 0 DEG. O FLAP LAND	ING. TEMP AT ALTITUDE WAS -60 DEG.  FERRIED BOTH BPSU`S REPLACED FLAPS FUNCTIONED CHECKED SER (804406 1/4/2008 06:57) (T	C NR 20080104001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008031900171	20080319	00171	EA  	2008	3	19	CA080104004      	1	20080101	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			14801	10343							(CAN) DURING PUSH BACK CREW SELECTED FLAPS TO 20 DEGREES AND RECEIVED A FLAP FAIL CAUTION MESSAGE. MAINT TROUBLESHOOTING	 LED TO REPLACEMENT OF RT BRAKE POSITION SENSOR UNIT (BPSU) AND RIGGING OF LT AND RT BPSUS. OF NOTE THE FIRST NEWLY INS	TALLED RT BPSU (S/N 172, TSN 17175, TSO 4879, CYCLES 3697) HAD TO BE REPLACED AS IT FAILED THE ELECTRICAL RIGGING. (TC N	R 20080104004)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500268	20080225	00268	SW  	2008	2	25	CA080104005      	1	20080104	G	6220	206011101109	YOKE            		206L1       	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					M/R HUB	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10379	135  		GDLM53264					(CAN) FOUND TO BE WRONG, YOKE M/R HUB ASSY, WITH THE INCORPORATION OF STC NR SH296NM, INSTALLATION OF ENGINE. CORRECT PN	 OF YOKE SHOULD BE 206-011-149-101. (TC NR 20080104005)					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2008022500269	20080225	00269	NM  	2008	2	25	CA080105002      	1	20080102	G	2910	992236H18697	SWITCH          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) SDR BEING SUBMITTED DUE TO (3) OCCURRENCES OF (RUD PRESS) AND (RUD FULL PRESS) CAUTION MESSAGES OVER A PERIOD OF (	4) DAYS. (1ST) EVENT OCCURRED DECEMBER 30, 2007 JUST AFTER TAKEOFF AND CAUSED AN AIR TURN BACK TO THE DEPARTURE AIRPORT.	 MAINT PERFORMED GROUND CHECK, THEN AN OPS CHECK IAW AMM 27-30-38 WITH NO FAULTS FOUND. (2ND) EVENT OCCURRED ON DECEMBER	 31, 2007 AGAIN JUST AFTER TAKEOFF. AC RETURNED TO AIRPORT OF DEPARTURE. MAINT TROUBLESHOOTING FOUND RUDDER PRESSURE DRO	PS APPROXIMATELY 800-1000 PSI ON NR 1 HYD SYS. RUDDER PRESSURE REGULATOR REPLACED BUT WITH NO FIX.  NR 1 HYD SYS BLED AN	D ALSO NO FIX.  NR 1 LWR ACTUATOR (PN 11200-1 SN UNK) WAS REPLACED AND OPERATION CHECKED IAW AMM 27-20-01 PG 215. (3RD) 	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008022500271	20080225	00271	WP  	2008	2	25	CA080105003      	1	20080101	G	8011	BC31510040	STARTER         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			679  								(CAN) ENGINE WOULD NOT START, STARTER NOT ENGAGING. SERVICEABLE STARTER INSTALLED, ENGINE STARTED WITH OUT FURTHER INCID	ENT. (TC NR 20080105003)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008031900173	20080319	00173	EA  	2008	3	19	CA080106001      	1	20080104	G	2150	78279015	ACM             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NR 1	SMOKE           	W				C				ABORTED TAKEOFF         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) SMOKE IN COCKPIT AND CABIN ON T/O ROLL.  DURING T/O ROLL, SMOKE APPEARS IN THE COCKPIT AND CABIN FIRSTS ROWS. ABOR	TED T/O, RETURN TO BLOCKS. ACM NR1 DETERMINED TO BE THE SOURCE OF THE SMOKE. ACM NR1 DEFERRED IAW MMEL 21-51-1. (TC NR 2	0080106001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008031900175	20080319	00175	EA  	2008	3	19	CA080106003      	1	20080103	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	INOPERATIVE     	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) FLAP FAIL MESSAGE DISPLAYED WHILE AC PARKED AT THE GATE. TROUBLESHOOTING REVEALED BRAKE AND POSITION SENSOR UNIT (	BPSU) RT AND LT OUT OF LIMITS.  MAINTENANCE RIGGED LT BPSU AND REPLACED RT BPSU. (TC NR 20080106003)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008031900178	20080319	00178	EA  	2008	3	19	CA080106004      	1	20080102	G	3260	895001	PROXIMITY SENSOR			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5     	30050	NE  					NLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, A LANDING GEAR DISAGREE WARNING MESSAGE WAS DISPLAYED. CREW CYCLED THE GEAR UNTIL SELECTED DOWN AND	 GEAR LOCKED DOWN INDICATION (3 GREEN LIGHTS). AC PERFORMED A TURNBACK AND LANDED UNEVENTFULLY (AFTER FUEL DUMPING FOR N	OT LANDING OVERWEIGHT). TROUBLESHOOTING PINPOINTED TO THE WEIGHT OFF WHEELS NR 2 SENSOR (PX 11), BEING OFF RIGGING LIMIT	S. MAINT PERFORMED RE-RIGGING FOLLOWED BY A SUCCESSFUL GROUND TESTS AND AC RETURNED TO SERVICE. AIRFRAME HOURS=7855:04. 	CYCLES=3748. (TC NR 20080106004)		2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008022500272	20080225	00272	EU  	2008	2	25	CA080107001      	1	20080107	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  	LYC   	LTS101	LTS101*     		NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1592 	1592 							(CAN) ON DAILY INSPECTION, A CRACK IN THE TRAILING EDGE OF THE TIP OF THE TAILROTOR ASSY WAS FOUND. THE CRACK WAS APPROX	 .5 INCH LONG FROM TIP OF BLADE LEADING TO T/E ON A DIAGONAL.  SUSPECT THIS CRACK, IF LEFT, WOULD HAVE CAUSED THE TRAILI	NG EDGE CORNER APPROX .7500 OF AN INCH TO DEPART FROM TIP OF THE BLADE. THIS WAS FOUND ON BOTH BLADES ONE BLADE MORE SEV	ERE THAN THE OTHER. THERE WAS NO INDICATION OF A TAILROTOR IMPACT. (TC NR 20080107001)			1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2008022500273	20080225	00273	CE  	2008	2	25	CA080107002      	1	20080103	G	2497		BUSS BAR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	ELECTRICAL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			354  								(CAN) WHILE PERFORMING SB 24-3871, AN EXTRANEOUS BUSS BAR WAS OBSERVED IN THE RT CB PANEL BETWEEN CB 140 AND CB 255. THI	S BUSS BAR WAS ATTACHED ONLY AT ONE END AND WAS LOOSE. NOTE, THE SB ONLY REQUIRES INSPECTION FOR AN EXTRA BUSS BAR BETWE	EN CB 327 AND 166. INSPECTION OF BB-1974 SHOWED NO EXTRANEOUS BUSS BARS INSTALLED. (TC NR 20080107002)				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2008020400119	20080204	00119	CE  	2008	2	4	CA080107003      	1	20080107	G	3230	1018100327	TORQUE KNEE     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING AN INSPECTION ON THE GEAR IT WAS NOTICED THAT GREASE WAS COMING FROM THE HORIZOTAL CRACK IN THE B	OTTOM OF THE TORQUE KNEE. A NEW KNEE WAS ORDERED AND REPLACED. (TC NR 20080107003)					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2008020400118	20080204	00118	NM  	2008	2	4	CA080107004      	1	20080102	G	6420	A0311	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					PITCH CONTROL	ROUGH           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1722 								(CAN) WHILE DOING AD 2003-04-04 THE BEARINGS WERE FOUND ROUGH ON ROTATION. PART WAS REPLACED WITH NEW. (TC# 20080107004)						1	G	7	1 	3O	3	O		H10WE   	E286				 
200805131    	20080513	1    	EU  	2008	5	13	CA080108005      	1	20080107	G	3610	9599021231	HOSE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BLEED AIR SYS	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			9247 								(CAN) ON CLIMB OUT TO CRUISE ALTITUDE, IT WAS DISCOVERED THE AC WOULD NOT PRESSURIZE, AND THERE WAS NO BLEED AIR HEAT. A	C RETURNED TO BASE. FOUND BLEED AIR HOSE CRACKED. (TC NR 20080108005)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
200805141    	20080514	1    	EA  	2008	5	14	CA080108006      	1	20080108	G	5752	215150622	SKIN            	CNDAIR      	2151506180  	CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	AILERON TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3481 								(CAN) AC UNDERGOING TURBO-PROP CONVERSION AT PRESENT.  RT AILERON GEAR TAB INSPECTION REVEALED A CRACK IN THE LOWER SKIN	 UNDER THE LOWER IB MASS BALANCE WEIGHT MOUNT.  THE CRACK IS APPROX 1.75 IN. LONG AND LOCATED LATERALLY, FWD OF THE BALA	NCE WEIGHT MOUNT ATTACHMENT FASTENER HOLES. THE REPLACEMENT GEAR TAB WAS INSPECTED AND FOUND CRACKED IN THE SAME LOCATIO	N. THE CUSTOMER AND OEM HAVE BEEN INFORMED. (TC NR 20080108006)			2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2008020400117	20080204	00117	EA  	2008	2	4	CA080108007      	1	20080103	G	7603	C6CE13151	RELEASE CABLE   			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BETA SYSTEM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RT POWER CONTROL WAS REPORTED STIFF. AFTER AN INSPECTION ON THIS AREA IT WAS NOTICED THE THE BETA RELEASE CABL	E HAD BROKEN AND WAS CAUSING THE POWER CABLE TO BE STIFF. A NEW CABLE WAS PURCHASED AND CABLE WAS CHANGED. (TC NR 200801	08007)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008020400116	20080204	00116	WP  	2008	2	4	CA080108009      	1	20080108	G	7603	B5642	LINK            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					THROTTLE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			721  								(CAN) WHILE CONDUCTING AN INSPECTION, IT WAS NOTED THAT THE BEARING LOOKED TO BE SEPERATED FROM THE LINK. THE LINK WAS R	EMOVED AND INDEED IT WAS. THE LINK AND NEW WASHERS (SB-62) WERE INSTALLED AND NO OTHER ISSUES WERE NOTED. WHILE CONDUCTI	NG RECENT THROTTLE LINKAGE WASHER INSTALLATION, WE ALSO NOTED THAT SOME OF THE LINKS HAD LITTLE SURFACE DAMAGE ON OTHER 	LINKS PRE-SB WASHER INSTALLATION. (TC NR 20080108009)			1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008020400115	20080204	00115	WP  	2008	2	4	CA080109001      	1	20080108	G	3260	BZE67RNT	DOWNLOCK SWITCH 			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	RT MLG	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) CREW REPORTED RT MLG GEAR UNSAFE LIGHT ILLUMINATED. REPLACED RT MLG DOWNLOCK SWITCH P/N BZE6-7RNT AND RETURNED TO 	SERVICE. (TC NR20080109001)					2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
2008020400114	20080204	00114	NM  	2008	2	4	CA080109002      	1	20080104	G	3233	NAS771236	BUSHING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG ACTUATOR	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN)  REMOVED NR2 MLG RETRACTION ACTUATOR FOR WORK CARD 2339 AND FOUND THE PICKUP FITTING MISSING (HAT) BUSHING. HOWEVE	R, THE RETRACTION ACTUATOR WAS ASSEMBLED TO FITTING AND IN SERVICE WITHOUT THIS BUSHING. THIS PLACED SEVERE STRESS ON AT	TACHMENT HARDWARE AND FITTING DUE TO THE IMPROPER ASSY.  NR2 MLG RETRACTION ACTUATOR FITTING REPLACED ALONG WITH ALL HAR	DWARE.  NR2 MLG RETRACTION ACTUATOR REPLACED.  RD8-54-1178 ACCOMPLISHED ALONG WITH NDT INSPECTION TO AFFECTED NACELLE ST	RUCTURE.  MISSING BUSHING REFERENCE: IPC 54-40-00, FIG. 20, ITEM 410, P/N NAS77-12-36. (TC NR 20080109002)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008020400113	20080204	00113	NM  	2008	2	4	CA080109004      	1	20080108	G	3260	H1010153	UPLOCK SWITCH   			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NLG	FAULTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FLIGHT WAS DEPARTING AND THEN DURING THE TAKEOFF ROLL, THE CREW SELECTED THE LANDING GEAR UP. WHEN THE GEAR HAD CY	CLED UP THERE REMAINED A RED NOSE GEAR UNSAFE LIGHT. THE CREW CYCLED THE LANDING GEAR 3 TIMES BEFORE THE UNSAFE LIGHT EV	ENTUALLY WENT OUT. THE AIRCRAFT RETURNED TO THE RAMP AND THE SYSTEM IS BEING TROUBLESHOT. THIS SDR WILL BE UPDATED WHEN 	A RECTIFICATION IS ESTABLISHED. (TC NR 20080109004)			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2008020400112	20080204	00112	NM  	2008	2	4	CA080109005      	1	20080105	G	2131		CIRCUIT BOARD   			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PRESS CONTROLLER	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			30004	30004		60498					(CAN) THE CREW REPORTED A STRONG BURNING ELECTRICAL ODOR UPON ARRIVAL. MAINTENANCE FOUND A FAULTY PRESSURE CONTROLLER. F	URTHER INVESTIGATION REVEALED THAT AN ELECTRONIC CIRCUIT BOARD INSIDE THE CONTROLLER HAD SOME BURN MARKS.  THE CONTROLLE	R WAS REPLACED AND THE AIRCRAFT RELEASED INTO SERVICE. (TC NR 20080109005)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008020400111	20080204	00111	EA  	2008	2	4	CA080109009      	1	20080107	G	7740	601509173	CONVERTER       			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A1     	30068	NE  					SIGNAL DATA	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA			6586 	6586 							(CAN) DURING ENGINE START, AT ABOUT 40 TO 50 PERCENT, N2, ALL LIGHTS ON THE ITT TAPE INSTANTLY LIGHTED UP. WE IMMEDIATEL	Y SHUTDOWN ENGINE. RESIDUAL ITT WAS ONLY 56 AND NR9702, AFTER MOTORING. VISUALLY INSPECTED THE ENGINE FOR SIGNS OF HEAT 	OR DAMAGE AND FOUND NOTHING. SUSPECTED INDICATION PROBLEM AND DECIDED TO TRY ANOTHER START. START WAS NORMAL.     WHILE 	WE CRUISED AT FL 390, ABOUT 50NM SOUTH,  NOTICED A HIGH ITT (ALL LIGHTS ON AGAIN) ON THE SAME LT ENGINE. IMMEDIATELY WE 	REDUCED THRUST TO REGAIN WITHIN LIMITS. ABOUT 5 MINUTES LATER, ITT STARTED RISING GRADUALLY, AGAIN WE REDUCED THRUST. CR	EW DISCUSSED ALTERNATE PLAN (DIVERTING), ITT STARTED AGAIN. KEPT REDUCING THRUST UNTIL WE HAD TO SHUTDOWN THE LT ENGINE 	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008020400110	20080204	00110	EA  	2008	2	4	CA080109011      	1	20080106	G	5610	NP13932110	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			5046 								(CAN) THE RT WINDSHIELD CRACKED WHILE IN CRUISE. WINDSHIELD WAS REPLACED IAW AMM. (TC NR 20080109011)						2	L	7	2 	4F			RT	A21EA   					 
2008020400109	20080204	00109	EU  	2008	2	4	CA080110001      	1	20080108	G	2571	L243M3810103	BATTERY BOX     			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			98   								(CAN) DURING A PREFLIGHT CHECK IT WAS NOTED THAT THE BATTERY TRAY WAS CRACKED.  REPLACED WITH NEW PART. (TC NR 200801100	01)					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2008033100037	20080331	00037	EA  	2008	3	31	CA080110003      	1	20080110	G	2797		CONNECTOR       			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5     	30050	NE  					TE FLAPS	FAILED          	W				C				ABORTED TAKEOFF         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) FLAP FAIL MESSAGE ON POWER UP. CODES READ AND BPSU NR 2 WIRING FAILED. MEL 27-51-02-1 APPLIED. WILL PROVIDE UPDATE	 WHEN MORE INFO BECOMES AVAILABLE (TC NR 20080110003)					2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008032000006	20080320	00006	EA  	2008	3	20	CA080110006      	1	20080105	G	2750	860D10018	FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAULTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			8560 	8560 							(CAN) THE CREW RECEIVED A FLAP FAIL .5 HR INTO THE FLIGHT CLIMBING BETWEEN 25000 TO 27000 FT. THE AC RETURNED WITHOUT IN	CIDENT. MAINT T/S WAS CARRIED OUT AND THE LT AND RT BPSUS WERE SWAPPED FOR T/S. SUSPECTED FAULTY FECU, FECU REPLACED, F	UNCTION CHECK C/O AND TEST FLIGHT C/O SATISFACTORY.  (TC NR 20080110006)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022500276	20080225	00276	NM  	2008	2	25	CA080111001      	1	20080110	G	5610	80260008	WINDSHIELD      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	BROKEN          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CO-PILOTS FORWARD WINDSHIELD SHATTERED IN FLIGHT AT 25,000 FEET. EMERGENCY DESCENT AND DIVERSION PERFORMED.  MAINT	 REPLACED THE WINDSHIELD AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20080111001)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008022500278	20080225	00278	SW  	2008	2	25	CA080111002      	1	20080107	G	5751	21993	HINGE           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1925 								(CAN) ON INSPECTION, 4 CRACKS FOUND IN CORNERS (TC NR 20080111002)						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2008030600205	20080306	00205	SW  	2008	3	6	CA080111003      	1	20080102	G	5751	21993	HINGE           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4718 								(CAN) CRACK FOUND DURING SIRP INSP (TC NR 20080111003)						1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2008030600206	20080306	00206	SW  	2008	3	6	CA080111004      	1	20080109	G	6410	212010750105	BLADE           	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317BLYC   	41616	NE  					TAIL ROTOR	DELAMINATED     	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			4047 			AHW00877					(CAN) PILOT HEARD A MUFFED LOW POP SOUND, WITH NO UNUSUAL GAUGE, WARNING LIGHTS, OR VIBRATIONS. UPON DEPARTING FOR ANOTH	ER SKI RUN THE PILOT AGAIN NOTED AN UNUSUAL NOISE. AC WAS LANDED, AN EXTERIOR INSP WAS CONDUCTED.  IT WAS THEN THAT THE 	DELAMINATING OF T/R BLADE WAS NOTED. AC REMAINED GROUNDED UNTIL ANOTHER SET OF T/R BLADES WERE INSTALLED. UPON INVESTIGA	TION OF THE T/R BLADE IT APPEARS THE DELAMINATING STARTED FROM A PREVIOUS REPAIR ALBEIT ON THE OTHER SIDE OF THE BLADE A	CCORDING TO THE COMPONENT LOG CARD. THE AIR FLOW STARTED TO PEEL BACK THE SKIN AT THIS SPOT, AS THE PEELING PROGRESSED S	KIN REMAINED INTACT UNTIL THE ADHESIVE STRENGTH OF THE GLUE WAS EXCEEDED AND WE SEE THE SECONDARY PEELING IB AND OB WHER	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008030600207	20080306	00207	NE  	2008	3	6	CA080111005      	2	20080111	G	7421	UREM38S	SPARK PLUG      								PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) (2) SEPARATE OCCASIONS NEW UREM38S SPARK PLUGS WERE REMOVED FROM THE PACKAGE AND FOUND TO HAVE CRACKED CERAMIC INS	ULATORS. TO VERIFY THE PLUGS WERE TESTED AND FOUND TO BE MISFIRING. THE CRACKING IN THE CERAMIC DOES NOT APPEAR TO BE SH	IPPING OR MISHANDLING DAMAGE AS THERE IS EVIDENCE OF TRACKING IN THE CRACKS. (TC NR 20080111005)									3	R			5E1				 
2008032000007	20080320	00007	EA  	2008	3	20	CA080112001      	1	20080110	G	2420	600591435	ADG             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  						UNWANTED DEPLOY 	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA			18107	18107							(CAN) A/C RETURNED DUE TO ADG UNCOMMANDED DEPLOYMENT ON T/O. PRESENTLY THE AUTO DEPLOYMENT SYS IS UNDER MEL UNTIL MAINT 	PERMITS. UPDATE FURTHER WHEN T/S HAS BEEN C/O. (TC NR 20080112001)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600208	20080306	00208	NM  	2008	3	6	CA080114001      	1	20080109	G	3230	483025	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	LT MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			42   								(CAN) AFTER TAKEOFF, LT MLG DOOR AMBER LIGHT REMAINED ON (FA CONFIRMED LT MLG DOOR OPEN). GEAR EXTENDED THEN L DOOR AMBE	R LIGHT, LT RED, AND GEAR HANDLE LIGHT REMAINED ON (FA CONFIRMED THE GEAR WAS PARTIALLY EXTENDED).  AFTER ABOUT 5 MINS, 	LT GREEN LIGHT ILLUMINATED AND LT MLG DOOR CLOSED. AIR RETURN TO BASE FOR LANDING.  MAINT REPLACED LT MLG SOLENOID SEQUE	NCE VALVE. (TC NR 20080114001)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008030600209	20080306	00209	EU  	2008	3	6	CA080114002      	1	20080111	G	2160	342B030000AM	SWITCH          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					TEMP CONTROL	INOPERATIVE     	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) NR 1 BLEED OVERHEAD SHOWED ON ECAM AIR ENG 1 BLD FAULT COMPLETED ECAM ACTION SHORTLY AFTERWARD AIR ENG 2 BLD FAULT	 COMPLETED ECAM. BOTH FAN AIR VALVES CHECKED IAW AMM 36-11-54-720-001 NFF. BOTH TCT`S REPLACED ( ENG 1 AND 2) IAW AMM 36	-11-43. ENG RUNS CARRIED OUT PACKS OPERATED NORMAL. (TC NR 20080114002)				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2008030600210	20080306	00210	NM  	2008	3	6	CA080114003      	1	20080110	G	2421		SENSOR          	LUCAS       	31708001A   	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2 A/C GEN	OPEN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						168					(CAN) HAD A FAILURE OF THE NR 2 AC GEN THE PREVIOUS WEEK, THE AC GEN WAS REPLACED WITH AN O/H UNIT.  THE AC TOOKOFF AND 	AT 7000 FEET HAD A NR 2 AC GENERATOR FAIL, THE AC RETURNED TO THE AIRPORT. INVESTIGATION WAS C/O AND FOUND THAT THE SPEE	D SENSOR WAS OPEN. THE UNIT SENT BACK TO THE SHOP REPLACED THE SPEED SENSOR, UNIT REINSTALLED ON THE A/C AND FOUND SERVI	CEABLE. A/C DEPARTED ON JAN 14-2008 AND NO OTHER REPORT REPORTED. (TC NR 20080114003)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008030600211	20080306	00211	NM  	2008	3	6	CA080115001      	1	20080112	G	3231	AR2674	LATCH           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NOSE LANDING GEAR ALTERNATE RELEASE DOOR FAILS TO OPEN DURING PRE FLIGHT CHECK. ALTERNATE EXTENSION DOOR LATCH BRO	KEN CAUSING DOOR TO STICK IN CLOSED POSITION. REPLACED LATCH ALL CHECKS OK. (TC NR 20080115001)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008030600212	20080306	00212	NM  	2008	3	6	CA080115002      	1	20080113	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			295  								(CAN) DURING TAXI OUT THE NR 2 HYD PUMP CAUTION LIGHT ILLUMINATED. PTU WAS SELECTED ON AT THE TIME. SHUT OFF PTU AND ALL	 NR 2 HYD SYS CAUTIONS ILLUMINATED AND CONFIRMED NO PRESSURE ON NR 2 SYS. FLUID QTY WAS LOW. RETURNED TO TERMINAL WHERE 	MAINTENANCE FOUND FLUID COMING FROM ENGINE DRIVEN PUMP DRAIN.   REMOVED EDP PUMP AND FOUND DRIVESHAFT SHEARED. PUMP REPL	ACED AND SYSTEM FLUSHED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20080115002)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008030600213	20080306	00213	EU  	2008	3	6	CA080115003      	1	20080107	G	2710	KA6D8X50	ROD END         			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12501    	59300	EU  					AT AILERON	BENT            	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			98   	98   							(CAN) WHILE RIGGING THE AILERON SYS FOLLOWING MAINT, NOTICED BOTH THE LT AND RT AILERON CONTROL ROD END FITTINGS WERE BE	NT WHERE THE CONTROL ROD IS ATTACHED TO THE BELLCRANK AT THE MOST OB POINT. NEW STRAIGHT FITTINGS WERE INSTALLED BUT THI	S CAUSED THE AILERON SYS TO BIND. THERE IS NO REFERENCE IN THE IPC OR MM REFERENCING BENT ROD ENDS AS BOTH ROD ENDS ON T	HE CONTROL ROD HAVE THE SAME PN. (TC NR 20080115003)			1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2008030600214	20080306	00214	NM  	2008	3	6	CA080115004      	1	20080112	G	3330	30180B23D1683	LIGHT           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CARGO BAY	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE CREW REPORTED (TO MOC) THAT THEY HAD THE (SMOKE) WARNING ILLUMINATED. THEY WERE TOLD TO DO A TU	RNBACK AND RETURN TO AIRPORT WHERE MAINT STAFF MET THE AIRCRAFT.  DURING THE INVESTIGATION, MAINT PERSONNEL FOUND THE SI	DEWALL BAGGAGE DOOR LIGHT WIRE HAD COME OFF INTERNALLY AND WAS ARCING ON ITS CASE. LIGHT ASSY REPLACED AND ENGINE RUNS C	ARRIED OUT. (TC NR 20080115004)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008030600215	20080306	00215	EU  	2008	3	6	CA080115005      	1	20080114	G	2710	DSPR116X058	PUSHROD         			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12502114 		EU  					AILERON	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9    								(CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, INSPECTED THE ROD ENDS ON OUR A	C.  ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE THE MOV	EMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MM. (TC NR 20080115005)				1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2008030600216	20080306	00216	EU  	2008	3	6	CA080115006      	1	20080114	G	2710	DSPR116X058	PUSHROD         			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12501    	59300	EU  					AILERON	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			37   								(CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, WE INSPECTED THE ROD ENDS ON OU	R AC. WE ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE TH	E MOVEMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MAINTENANCE MANUAL. (TC NR 2008011500	6)			1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2008030600217	20080306	00217	NM  	2008	3	6	CA080115007      	1	20080115	G	2710	129307	PCU             			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					AILERON	FROZEN          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			13147	2175 							(CAN) THE AC ARRIVED AT DESTINATION AND WAS ON A TURN-AROUND WHEN THE CREW NOTICED ON TAXI OUT, THAT THE AILERONS HAD FR	OZEN UP. THE AC RETURNED TO THE RAMP WHERE MAINT INSPECTED THE SYS. IT WAS DETERMINED THAT THE AILERON POWER CONTROL UNI	T HAD FROZEN UP.  HEAT WAS PLACED ON THE PCU AND THE CONTROLS FREED UP. THE CONTROL UNIT WAS FLUSHED OF ALL WATER CONTAM	INATES AND LUBRICATED. HEAT WAS APPLIED TO THE PCU FOR APPROX (4) HOURS. IT HAD BEEN NOTED BY FLIGHT CREW THAT THE AC HA	D BEEN IN A RAINY ENVIRONMENT EARLIER IN THE DAY. THE AC WAS COLD SOAKED FOR (4) HOURS IN -10 DEGREES AND A 50KPH WIND. 	NO FURTHER FAULTS FOUND. (TC NR 20080115007)	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2008030600218	20080306	00218	EU  	2008	3	6	CA080115008      	1	20080114	G	2710	DSPR116X058	CONTROL ROD     			DIAMON	DA42  	DA42        	2990004	EU  	THIELT	TAE125	TAE12501    	59300	EU  					AILERON	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			50   								(CAN) AFTER RECEIVING A REPORT OF AN ANOMALY WITH THE CONTROL ROD FROM ANOTHER OPERATOR, WE INSPECTED THE ROD ENDS ON OU	R AC.  ALSO FOUND THE ROD ENDS ON BOTH LT AND RT AILERONS BENT. THE ROD ENDS APPEAR TO HAVE BEEN BENT TO ACCOMODATE THE 	MOVEMENT OF THE AILERON BUT WE CANNOT FIND A DESCRIPTION OF THIS PROCESSS IN THE MM. (TC NR 20080115008)				1	L	7	2 	3I	3	B	RT	A57CE   	E00069EN				 
2008030600219	20080306	00219	EU  	2008	3	6	CA080115009      	1	20080110	G	6797		GROUND WIRE     			SNIAS 	350   	AS350B      	8680801	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					HYD SERVO	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			10932			AC67244					(CAN) IN THE PROCESS OF DOING RECURRENT TRAINING FLIGHT. AFTER SEVERAL SIMULATED HYD FAILURES IN AND OUT OF GROUD EFFECT	 HOVER, PROCEEDED TO PRACTICE THE SIMULATED HYD FAILURE. THE SIMULATED PROCEDURE WAS INITIATED FROM 100 FOOT HOVER WITH 	A VERBAL WARNING THAT WE NOW HAVE A LOSS OF HYD. AT NO TIME WAS THE HYD ACCUMULATOR TEST BUTTON USED TO SIMULATE, HYD FA	ILURE, IE. HORN AND LIGHT. FROM THE HOVER THEY ACCELERATED TO 60 KNOTS, AT WHICH TIME THE HYD ON/OFF SWITCH ON THE COLLE	CTIVE WAS SELECTED TO THE HYD OFF POSITION, AND THEY MAINTAINED 60 KNOTS THROUGHOUT THE CIRCUIT. ON DOWNWIND FOR EAST LI	MA TAXIWAY AT 500 FEET ABOVE GROUND. THE PILOT IN COMMAND WAS INFORMED TO WIDEN OUT HIS CIRCUIT SO THAT HE WOULD NOT HAV	1	G	7	1 	3U	3	U		H9EU    	E5NE				 
2008032000009	20080320	00009	EA  	2008	3	20	CA080115010      	1	20080113	G	5250		LATCH           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					LAVATORY DOOR	STUCK           	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA						3261508					(CAN) ON SHORT FINAL A PASSENGER GOT STUCK INTO LAVATORY COMPARTMENT. THE F/A TRIED TO UNLOCK THE DOOR LATCH BUT THE PAS	SENGER ELECTED TO KICK THE DOOR OFF.  IMPORTANT DAMAGES WERE DONE TO THE DOOR HINGE AND LOCKING MECHANISM. AT THIS TIME,	 INVESTIGATION COULD NOT IDENTIFY THE CAUSE OF THE INCIDENT. (TC NR 20080115010)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600221	20080306	00221	NE  	2008	3	6	CA080115012      	2	20080111	G	7240		COMBUST CHAMBER 			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					ENGINE	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2190 					22386			(CAN) DURING A 600 HR ENGINE INSPECTION, A BORESCOPE INSPECTION WAS CONDUCTED IN THE COMBUSTION CHAMBER AREA( INTERNAL) 	AN OBJECT WAS DISCOVERED HANGING OUT INTO THE FLAME PATH JUST UPSTREAM OF THE POWER TURBINE. THE OBJECT WAS PROTRUDING F	ROM AN INNER COOLING HOLE IN THE COMBUSTION CHAMBER. AFTER DISCUSSION WITH MFG, THE AC WAS REMOVED AND AN ENGINE TEARDOW	N WAS CONDUCTED. THE ITEMS REMOVED AND ENGINE REASSEMBLED AND TESTED ON THE A/C. THE OBJECT COULD NOT BE IDENTIFIED AT T	HIS LEVEL AND WAS TAKEN BY THE MFG SERVICE REP FOR TESTING. HAVE A FEW BORESCOPE IMAGES AVAILABLE IF REQUIRED. (TC NR 20	080115012)	1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20080520		CE  	2008	5	20	CA080116001      	1	20080115	G	5340	4552803060003	FITTING         		45528030040 	LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6170 	6170 							(CAN) DURING DAILY INSP A CRACK WAS NOTICED ON LT MAIN IB LANDING GEAR DOOR ACTUATOR FITTING, A NEW PART IS ORDERED AND 	WILL BE REPLACED WHEN RECEIVED. LT IB MAIN GEAR DOOR P/N 4552803004-003 FITTING IS ITEM 69 ON ATTACHED IPC. (TC NR 20080	116001)				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
	20080520		EU  	2008	5	20	CA080116002      	1	20080109	G	3230	5322012289	DRAG LINK       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	CRACKED         	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, THE INTRANSIT LIGHT CAME ON IN THE COCKPIT FOR THE NOSE GEAR. THE GEAR WAS THEN SELECTED DOWN AND 	LOCKED. THE CAPTAIN AND MAINT FELT THERE WAS MORE THEN JUST A SIMPLE INDICATION PROBLEM AND RETURNED THE AC TO THE HOME 	BASE. AS A SAFETY PRECAUTION THE PASSENGERS WERE OFFLOADED ON THE RUNWAY. THE RT DRAG LINK WAS FOUND TO BE CRACKED. THER	E WAS NO TELLTALE SIGNS THAT WOULD CAUSE THE LINK TO CRACK LIKE IT DID. FROM THE LOOK OF THE CRACK IT WAS ALL NEW. THE R	EST OF THE PC-12S IN THE FLEET WERE CHECKED AND NO OTHER DRAG LINKS WERE CRACKED. THE LINK WAS REPLACED, SWINGS WERE COM	PLETED AND THE AC WAS RETURNED TO SERVICE. (TC NR 20080116002)	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008030600224	20080306	00224	CE  	2008	3	6	CA080116007      	1	20080112	G	2820	3032791	LINE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	LT NACELLE	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL FLOW INDICATION LINE FOUND CHAFED AND LEAKING. NEW LINE INSTALLED. (TC NR 20080116007)						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008030600226	20080306	00226	CE  	2008	3	6	CA080116009      	1	20080108	G	7603	11452411411	BELLCRANK       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	POWER LEVER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RT POWER LEVER BELLCRANK LOCATED IN THE BOTTOM OF THE PEDESTAL WAS REPLACED DUE TO WEAR.  AFTER REMOVAL THE PA	RT WAS FOUND TO BE CRACKED. (TC NR 20080116009)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2008030600231	20080306	00231	NE  	2008	3	6	CA080116014      	2	20080106	G	7310		FUEL SYS        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	LOW PRESSURE    	W				D				RETURN TO BLOCK         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								77771			(CAN) DURING PRE TAKEOFF ACTIVITES, THE LOW FUEL PRESSURE WARNING ILLUMINATED. AS THE AC TAXIED BACK TO THE RAMP, THE EN	GINE SHUT ITSELF DOWN. ENGINE RESTARTS WERE UNSUCCESSFUL.  THE FUEL FLOW DIVIDER WAS REPLACED AND THE AC RETURNED TO SER	VICE. (TC NR 20080116014)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008030600232	20080306	00232	EA  	2008	3	6	CA080116015      	2	20080104	G	7250		TURBINE BLADES  			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FRACTURED       	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	HO	HOVERING       	1			CA								TH0463			(CAN) DURING HOVER THE CREW NOTED VIBRATION FOLLOWED BY CHIP DETECTOR LIGHT ILLUMINATION AND LOSS OF POWER. POST FLIGHT 	INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND ASSOCIATED DAMAGE. IT WAS REPORTED THAT THE PILOT HAD DIFFICULTY 	STARTING THE ENGINE PRIOR TO THIS FLIGHT.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTAB	LISHED (TC NR 20080116015)			1	G	7	2 	4U	4	U		H4SW    	E22EA				 
2008030600234	20080306	00234	EA  	2008	3	6	CA080116017      	1	20080115	G	3213	15101103	HOUSING         			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 6 YEAR CORROSION INSPECTION, A CRACK WAS FOUND ON THE LT MLG OUTER HOUSING. THE CRACK IS LOCATED ON THE F	WD SIDE AT ABOUT THE ONE OCLOCK POSITION JUST WERE THE HOUSING TAPERS DOWN. EDDY CURRENT WAS USED ON THE CRACK, IT WAS 	DEEPER THAN THE 0.040. THE LANDING GEAR HAS A 60 000 LANDING LIFE LIMIT AND A 10 000 LANDING INSPECTION REQUIREMENT, THI	S GEAR HAD 44 528 LANDINGS SINCE NEW AND 5925 LANDINGS SINCE INSPECTION. THE HOUSING WILL BE REPLACED.  (TC NR 200801160	17)		2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2008032400428	20080324	00428	EA  	2008	3	24	CA080116020      	2	20080109	G	7200		ENGINE          			PIPER 	PA46  	PA46350P    	7104602	SO  	PWA   	PT6   	PT6*        	52043	EA  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	M		SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 		CR	CRUISE         	1			CA								RR0005			(CAN) PILOT REPORTED ENGINE TROUBLE AND ATTEMPTED TO RETURN TO BASE. ENGINE WAS SHUTDOWN BY THE PILOT, AND AC LANDED SHO	RT OF THE RUNWAY CAUSING SUBSTANTIAL DAMAGE TO THE AIRFRAME. INITIAL INVESTIGATION INDICATES NO OBVIOUS GAS PATH OR TURB	INE BLADE DAMAGE, HOWEVER NO OIL WAS VISIBLE ON THE DIPSTICK.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF R	OOT CAUSE ONCE ESTABLISHED (TC NR 20080116020)			1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2008032400429	20080324	00429	NE  	2008	3	24	CA080116021      	2	20080109	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						POWER LOSS      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA								17458			(CAN) CLIMBING THROUGH 4000 FT, ENGINE PWR WAS LOST. ACTIVATION OF THE EMERGENCY POWER LEVER HAD NO EFFECT. THE ENG WAS 	SECURED AND THE AC WAS ABLE TO RETURN TO POINT OF DEPARTURE. INITIAL INVESTIGATION REVEALS AN EXTERNAL OIL LEAK AND A SE	IZED PROP SHAFT ROTOR. THE ENGINE HAS BEEN IMPOUNDED BY THE AUTHORITIES AND WILL BE INVESTIGATED IN THE MFG FACILITY. UP	DATES WILL BE PROVIDED IN DUE COURSE. (TC NR 20080116021)			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
2008032400431	20080324	00431		2008	3	24	CA080116022      	4	20080109	G	6122		MOUNT           			BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	GOVERNOR	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								L1832351A			(CAN) AFTER ENGINE REPLACEMENT FOR OVERHAUL A PRELIMINARY GROUND RUN WAS CARRIED OUT. IT WAS FOUND THAT THE PROPELLER WO	ULD NOT FEATHER WHEN PERFORMING A GOVERNOR CHECK. THE PROBLEM WAS TRACED TO THE GOVERNOR MOUNT PAD WHICH HAD NOT HAD AN 	OIL GALLERY COMPLETELY DRILLED PREVENTING PROPELLER CONTROL. MAINT REPLACED THE GOVERNOR PAD AND THE AC PROPELLER CONTRO	L SYS FUNCTIONED NORMALLY (TC NR 20080116022)			1	L	7	2 	3O	3	O		3A16    	1E10	5	C	P920	 
2008032400432	20080324	00432	EA  	2008	3	24	CA080116023      	2	20080111	G	8520	7106403	CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 1 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1829 				RL489461A			(CAN) DURING SCHEDULED NR 1 EVENT INSPECTION, AME FOUND LT ENGINE, NR 5 CYL DIFFERENTIAL PRESSURE TEST VERY LOW.  NR 5 C	YL REMOVED FOR DETAILED INSP AND POSSIBLE REPLACEMENT. UPON FURTHER INSP MAINT FOUND AN APPROX 4 INCH CRACK, STARTING FR	OM NR 5 CYL LOWER FWD MOUNT STUD BASE, ALONG CYL. BASE INTO RT CASE EXTENDING APPROX 3.5 INCH TOWARD NR 5 CYL COVER OIL 	DRAIN PORT IN THE CASE. LT ENGINE REPLACEMENT UNDERWAY. (TC NR 20080116023)			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2008030600236	20080306	00236	EA  	2008	3	6	CA080116024      	1	20080113	G	3260	16868101	PROXIMITY SWITCH	MESSIER     		CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					NLG	MISINSTALLED    	W				B				EMER. DESCENT           				N			FALSE WARNING             			AP	APPROACH       	1			CA						07MDT0422					(CAN) DURING APPROACH, GEAR WAS SELECTED DOWN AND NLG INDICATED AMBER. NO GEAR DISAGREE MESSAGE POSTED. GEAR WAS RAISED 	NORMALLY AND MISSED APPROACH WAS EXECUTED.  AT THAT MOMENT QRH ACTIONS WERE CARRIED OUT FOR GEAR MALFUNCTION. NOSE GEAR 	INDICATION BECAME RED. TROUBLESHOOTING WAS CARRIED OUT VIA RADIO WITH ENGINEERING NOSE GEAR WOULD NOT INDICATE DOWN. A L	OW APPROACH WAS CONDUCTED AT AIRPORT TO VISUALLY CHECK NOSE GEAR POSITION. GEAR APPEARED DOWN.  EMERGENCY DECLARED.  FOL	LOWED BY AN UNEVENTFUL LANDING.  THE AC WAS PUT IN QUARANTINE FOR TEST ON GROUND AND FINDING OF THE ROOT CAUSE.  AFTER D	EPLOYMENT TEST ON LANDING GEAR AND FUNCTIONAL TEST ON PSEU THE PROBLEM WAS DISCOVERED. THE PROBLEM WAS AN INAPPROPRIATE 	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008033100039	20080331	00039	NE  	2008	3	31	CA080117001      	2	20080110	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					LEFT	FLAMED OUT      	W				A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CA			21835					872629			(CAN) FLIGHT,IN CRUISE, LT ENGINE FLAMED OUT WITH NO PREVIOUS WARNINGS. FLIGHT CREW TRIED TO RESTART LT WITHOUT SUCCESS.	 AC LANDED. NO ENGINE EXCEEDANCES FOUND. NO EVIDENCE OF WATER CONTAMINATION IN MAIN FUEL TANKS AND FUEL FILTER HOUSING. 	 PERFORMED A VISUAL EXTERNAL AC INSP AND NO EVIDENCE OF LIGHTNING STRIKE. CHECKED ENGINE THROTTLE RIGGING, FOUND OK. CHE	CKED FEEDBACK CABLE, FOUND OK. DURING T/S THE ENGINE STARTS NORMALLY, AND ALL ENGINE PARAMETERS ARE STABLES AND NORMAL. 	POWER ASSURANCE CHECK PERFORMED AND ALL ENGINE PARAMETERS ARE WITHIN SERVICEABLE LIMITS.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600237	20080306	00237	SW  	2008	3	6	CA080117002      	1	20080117	G	6420		BEARING         	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					T/R HUB	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6085 	801  							(CAN) FOUND TAIL ROTOR HUB ASSY OB BEARING CAGE INSERT OUT OF IS SOCKET.  ASSY SEND FOR O/H. (TC NR 20080117002)						1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008030600238	20080306	00238	EU  	2008	3	6	CA080117003      	1	20080111	G	2821	571712A	BYPASS VALVE    			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) THE AC LANDED AFTER FLYING SEVERAL HOURS ON A SEISMIC JOB. WHILE DOING A QUICK DI, THE ENGINEERS NOTICED FUEL ON T	HE TRANSMISSION DECK. IT WAS DISCOVERED THAT THE FUEL FILTER BYPASS INDICATOR PLASTIC HOUSING ON THE BYPASS VALVE ASSY (	PN 57171-2A) WAS CRACKED AND WAS LEAKING FUEL ON THE TRANSMISSION DECK. IT IS NOT KNOW HOW MANY HOURS THE AC FLEW THAT D	AY WITH THIS FUEL LEAK. THE VALVE ASSY WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080117003)			1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2008032400434	20080324	00434	NM  	2008	3	24	CA080117004      	1	20080115	G	5330	143A321220	SKIN            			BOEING	737   	737800*     	       	NM  										BS 480 S21L	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11057								(CAN) UNDERGOING MAINT,  LIGHTNING STRIKE ON RIVET AT BS 480,1.3INCHES BELOW STRINGER 21, LT SIDE. REPAIRED IAW EA 5330-	02286.					2	L	7	2 	4F			RT	A16WE   					 
2008032500001	20080325	00001	WP  	2008	3	25	CA080117005      	2	20080111	G	7261	8941171	ADAPTER         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENG OIL FILTER	CRACKED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA								P54055			(CAN) DURING THE DAILY INSPECTION IT WAS NOTICED THAT THERE WAS OIL IN THE BOTTOM OF THE COWLING. FURTHER INSP REVEALED 	THAT THE (3) OF THE (4) TANGS FOR THE STUDS WHICH HOLD DOWN THE OIL FILTER ADAPTER WERE CRACKED. TOTAL TIME ON THIS PART	 IS UNDETERMINED BECAUSE IT IS ON CONDITION.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2008030600239	20080306	00239	NE  	2008	3	6	CA080117006      	1	20080116	G	7921	28E252	THERMOSTAT      			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR1 POSITION	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			HO	HOVERING       	1			CA											(CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP BEGAN TO RISE TO LIMIT. (TC NR 20080117006)						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2008032000010	20080320	00010	EA  	2008	3	20	CA080117007      	2	20080115	G	7200		ENGINE          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LEFT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			11901	4605 				PCE22135			(CAN) WHILE DOING PILOT TRAINING, THE LT OIL PRESSURE WARNING LIGHT CAME ON. PILOTS LOOKED DOWN AT OIL PRESSURE GAUGE, T	HE PRESSURE WAS DROPPING SO THEY SHUTDOWN THE ENGINE AND FEATHERED THE PROP. THEY RETURN TO BASE. ENGINE REMOVED FOR FUR	THER INSPECTION. (TC NR 20080117007)				1	L	7	2 	3T	3	T		A14CE   	E4EA	6	C	P15EA	 
2008030600240	20080306	00240	CE  	2008	3	6	CA080117008      	1	20080114	G	3230	1158200381	SPROCKET        			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSP OF THE NLG RETRACT MECHANISM CHAIN FOR TENSION AND LUBRICATION, MAINT NOTED THE DUAL LINK CHAIN WAS ON	LY RUNNING ON ONE LENGTH OF CHAIN RATHER THAN (2).  AC WAS INSPECTED MORE CLOSLEY AND THE BRAZE/SPROCKET ASSY WHICH IS I	NTERMEDIATE BETWEEN LANDING GEAR MOTOR AND RETRACT ACTUATOR FOR THE NOSE GEAR WAS FOUND MISALIGNED AND DISPLACED. UPON R	EMOVAL OF THE SPROCKET AND IT`S HOUSING IT WAS NOTED THE UNDERLYING AC STRUCTURE WAS CRACKED AND NOT PROVIDING ADEQUATE 	SUPPORT TO THE SPROCKET ASSY FOR PROPER OPERATION AND ALIGNMENT. THE LACK OF ALIGNMENT BETWEEN THE CHAIN AND SPROCKET CA	USED THE DUAL LINK CHAIN TO SKIP OVER ONE SPROCKET AND ONLY UTILIZE HALF OF THE CHAIN FOR GEAR RETRACTION AND EXTENSION.	1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
2008022000015	20080220	00015	EA  	2008	2	20	CA080117010      	1	20080116	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			13017	13017							(CAN) DURING DESCENT, CREW REPORTED A FLAP FAIL CAUTION MESSAGE WITH NO FLAP SELECTION. AN EMERGENCY WAS DECLARED AND AN	 UNEVENTFUL FLAPLESS LANDING WAS CARRIED OUT. THE AC WAS FERRIED TO MAINTENANCE BASE WERE THE LT BRAKE POSITION SENSOR U	NIT (BPSU) WAS REPLACED AND RIGGED. A SUCCESSFUL FLIGHT TEST WAS COMPLETED AND THE AC RETURNED INTO SERVICE. THE UNIT HA	S ACCUMULATED 30:20 FLIGHT HOURS SINCE REPAIR. (TC NR 20080117010)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000016	20080220	00016	EA  	2008	2	20	CA080117011      	1	20080116	G	5610	601R3303319	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			8194 	8194 							(CAN) LT COCKPIT SIDE WINDOW SHATTERED IN DESCENT.  THE CREW DID NOT REPORT ANY IMPACT OR PROBLEM WITH THE WINDOW PRIOR 	TO INCIDENT. VISUAL INSPECTION OF THE WINDOW INDICATES THAT ONLY THE OUTER PLY WAS DAMAGED. THE SIDE WINDOW WAS REPLACED	, TESTED AND THE AC RETURNED TO SERVICE. (TC NR 20080117011)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000017	20080220	00017	EA  	2008	2	20	CA080118000      	1	20080116	G	5610	NP1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF343B      	30069	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			8931 								(CAN) COPILOTS WINDSHIELD INNER PANE SHATTERED AT 37,000 FT ON DESENT.  NO EVIDENCE OF HEATER FAILURE WAS OBSERVED. (TC 	NR 20080118000)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600241	20080306	00241	SW  	2008	3	6	CA080118001      	1	20080105	G	6310	206040230019	FREEWHEEL UNIT  			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				5    							(CAN) AFTER FLIGHT THE FREEWHEEL ASSY WAS DISCOVERED LEAKING FROM THE FWD HSG CAP. FREEWHEEL ASSY CHANGED, LEAK CHECK CA	RRIED OUT SERVICEABLE. (TC NR 20080118001)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008030600242	20080306	00242	EU  	2008	3	6	CA080118002      	1	20080118	G	2571		BATTERY BOX     			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					FUSELAGE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1889 								(CAN) DURING DAILY INSPECTION FOUND (2) BROKEN HEAD OF RIVETS ON BATTERY TRAY. RIVETS REPLACED AND AIRCRAFT, SERVICEABLE	 (TC NR 20080118002)					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2008022000018	20080220	00018	EA  	2008	2	20	CA080118003      	1	20080115	G	2420	820465	ADG             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  						UNWANTED DEPLOY 	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			16687	16687							(CAN) WHILE AC  WAS IN CRUISE AT 30000 FT, ADG DEPLOYED UN-COMMANDED. ALL ELECTRICAL SYSTEMS WERE POWERED. TRIED SWITCHI	NG BACK TO IDG POWER. ADG WOULD NOT SWITCH OVER. MAINTENANCE REPLACED ADG AUTO DEPLOYMENT CONTROLLER AND ADG RESTORE PUM	P. (TC NR 20080118003)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008030600243	20080306	00243	NE  	2008	3	6	CA080119001      	2	20080118	G	7314	15473	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			797  	797  							(CAN) FUEL PUMP LEAKING OIL FROM DRAIN LINE. PUMP REMOVED AND NEW PUMP INSTALLED. DEFECT RECTIFIED. (TC NR 20080119001)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022000019	20080220	00019	EA  	2008	2	20	CA080121001      	1	20080116	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			12588	12588							(CAN) ON CLIMB OUT THROUGH 6000 FT CREW SELECTED WINDSHIELD HEAT. THE (L WSHLD HEAT) EICAS MESSAGE ILLUMINATED. ABOUT 15	 SECONDS LATER CAPTAINS FRONT WINDSHIELD OUTER PLY BEGAN CRACKING. SPIDER WEB LIKE CRACKING CONTINUED UNTIL WHOLE OUTER	 PANE APPEARED SHATTERED. CAPTAINS FRONT WINDSHIELD WAS REPLACED. AS A PRECAUTION, THE LT WINDSHIELD TEMPERATURE CONTRO	LLER PN 1659-1 WAS ALSO REPLACED. (TC NR 20080121001)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000020	20080220	00020	EA  	2008	2	20	CA080121002      	1	20080120	G	2750	5275102	FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	DEFECTIVE       	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) FLAPS FAILED ON INITIAL SELECTION FROM 0 TO 8 DEGREES JUST AFTER PUSHBACK FOR HEADSTART FLIGHT. OAT WAS -29 C OVER	NIGHT.  MAINTENANCE GOT CODES FROM FECU, CLEARED FAULT AND RESET FLAPS. FLAPS FUNCTION CHECKED SERVICEABLE, BUT DUE TO R	ECENT HISTORY IT WAS DECIDED TO FERRY THE AC FOR FURTHER TROUBLESHOOTING. TROUBLESHOOTING IS UNDER WAY AND INFORMATION W	ILL BE UPDATED AS SOON AS IS AVAILABLE. (TC NR 20080121002)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008032500002	20080325	00002		2008	3	25	CA080121003      	4	20080102	G	3497		WIRE            			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					TAWS COMPUTER	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) TAIL 523 ON JAN 2ND APPROACH BACK COURSE ON RWY 15 YELLOWKNIFE 1040FT ASL 350FT AGL LEVEL FLIGHT 140K  IN THIS CAS	E THE FLIGHT CREW EXPERIENCED A TAWS GENERATED A PICTORIAL DISPLAYED IMPACT WARNING. THE CREW WAS IN VISUAL CONDITIONS A	ND SAW NO DANGER OF IMPACT. THE AC LANDING WITHOUT FURTHER INCIDENT. IN THE FOLLOWING WEEKS, AC EQUIPPED WITH THE UNIVER	SAL TAWS COMPUTER (STC ST10622SC) EXPERIENCED SIMILAR ANOMALIES.  UNIVERSAL AVIONICS WAS CONTACTED CONCERNING THE ISSUE.	 THIS NORTH REGION AIRPORT DATA BASE WAS ALREADY UNDER REVIEW DUE TO OTHER OPERATOR COMPLAINTS. A NEW DATA BASE WAS RELE	ASED AND FORWARDED. ATTEMPTS TO LOAD THE NEW DATA BASE INTO THE TAWS UNITS FAILED DUE TO A COMMUNICATION PROBLEM BETWEEN	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2008022000021	20080220	00021	EU  	2008	2	20	CA080121004      	1	20080118	G	7820	L24266710000	BAFFLE          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INTERNAL BAFFLE ATTACH WELD WAS FOUND CRACKED DURING A 100 HOUR INSPECTION. (TC NR 20080121004)						1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2008022000022	20080220	00022	EU  	2008	2	20	CA080121005      	1	20080118	G	6230	350A37000402	GUIDE           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					SWASHPLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			602  								(CAN) DURING A SCHEDULED 100 HOUR INSPECTION THE COLLECTIVE LEVER WAS RAISED TO EXAMINE THE SWASHPLATE GUIDE.  IT WAS DI	SCOVERED THAT THE SELF ADHESIVE TAPE APPLIED TO THE GUIDE WAS BUNCHED UP BETWEEN THE ROTATING SWASHPLATE AND THE SWASHPL	ATE GUIDE.  THE ROTATING SWASHPLATE CONTACTED THE SWASHPLATE GUIDE LEAVING LIGHT WEAR MARKS AROUND THE CIRCUMFERENCE.  T	HE SWASHPLATE GUIDE WAS REPLACED AND WILL BE SENT TO THE MFG FOR EVALUATION AND SERVICEABILITY CHECK. (TC NR 20080121005	)		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2008022000023	20080220	00023	NM  	2008	2	20	CA080121007      	1	20080116	G	2436		VOLT REGULATOR  			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  						ODOR            	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT CREW SHUTDOWN CHECKLIST, ON APU POWER, SMOKE ALARM SOUNDED IN THE AC LAVATORY.  LAVATORY INSP REVEAL	ED SOME SMOKE.  ALARM SILENCED WHILE INSPECTING THE LAVATORY AREA.  AFTER APPROXIMATELY 30 SECONDS, THE ALARM SOUNDED AG	AIN, AND THE AC POWERED DOWN.  MAINT  INSPECTED THE LWR E/E COMPARTMENT AND FOUND SUBSTANTIAL AMOUNT OF SMOKE WITH AN EL	ECTRICAL BURNING ODOR. FIRE DEPARTMENT WAS CALLED BY THE FLIGHT CREW.  MAINT DISCONNECTED THE MAIN AC BATTERY AND DISCON	NECTED THE BATTERY CHARGER. NO OBVIOUS FAULTS WERE NOTED WITH THE BATTERY OR CHARGER AND BOTH UNITS DID NOT APPEAR TO BE	 OVERHEATED. THE AC WAS THEN REPOWERED USING ONLY EXTERNAL POWER WITH NO FURTHER SMOKE EVIDENT. INSP OF ALL ELECTRICAL R	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2008022000024	20080220	00024	WP  	2008	2	20	CA080121008      	1	20080109	G	6310	369D25351DSN	SPRAG CLUTCH    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			958  								(CAN) DURING 300 HOUR INSPECTION PART WAS FOUND TO HAVE PITTING ON SEVERAL ELEMENTS.  SPRAG CLUTCH REPLACED. (TC NR 2008	0121008)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2008022000027	20080220	00027	SO  	2008	2	20	CA080121009      	1	20080108	G	2421	ALU8421R	ALTERNATOR      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  		INOPERATIVE     	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				278  							(CAN) IN CRUISE, AC STARTED TO LOOSE ELECTRICAL POWER. FIRST INDICATION, THE TRANSPONDER FAILED. AC THEN RETURNED TO AIR	PORT. BOTH LT AND RT ALTERNATOR FAIL INDICATOR LIGHTS REMAINED OUT DURING THE FLIGHT. UPON INSP NEITHER ALTERNATOR WAS C	HARGING THE SYS. THE ONLY POWER SUPPLY WAS THE AC BATTERY. THE LT ALTERNATOR WAS FOUND TO BE UNSERVICEABLE. THE RT ALTER	NATOR, BECAUSE OF THE ADDED ELECTRICAL LOAD PUT ON IT, CAUSED THE ALTERNATOR BELT TO SLIP ON THE PULLEY, MAKING THE ALTE	RNATOR INOPERATIVE. ALL AC RADIOS, NECESSARY LIGHTS AND DEICING HEAT WAS ON AT THIS TIME. (TC NR 20080121009)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P52GL	 
2008022000028	20080220	00028	EA  	2008	2	20	CA080121011      	2	20080104	G	7414	BL600646201	MAGNETO         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					RT MAGNETO	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				890  							(CAN) DURING MAGNETO CHECK PRIOR TO FLIGHT, THE RT MAGNETO FAILED. MAGNETO REPLACED AND CHECKED SERVICEABLE. (TC NR 2008	0121011)					1	G	7	1 	3O	3	O		H11NM   	E295				 
2008022000029	20080220	00029	NE  	2008	2	20	CA080122001      	2	20080108	G	7414	BL600646201	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					RT	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				767  							(CAN) RT MAGNETO FOUND UNSERVICEABLE ON PREFLIGHT. MAGNETO CHANGED, GROUND RUN AND LEAK CHECK CARRIED OUT SERVICEABLE. (	TC NR 20080122001)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
2008022000030	20080220	00030	NM  	2008	2	20	CA080122002      	1	20080105	G	5320		WEB             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2452 							(CAN) DURING MAINT ROUTINE INSP, THE NOSE LANDING GEAR GROUND LOCK MECHANISM WAS FOUND HARD TO OPERATE. FURTHER INVESTIG	ATION REVEALED THAT THE FLOOR WEB AT ZONE 112, STA X97 WAS CRACKED CAUSING THE GROUND LOCK LEVER TO CONTACT THE PIVOT TU	BE ARM. THE CRACKED AREA WAS REPAIRED IN AUGUST 2006 IAW RD8-53-0638. THE AC HAS ACCUMULATED 2451:46 HOURS AND 3379 CYCL	ES SINCE REPAIRED. THE OLD PATCH WAS REPLACED IAW THE ABOVE RD AND THE AC WAS RELEASED INTO SERVICE. (TC NR 20080122002)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081104		CE  	2008	11	4	CA080122003      	1	20080121	G	5350		STRUCTURE       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	TAIL CONE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16225								(CAN) WHILE INSPECTING SOME ITEMS, MFG CONTINUED AIRWORTHINESS PROGRAM IT WAS NOTICED THAT 2 CRACKS CAME FROM THE RUDDER	 CABLE HOLES AND ANOTHER CRACK CAME FROM THE NUTPLATE UNDER THE DOUBLER. CONTINUED AIRWORTHINESS INSP 53-40-04 COVERS TH	IS INSPECTION BUT IS N/A BY S/N ON OUR ACFT. A NEW BULKHEAD IS ORDERED AND WILL BE CHANGED BEFORE NEXT FLIGHT. (TC NR 20	080122003)			1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2008022000031	20080220	00031	SO  	2008	2	20	CA080122005      	1	20080111	G	3213	753227	YOKE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3004 				273354				(CAN) DURING ANNUAL INSP, A CRACK WAS FOUND ON THE OB SIDE OF THE LT MAIN LANDING GEAR YOKE.  THE CRACK WAS ALONG THE ED	GE OF THE CASTING MARK AT THE TOP WHERE THE OLEO SHAFT IS ATTACHED TO THE YOKE. THE CRACK WAS FOUND BY VISUAL INSPECTION	. (TC NR 20080122005)				1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2008022000032	20080220	00032	GL  	2008	2	20	CA080122007      	3	20080122	G	6110	3GFR34C703	PROPELLER       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  		LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			202  								(CAN) AFTER START UP AND REPOSITION OF AC FOR FUEL, A HYD LEAK WAS NOTED FROM THE PROPELLER, RUNNING FROM THE BLADE ROOT	 TO THE BLADE TIP. THE PROPELLER WAS REMOVED AND ROUTED TO A OVERHAUL SHOP FOR REPAIR. (TC NR 20080122007)					1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2008022000033	20080220	00033	NE  	2008	2	20	CA080122008      	2	20080118	G	8550		LINE            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN1     	52008	NE  	HARTZL	HCB3R	HCB3R302    	GL  	OIL SYSTEM	OBSTRUCTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN ENG WAS REMOVED FOR O/H, IT WAS DISCOVERED THAT IN THE OIL DELIVERY LINE THERE WAS PLASTIC DEBRIS FROM THE CO	NTAINERS USED TO REPLENISH THE ENGINE OIL.  THERE WAS POOR MAINTENANCE PRACTICE WHEN OPENING THESE CONTAINERS TO POUR TH	E OIL IN THE TANK IN THE AC, THE CAPS WERE NOT FULLY REMOVED FROM THE CONTAINERS. THERE WERE NUMEROUS ITEMS IN THE OIL S	YS AND THIS HAS THE POTENTIAL TO RESTRICT THE FLOW OF THE OIL RESULTING IN SHUTDOWN OF THE ENGINE.  CARE MUST BE TAKEN W	HEN CARRYING OUT THIS TASK AND THIS NEEDS TO BE COMMUNICATED TO ANYONE WHO IS SERVICING THESE AC. (TC NR 20080122008)		1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
2008022000034	20080220	00034		2008	2	20	CA080122009      	4	20080120	G	3457	10706	ANTENNA         			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	GPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GPS ANTENNA WAS REPLACED DUE TO NO SIGNAL TO UNS-1K FMS. UPON REMOVING ANTENNA FROM FUSELAGE (UPPER COCKPIT ROOF),	 FOUND HEAVY CORROSION ON ANTENNA AND SOME CORROSION ON FUSELAGE SKIN. A QUICK REVIEW OF THE RECORDS SHOWS THAT THIS ANT	ENNA WAS LIKELY INSTALLED AT THE FACTORY (2001) THERE WAS NO SEALANT UNDER THE ANTENNA AND NO GASKET MATERIAL EITHER. TH	ERE WAS SOME SEALANT AROUND THE EDGE. THE CO-AX CONNECTER WAS ALSO CORRODED. REPLACED ANTENNA, CLEANED, ETCHED, ALODINED	 AND PRIMED THE SKIN AND RETURNED A/C TO SERVICE. (TC NR 20080122009)		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2008022000036	20080220	00036	SW  	2008	2	20	CA080122010      	1	20080111	G	6230	206010447109	BEARING         			BELL  	206   	206L4       	1182110	SW  										SWASHPLATE ASSY	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19193	275  		EAJG11437					(CAN) DURING A PHASE INSP, MECHANIC FOUND A CHAFED AREA ON TOP OF THE COLLECTIVE LEVER BEARING EAR P/N 206-010-447-109. 	 FURTHER INSP REVEALED CHAFING AT BOTTOM OF BOTH SWASHPLATE ROTATING RING BEARING EARS. CHAFED AREAS APPROX 0.020-0.040 	INCH DEPTH. MECHANIC POSITIONED THE COLLECTIVE STICK FULL DOWN AND CYCLIC FULL FWD WHILE CAUTIOUSLY LINING UP EACH ROTAT	ING RING WITH THE COLLECTIVE LEVEL FOR A CLEARANCE CHECK. BOTH WERE CONTACTING. REPLACED SWASHPLATE, DRIVE LINK AND M/R 	PITCH CHANGE LINK ASSY`S. COLLECTIVE AN CYCLIC CONTROLS WERE RE-RIGGED. (TC NR 20080122010)		1	G	7	1 	3U			NC	H2SW    					 
2008022000039	20080220	00039	SO  	2008	2	20	CA080123001      	2	20080119	G	8530		CYLINDER        			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	NR 4	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				721  				684508A			(CAN) WHILE CARRYING OUT MAINT, CYLINDER NR 4 WAS FOUND LOW ON COMPRESSION 45/80.  AIR WAS LEAKING THROUGH THE EXHAUST. 	(TC NR 20080123001)					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
2008022000040	20080220	00040	SW  	2008	2	20	CA080123002      	1	20080122	G	3220	99353	COLLAR          			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) UNSAFE NOSE GEAR, CIRCLING AT AIRPORT,  DECIDED TO FLY AC TO ANOTHER AIRPORT. AC CAME BY SLOW WITH GEAR DOWN. NOSE	 LOOKED DOWN HOWEVER NOSE WHEEL WAS COCKED TO THE RT. PILOT CIRCLED TO THE WEST UNTIL EMERG EQUIPMENT WAS IN PLACE. THEN	 LANDED RUNWAY 29. HELD THE NOSE OFF AS LONG AS HE COULD THEN LET IT DOWN. NOSE GEAR COLLAPSED. 4 PEOPLE ON THE TAIL WE 	PULLED THE NOSE GEAR DOWN, THEN TOWED AC TO OUR HANGAR.   IT WAS NOTED THAT THEIR WAS A CROSSWIND WHEN THE AC DEPARTED  	MINOR DAMAGE TO NOSE DOORS. MAINT IS LOOKING INTO THE PROBLEM. MAINT FOUND EXCESSIVE WEAR IN NOSE GEAR TRUNNION SLOT (PN	 9935-1) AND DAMPING COLLAR (PN 9935-1, -3). EXCESSIVE WEAR CAUSED BINDING AND PREVENTED NOSE WHEEL FROM CENTERING WHEN 	1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA	 
	20081229		CE  	2008	12	29	CA080123003      	1	20080123	G	3245	0923150	TUBE            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	NLG TIRE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			51   								(CAN) THE FLAT WAS DISCOVERED UPON LANDING AND THE A/C WAS SHUTDOWN BECAUSE IT WAS UNABLE TO TAXI. THE FENDER AND THE WH	EEL WERE REPLACED. UPON INSP OF THE FLAT TIRE IT WAS DISCOVERED THAT THE INNER TUBE WAS SPLIT ALONG THE SEAM, THERE WAS 	NO ISSUES OR HOLES IN THE TIRE AND THE ASSY WAS ASSEMBLED CORRECTLY.				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
2008022000043	20080220	00043	SW  	2008	2	20	CA080123007      	1	20080115	G	2810	71494R	FUEL TANK       			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	OUTBOARD	CRACKED         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA			2686 								(CAN) GAS FUMES WERE DETECTED AROUND AC.  WHEN RT OB FUEL TANK WAS REMOVED A CRACK WAS FOUND ON A REPAIRED RADIUS OF THE	 LATERAL RE-ENFORCEMENT INDENT OF THE TANK.  720 HOURS SINCE THE TANK WAS REPAIRED. (TC NR 20080123007)					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2008022000044	20080220	00044	SW  	2008	2	20	CA080123008      	1	20080115	G	2810	71493R	FUEL TANK       			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	INBOARD	CRACKED         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA			2686 								(CAN) GAS FUMES WERE DETECTED AROUND AC.  WHEN THE RT IB FUEL TANK WAS REMOVED A CRACK WAS FOUND AROUND THE FUEL VENT IN	TERCONNECT WELD. (TC NR 20080123008)					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
2008022000056	20080220	00056	NM  	2008	2	20	CA080124001      	1	20080123	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 WOW	FAULTY          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) GEAR WOULD NOT RETRACT AFTER TAKEOFF, RETURN TO FIELD. CREW ELECTED TO RETURN BASE. MAINTENANCE FOUND THE NLG NR 2	 WOW HARNESS TO BE AT FAULT.  NEW HARNESS INSTALLED, AIRCRAFT RETURNED TO SERVICE. (TC NR 20080124001)					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2008022000057	20080220	00057	NM  	2008	2	20	CA080124002      	1	20080124	G	2910		SWIVEL          			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 6 SLAT	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			8455 	709  							(CAN) AC WAS DISPATCHED AND DURING CRUISE FLIGHT, THE FLIGHT ENGINEER NOTICED THAT THE (A) SYS HYDRAULICS INDICATED .125	0 OF A TANK REMAINING. THE CREW DECIDED TO DECLARE AN EMERGENCY AND THE LANDING GEAR NEEDED TO BE CRANKED DOWN. THE AC L	ANDED SAFELY AND WAS TOWED OFF THE RUNWAY TO THE RAMP.  MAINT TROUBLESHOT THE SNAG AND FOUND THAT THE NR 6 LEADING EDGE 	SLAT WAS LEAKING HYD FLUID FROM A LEAK IN THE SWIVAL ASSY OF THE SLAT. THE ACTUATOR WAS REMOVED AND REPLACED AND THE HYD	 SYS WAS REPLENISHED. THE AC WAS FUNCTION TESTED SERVICEABLE AND RETURNED TO SERVICE. (TC NR 20080124002)		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2008022000059	20080220	00059	SW  	2008	2	20	CA080124003      	1	20080117	G	3210	D212664201	CROSSTUBE       			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					LG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2236 				30294				(CAN) WHILE THE ENGINEER WAS CONDUCTING THE DI, A CRACK IN THE AFT DART CROSSTUBE WAS DISCOVERED. THE DART CROSSTUBE FOL	LOWS 300/600 HR INSP CYCLE. CROSSTUBE WAS 60.7 FROM 300 HR INSP, AND 360.7 FROM THE 600 HR. CROSSTUBE WAS CHECKED FOR EX	CESSIVE DEFLECTION, TOTAL SPREAD WAS 107 INCHES AND SYMMETRICAL TO THE MIDPOINT OF THE CROSSTUBE. THESE MEASUREMENTS ARE	 ACCEPTABLE WITH THE ICA-D212-664 MANUAL. THE CRACK WAS ON THE LOWER PART OF THE UPPER PORTION OF TUBE AND 4.5 INCHES FR	OM MIDPOINT. AT THE TIME OF DISCOVERY THE HELICOPTER WAS BEING USED FOR HELI-SKIING. NO HARD LANDING HAD OCCURED DURING 	ITS INSTALLATION LIFE. MEMOS TO INSPECT THE OTHER AC LANDING GEAR HAS BEEN SENT TO THE ENGINEERS. (TC NR 20080124003)	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
2008022000060	20080220	00060	WP  	2008	2	20	CA080124005      	2	20080122	G	7260	8937373	NUT             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	GEAR SHAFT	BACKED OUT      	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA				2034 							(CAN) A/C CAME IN TO THE MAINT HANGER DUE TO HAVING A CHIP LIGHT COME ON IN THE COCKPIT. INSP FROM MAINT NOTICED THAT TH	ERE WAS METAL ON THE CHIP DETECTOR OF ENGINE P-54121. AT THAT TIME THE ENGINE WAS FORWARDED TO THE ENGINE SHOP FOR FURTH	ER INSP. THE ENGINE WAS DISMANTLED TO FIND THAT THE HIGH SPEED PINION NUT (HSP) PN 893737-3, WAS STARTING TO BACK OFF FR	OM ITS OVERHAULED TORQUE SPECIFICATIONS.  THE HSP WAS OVERHAULED ON THE 22 JULY 05. THE NUT WHEN TORQUED IS SUPPOSED TO 	HAVE A PIN PN S815N4-0-200 STAKED BESIDE THE NUT TO PREVENT IT FROM BACKING OFF. UPON FURTHER INSPECTION OF THE PIN AREA	 IT DOES NOT LOOK LIKE THERE WAS EVER A PIN INSTALLED AT THE TIME OF INSP, WITH THE NUT BACKING OFF OF THE HSP THIS COUL	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081104		SW  	2008	11	4	CA080124006      	1	20080123	G	7921	8945682	LINE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	OIL COOLER	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) LINE FOUND LEAKING BETWEEN OIL COOLER TO FUEL HEATER. THE CHAF WAS FOUND BY THE STEEL IDENTIFIER ON THE LINE. LINE	 WAS REPLACED AND AREA WAS CORRECTED SO THAT THE NEW LINE WOULD CHAF IN THE FUTURE (TC NR  20080124006)					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081104		SW  	2008	11	4	CA080124007      	1	20080123	G	7921	8945682	LINE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	OIL COOLER	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) LINE FOUND LEAKING BETWEEN OIL COOLER TO FUEL HEATER. THE CHAFE WAS FOUND BY THE STEEL IDENTIFIER ON THE LINE. LIN	E WAS REPLACED AND AREA WAS CORRECTED SO THAT THE NEW LINE WOULD NOT CHAFE IN THE FUTURE. (TC NR 20080124007)					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081104		WP  	2008	11	4	CA080124008      	2	20080121	G	7313	310323259	FUEL NOZZLE     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED FUEL NOZZLE CHANGE A NOZZLE WAS FOUND TO BE CRACKED IN THE AREA, SECONDARY MANIFOLD FITTING THAT 	MFG SAYS TO INSPECT. (TC NR 20080124008)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081104		WP  	2008	11	4	CA080124009      	2	20080120	G	7310	310323259	FUEL NOZZLE     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  		CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL NOZZLE FOUND CRACKED ON SECONDARY MANIFOLD DURING SCHEDULED NOZZLE CHANGE IN THE AREA THAT MFG SAYS TO INSPEC	T FOR CRACKS.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2008022000061	20080220	00061	EA  	2008	2	20	CA080124011      	1	20080124	G	5330		SKIN PANEL      			DHAV  	DHC7  	DHC7102     	2802708	EA  										FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							068				(CAN) WHILE CONDUCTING A CORROSION INSP ON AC, VENEZUELAN REGISTRATION YV1000, IAW THE CUSTOMERS EQUALIZED MAINT PROGRAM	. NUMEROUS AREAS OF CORROSION WERE DETECTED THROUGHOUT THE AC.  A THRESHOLD AND REPETITIVE CORROSION INSP PROGRAM IS MAN	DATED BY ADCF-98-03 AND IS TO BE CARRIED OUT IAW THE AC CORROSION PREVENTION AND CONTROL MANUAL (PSM 1-7-5). NO INFORMAT	ION IS AVAILABLE TO KNOW IF THE THRESHOLD OR REPEAT CORROSION INSPECTIONS WERE COMPLIED WITH.  WHILE CONDUCTING THE 3-YE	AR REPETITIVE DISBOND INSP REQUIRED BY ADCF-94-15 IAW MFG SB 7-51-1 AND THE NDT MANUAL (PSM 1-7-7A) PART 5, SEVERAL AREA	S OF DISBOND WERE FOUND ON THE FUSELAGE SKIN PANELS, HORIZONTAL STABILIZER SKIN PANELS AND WING PANELS. IN ADDITION, ARE	2	H	7	4 	4T				A20EA   					 
2008022000064	20080220	00064	SO  	2008	2	20	CA080124013      	2	20080109	G	8530	636242	GUIDE           	CONT        							CONT  	O550  	IO550D      	17042	SO  					EXHAUST	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			296  								(CAN) 5 CYLINDER ASSYS RECEIVED FOR REPAIR DUE TO LOW COMPRESSION. ABNORMALLY HIGH WEAR WAS FOUND INSIDE THE EXHAUST GUI	DES. WEAR PATTERNS ON THE EXHAUST VALVES AND SEATS INDICATED THAT THEY WERE NOT PROPERLY ALIGNED CAUSING THE VALVE STEMS	 TO WEAR AGAINST THE GUIDES. (TC NR 20080124013)									3	O			E3SO				 
2008022000065	20080220	00065	SO  	2008	2	20	CA080124014      	2	20080111	G	8530	628309	GUIDE           	CONT        	655483A11   						CONT  	O200  	O200A       	17020	SO  					CYLINDER	UNDERSIZE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			188  								(CAN) EXHAUST VALVE GUIDES FOUND TO BE 0.002 INCH SMALLER THAN THEY SHOULD BE AFTER 2 CYLINDERS WERE SENT IN FOR REPAIR 	DUE TO STUCK EXHAUST VALVES. (TC NR 20080124014)										3	O			E252				 
	20081219		CE  	2008	12	19	CA080124015      	1	20080123	G	5753	55250007983	BEARING         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAP	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACFT ARRIVED AT OUR FACILITY FOR PAINT.  UPON DISASSEMBLY MX NOTED THE BOLT SECURING THE RT FLAP CENTRE AFT ROLLER	 WAS LOOSE.  FURTHER INVESTIGATION AND REMOVAL DETERMINED THAT THE BEARING AND SHIM REQUIRED TO BE UNDER THE HEAD OF BOL	T WAS MISSING AND PROBABLY NOT INSTALLED THE LAST TIME MX WAS DONE IN THAT AREA.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008022000066	20080220	00066	SO  	2008	2	20	CA080124016      	2	20080123	G	8530	636242	GUIDE           	CONT        	655471A4    						CONT  	O550  	IO550D      	17042	SO  					CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			803  								(CAN) RECEIVED CYLINDER FOR REPAIR DUE TO LOW COMPRESSION. WHEN RESURFACING THE VALVE SEATS IT WAS NOTED THAT THE INTAKE	 GUIDE AND SEAT DID NOT PROPERLY LINE UP. THIS COULD HAVE CAUSED THE LEAK THAT RESULTED IN LOW COMPRESSION. (TC NR 20080	124016)									3	O			E3SO				 
2008022000067	20080220	00067	CE  	2008	2	20	CA080125001      	1	20080122	G	7931		OIL SYSTEM      			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					PRESSURE	UNKNOWN         	W				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			576  								(CAN) APPROXIMATELY 5 -7 MINUTES AFTER TAKEOFF, THE WARNING LIGHT (LOW OIL PRESS R ) WAS OBSERVED ON THE M.A.P. AND (0) 	ON THE OIL PRESSURE INDICATOR TAPE . A PRECAUTIONARY ENGINE SHUTDOWN WAS PERFORMED FOLLOWED BY THE DECLARATION OF AN EME	RGENCY. ENG IS STILL UNDER INVESTIGATION TO DETERMINE THE CAUSE. (TC NR 20080125001)				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2008022000068	20080220	00068	EA  	2008	2	20	CA080125002      	1	20080122	G	2752		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					FLAP	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON FINAL AFTER SELECTING FLAP TO 8 DEGREES. AN EMERGENCY WAS DECLARE	D AND THE AC CONDUCTED A FLAPLESS LANDING WITHOUT FURTHER INCIDENT. THE AC WAS FERRIED. ALL FLAP ACTUATORS WERE REPLACED	 AND THE AC WAS RELEASED. A SUCCESSFUL TEST FLIGHT WAS CONDUCTED AND THE AC RETURNED INTO SERVICE. ALL FLAP ACTUATORS WE	RE SENT TO THE SHOP FOR LOW TEMPERATURE TORQUE CHECK. RT NR 4 FLAP ACTUATOR P/N 854D100-20 S/N OFF 1911, TSN 8231 TSR 29	46 CSN 6684 CSR 2558 RT NR 3 FLAP ACTUATOR PN 853D100-20 S/N OFF 2604, TSN 8231 TSR 2946 CSN 6684 CSR 2558 RT NR 2 FLAP 	ACTUATOR P/N 852D100-19 S/N OFF 5996 TSN 2946 TSR 2946 CSN 2558 CSR 2558 RT NR 1 FLAP ACTUATOR PN 852D100-19 SN OFF 5948	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000069	20080220	00069	EA  	2008	2	20	CA080126001      	1	20080118	G	5610	NP13932113	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					LT/ CAPTAIN	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			14906								(CAN) (CAPTAINS WINDSHIELD SHATTERED IN FLIGHT. PRESSURIZATION STAYED NORMAL AND THE AC CONTINUED.  MAINT IS GOING TO CH	ANGE THE WINDSHIELD). REPLACED THE WINDOW  WINDSHIELD, MAIN PILOT, NP-139321-13 01355H5650 TSO: 14906.50 CSO: 12838 (TC 	NR 20080126001)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000070	20080220	00070	EA  	2008	2	20	CA080126002      	1	20080117	G	7603	1603730003	THROTTLE CONTROL			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					LT ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) CREW REPORTED LT ENG REMAINED AT HIGH POWER SETTING WHEN AC BROUGHT TO IDLE. N1 REMAINED BETWEEN 82 AND 91 PERCENT	.  IFSD PILOT COMMANDED IN FLIGHT SHUTDOWN: CONFIRMED, AFTER (ABORTED APPROACH) PILOT SHUTDOWN THE LT ENG USING FIRE PUS	H DURING (GO AROUND). LANDED ON ONE (RT) ENGINE.  NOT POSSIBLE TO LAND THE A/C WITH (LT) AT 82 TO 90 PERCENT N1 FWD THRU	ST, NO ABILITY TO RETARD LT THRUST LEVER TO REDUCE THRUST AND EFFECT FUEL SHUTOFF.   CONTROL ASSY, THROTTLE PUSHPULL (LT	) P/N: 1603730 AND NR 8722, 003 S/N: UKN (TC NR 20080126002)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000072	20080220	00072	EA  	2008	2	20	CA080126003      	1	20080116	G	5610	601R3303320	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5     	30050	NE  					COCKPIT	CRACKED         	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			O			OTHER                     			CR	CRUISE         	1			CA			9573 								(CAN) AC DIVERTED, FOS SIDE WINDOW CRACKED IN FLT, CREW DECLARED EMRG NO PRESS ISSUES. NOTED CREW USED MASKS. MASKS NOT 	DROPPED IN CABIN.  SIDE WINDOW P/N:601R33033-20, S/N: 04023H4068: CO-PILOT SIDE WINDOW 9573 HRS / 6860 CYCLES (TC NR 200	80126003)				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
2008022000073	20080220	00073	EA  	2008	2	20	CA080126004      	1	20080124	G	5210	NAS76A16011	BUSHING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					PAX DOOR	MIGRATED        	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			24960								(CAN) CREW REPORTED THAT AT 12000 FT PAX DOOR WARNING MSG POSTED. FOLLOWED QRH AND RETURNED TO FIELD.  FOUND BUSHING IN 	FWD LATCH CAM FITTING MIGRATED. REINSTALLED BUSHING IN UPPER FWD CAM LEVER REF AMM 52-11-23.  NOTE: AC WAS PRE SB 601R-5	2-110 CONFIGURATION.  MECHANISM GA, PASS DOOR LATCH MFG 601R31903,  BUSHING: P/N: NAS76A16-011 MIGRATED 24960:41 TSN / 2	2803 CSN (TC NR 20080126004)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008022000074	20080220	00074	EU  	2008	2	20	CA080128001      	1	20080121	G	2710	19004212401	CONTROL CABLE   			EMB   	ERJ190	ERJ190100IGW	3260408	EU  	GE    	CF34  	CF3410E5A1  	30022	NE  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AILERON CONTROL CABLES INSP, ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401 AND PN 190-04209	-401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WING	S RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 SNAGS NO 128, 165 AND J/C 27-11-00-0	03-RT/2 SNAGS NR 87, 166.  THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED O	N THE FAIRLEAD. SAME FINDING ON ERJ190 NR 00015 HRS5830 CYCLES 2643, C02 CHECK AND ALSO ERJ190 NR 00013 HRS5720 CYCLES 2	635 C02 CHECK.  (TC NR 20080128001)	2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
2008022000075	20080220	00075	EA  	2008	2	20	CA080128002      	1	20080127	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN EXERCISING FLAPS DURING MAINTENANCE COLD WEATHER CHECKS, FLAP FAIL MESSAGE SHOWED AS SOON AS FLAPS SELECTED. 	 A/C FERRIED, MFG FSR CALLED TO ATTEND HANGAR FOR TEARDOWN AND INSPECTION.  MORE TO FOLLOW. (TC NR 20080128002)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080520		SW  	2008	5	20	CA080128004      	1	20080128	G	2720		CONTROL CABLE   			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	RUDDER	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			499  								(CAN) DURING INSP, THE LT RUDDER CABLE WAS FOUND SNAGGED ON THE WATER RUDDER CABLE PULLEY GUARD.  (TC NR 20080128004)						1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2008022000078	20080220	00078	SW  	2008	2	20	CA080128007      	1	20080118	G	6730	206076062	SERVO           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	NOISY           	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			6987 								(CAN) WORN LINKAGE AND PILOT VALVE CAUSED SERVO TO MAKE LOUD GROWLING NOISE. THIS WAS AN INTERMITTENT PROBLEM THAT COULD	 BE INDUCED BY CERTAIN CONTOL INPUTS. THE SOUND WAS FINALLY DETERMINED TO BE COMING FROM THE RT SERVO AND IT WAS REPLACE	D. THERE WERE NO CONTROL PROBLEMS ENCOUNTERED AND THE SERVO HAS SINCE BEEN OVERHAULED. (TC NR 20080128007)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2008022000079	20080220	00079	SW  	2008	2	20	CA080129003      	1	20080116	G	7921	MS172244	NUT             			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					OIL COOLER BLOW	UNDERTORQUED    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1650 	1650 							(CAN) DURING 100 HR, LUBRICATION OF T/R HANGER BEARINGS, IT WAS NOTED THAT THE AFT HEAT SHIELD WAS FREE TO ROTATE, UP ON	 FURTHER INSPECTION IT WAS FOUND THAT THE AFT SPANNER NUT WAS LOOSE, BUT THE LOCK WASHER WAS STILL IN THE LOCK POSITION.	 RECORDS SHOW THAT THIS PART WAS NEVER TAKEN APART OR WORK ON SINCE THE AC LEFT THE FACTORY. (TC NR 20080129003)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2008022000080	20080220	00080	WP  	2008	2	20	CA080129005      	1	20080128	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			1620 								(CAN) DURING OVER HAUL, THE CAGE OF THE SPRAG CLUTCH WAS FOUND CRACKED IN 8 PLACES. (TC NR 20080129005)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080520		EA  	2008	5	20	CA080130001      	1	20080128	G	3246	AN620A	BOLT            	AIRCRFTPRDTS		DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLOAT ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, THE TIE ROD TO FUSELAGE LUG WAS FOUND TO HAVE ONE OF THE (2) ATTACH BOLTS BROKEN. THE BREAK OCC	URRED IN THE THREADED AREA OF THE BOLT. BOTH BOLTS WERE REPLACED AND THE AC WAS RETURNED TO SERVICE. THIS AC IS OPERATED	 IN A GENERALLY ROUGH WATER ENVIRONMENT, WITH SWELLS, LARGE WAVES AND LARGE BOAT WAKES MAKING THE LANDING AREA CHALLENGI	NG AT TIMES. (TC NR 20080130001)			1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008022000081	20080220	00081	EU  	2008	2	20	CA080130002      	1	20080115	G	3212	29022979	HEAD            	AIRCRUISERS 		BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					EMERGENCY FLOAT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION THE EMERGENCY FLOAT SYS WERE DEPLOYED ACCIDENTALLY. (2) REFURBISHED KITS (PN:28022969) WERE O	RDERED. BOTH VALVE ASSY (PN: 105-E-0031) WERE REBUILDED INCLUDING SHEARHEAD ASSY. (PN:29022979) NITROGEN PRESSURE WAS BR	OUGHT UP TO 3200PSI AND CHECK FOR LEAK. AFTER 2 DAYS PRESSURE STARTED TO DROP SLOWLY. BOTTLE WERE REFILLED WITH NITROGEN	 TO 3200 PSI AND PRESSURE CONTINUE TO DROP SLOWLY ON LT SIDE. BOTTLE WAS REMOVED FROM FLOAT AND CHECK FOR LEAK. LEAK WAS	 FOUND COMING FROM SHEARHEAD ASSY. SHEARHEAD WAS REPLACED AND FLOAT RETURNED TO SERVICE. (TC NR 20080130002)		1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2008022100001	20080221	00001	CE  	2008	2	21	CA080131003      	1	20080116	G	7110	B140048	LATCH           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	COWLING	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			309  								(CAN) THE LOWER FWD COWLING HOOK AND CAM ASSY FAILING TO LATCH WITH THE UPPER COWL ASSY WHEN INSTALLING THE COWLS ON THE	 ENGINE. IT IS POSSIBLE TO HAVE THE ALIGNMENT MARKS INDICATE A SUCCESSFUL LATCH WHEN IN FACT THE HOOK MAY HAVE MISSED TH	E CAM DURING ROTATION OF THE HOOK. A THOROUGH VERIFICATION OF A SUCCESSFUL LATCH, IN ADDITION TO THE VISUAL ALIGNMENT MA	RKS INDICATION, IS REQUIRED WHEN INSTALLING ENGINE COWLS. (TC NR 20080131003)			1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
2008022100002	20080221	00002	NE  	2008	2	21	CA080131008      	3	20080109	G	6114		WASHER          	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				603  		B1991			B1991		(CAN) PROP MODEL 2D30-237 S/N B1991. UPON RECEIPT CUSTOMER WAS COMPLAINING THAT PROP WAS NOT CYCLING. ONCE PROP WAS DISM	ANTLED A CRACKED THRUST BEVEL WASHER WAS NOTICED. THE THRUST WASHER IS CRACKED RIGHT THROUGH, CAUSING THE BLADE TO HANG 	UP INSIDE OF THE BARREL. THIS UNIT HAS 603.3 HRS SLOH IN NOV 17/05. (TC NR 20080131008)				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
2008031900179	20080319	00179	CE  	2008	3	19	CA080201001      	1	20080130	G	3230	C6189CL	CHAIN           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	BENT            	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, A LOUD NOISE WAS HEARD AND THE GEAR FAILED TO RETRACT (3) GREEN INDICATION DURING INSP THE AFT NOSE 	GEAR CHAIN WAS BROKEN AND THE REMOTE CIRCUIT BREAKER WAS FOUND POPPED NOSE CHAIN AND MASTER LINK REPLACED AND SYS INSPEC	TED 5 GEAR CYCLES C/O AND NO FAULTS FOUND RECORDS INSPECTED FOR COMPLIANCE WITH AD 72-10-04 PART A FOUND CARRIED OUT AT 	INTERVALS NOT EXCEEDING 100 HOURS (TC NR 20080201001)			1	L	7	2 	3T	3	T		A14CE   	E4EA	6	C	P15EA	 
	20080520			2008	5	20	CA080201002      	2	20080201	G	7414	1051324	SPRING          		107902010   															IMPULSE COUPLING	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1220 							(CAN) MAGNETO WAS RECEIVED ON AN ENG FOR INSP, DUE TO VIBRATION. MAG ROTOR WAS SPUN BY HAND TO INSPECT BEARINGS AND WHEN	 THE IMPULSE COUPLING FLYWEIGHTS CONTACTED THE STOP PINS THE FORCE REQUIRED TO WIND UP THE SPRING WAS FOUND TO BE LESS T	HAN NORMALLY REQUIRED. THE MAG HAD A 500 HOUR INSP PERFORMED 116.2 HOURS AGO AND IT APPEARS THAT THE SPRING WAS IMPROPER	LY WOUND AT THAT TIME. REPAIR OF MAG IS BEING HELD OFF PENDING ESTIMATE OF ENTIRE ENGINE. (TC NR 20080201002)																 
	20081104		NE  	2008	11	4	CA080204001      	2	20080201	G	7261		OIL SYSTEM      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NR 1 ENGINE	OVERSERVICED    	W				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			W	J		INADEQUATE Q C            	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DUE TO HIGH OIL TEMP INDICATION, NR 1 ENGINE WAS SHUTDOWN BY THE CA, ACFT LANDED IN IAD WITHOUT INCIDENT AND TAXIE	D TO THE GATE UNDER ITS OWN POWER.  MAINT INSPECTED ACFT. INVESTIGATION OF ENGINE WAS BELIEVED TO BE OVER SERVICED. WHEN	 MAINT OPENED THE OIL TANK APPROX. 3 QUARTS OF OIL SPILLED OUT OF THE TANK. SUSPECT THE REMOTE REPLENISHMENT SYS TO BE A	T FAULT FOR THE OVER SERVICING AND HAS PLACED IT ON MEL. AFTER PROPER SERVICING LEVELS ARE MEET AND UNEVENTFUL ENGINE RU	NS ARE CARIED OUT THEY PLAN TO PUT THE ACFT BACK INTO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008031900180	20080319	00180	NM  	2008	3	19	CA080204004      	1	20080131	G	3232	8290018013	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT MLG DOOR	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			21658	166  							(CAN) RT MAIN GEAR DOOR CAUTION LIGHT AFTER T/O. GEAR CYCLED WITH NO CHANGE, FLIGHT RETURNED TO  BASE.  MAINT SUSPECTS T	HE FWD DOOR ACTUATOR TO BE AT FAULT. THE ACTUATOR WAS REPLACED AND FUNCTION CHECKS WERE C/O SERVICEABLE. THE ACTUATOR WA	S REPAIRED 166 HOURS AGO, I HAVE REQUESTED A TEARDOWN REPORT AND WILL UPDATE FURTHER WHEN THE INFORMATION IS AVAILABLE. 	CURRENT A/C HOURS: 43033:33 CYCLES: 47150 (TC NR 20080204004)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2008031900182	20080319	00182	NE  	2008	3	19	CA080204005      	2	20080204	G	7250	3024211	TURBINE WHEEL   								PWA   	PT6   	PT6A135     	52043	NE  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7075 								(CAN) THE CT DISK WAS FOUND WITH (4) VISUAL CRACKS AT (3) OF THE FIRTREES. THE CRACKS ARE LOCATED AT THE EDGE OF THE TOP	 SERRATION RADIUS WITH THE FIRTREE FACE. THE CRACKS ARE BELIEVED TO BE RELATED TO CORROSION, THEY ARE QUITE OPEN WITH SI	GN OF OXIDATION. CRACKS WERE NOTICED VISUALLY AFTER THE REMOVAL OF CORROSION AT THE EDGE ON THE FIRTREE FACE SIDE. THE F	PI TEST BEFORE AND AFTER THE REMOVAL OF CORROSION COULD NOT DETECT THE CRACKS. INVESTIGATION IS ON-GOING FURTHER RESULT 	WILL FOLLOW. (TC NR 20080204005)							4	T			E4EA				 
2008031900185	20080319	00185	SW  	2008	3	19	CA080205004      	1	20080201	G	5302	427034851103	SUPPORT         			BELL  	427   	427         	1182207	SW  										T/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			631  								(CAN) T/R GEARBOX SUPPORT CAST SURFACE FOUND CRACKED AT LWR FWD LEG, ATTACHMENT POINT FOR THE VERTICAL FIN. (TC NR 20080	205004)					1	G	7	1 	3U				R00001RC					 
2008031900186	20080319	00186	EU  	2008	3	19	CA080205005      	1	20080121	G	7603	350A57105721	BALL JOINT      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					THROTTLE LINK	WORN            	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN THROTTLE WAS RETARDED DURING ENGINE START, T4 CONTINUED TO INCREASE. EMERGENCY SHUTOFF PULLED AND ENGINE MOTO	RED AS T4 REACHED 900C FOR 2 SECONDS.  INVESTIGATION FOUND THE THROTTLE LINK DISCONNECTED BUT THE LOCKING PIN WAS PROPER	LY ENGAGED AND IN THE PROPER POSITION. INCIDENT WAS DUPLICATED 2 OUT OF 3 TIME ON TESTING. PARTS INSPECTED AND FOUND, EN	D EQUIPPED AND BALL JOINT BOTH WORN. (TC NR 20080205005)			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081104		WP  	2008	11	4	CA080205007      	2	20080129	G	7260	3588941	BEARING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TACH/GEN IDLER ASSY DUAL SPUR GEAR, CENTER ANTI FRICTION BEARING FOUND WITH AN UNUSUALLY HIGH AMOUNT OF RADIAL PLA	Y AND WAS EXTREMELY ROUGH WHEN TURNED OVER BY HAND. THE ENGINE WAS REMOVED DUE TO CARBON STEEL PLATELETS FOUND IN THE OI	L SAMPLE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2008031900188	20080319	00188	SW  	2008	3	19	CA080205008      	1	20080204	G	7603	540122519	POWER CABLE     			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	POWER LEVER	FROZEN          	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING A TEST FLIGHT, THE LT POWER LEVER CABLE FROZE AND WOULD NOT RESPOND TO INPUTS. THE OAT AT THE TIME WAS -28 	DEG C. THE POWER SETTING WAS AT MAX ITT FOR TEST PURPOSES.  SINCE THE PILOT COULD NOT REDUCE POWER, THE ENGINE WAS SHUTD	OWN AND THE PROPELLER WAS FEATHERED. THE AC RETURNED TO THE AIRPORT AND LANDED WITHOUT INCIDENT. UPON INVESTIGATION, MOI	STURE WAS FOUND IN THE POWER LEVER CABLE. THE MOISTURE WAS REMOVED FROM THE CABLE AND THE CABLE WAS INSPECTED SERVICEABL	E. THE AC WAS RETURNED TO SERVICE. (TC NR 20080205008)		1	H	7	2 	3T	4	T		2A4     	E2WE	6	C	P15EA	 
	20081104		NE  	2008	11	4	CA080206004      	2	20080116	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					LEFT	VIBRATION       	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								807605			(CAN) CREW REPORTED SEVERE NOISE AND VIBRATION FELT ON LT ENGINE. SHUT ENGINE DOWN AS PRECAUTION AND RETURNED TO FIELD. 	ENGINE/QEC REMOVED AND REPLACED. SIGNIFICANT DAMAGE TO TURBINE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2008031900194	20080319	00194	NE  	2008	3	19	CA080206008      	2	20080117	G	7320		COUPLING        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  					FUEL SYSTEM	WORN            	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								93137			(CAN) DURING CRUISE, THE ENGINE PARAMETERS WERE OBSERVED TO INCREASE REACHING NEAR MAXIMUM LIMITS. THE PILOT ELECTED TO 	SHUTDOWN THE ENGINE AND PERFORM A SINGLE ENGINE LANDING. POST FLIGHT INVESTIGATION REVEALED A WORN COUPLING BETWEEN THE 	FUEL PUMP AND FUEL CONTROL. (TC NR 20080206008)				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2008031900196	20080319	00196	NE  	2008	3	19	CA080206009      	2	20080122	G	7261		OIL SYSTEM      			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					ENGINE	EMPTY           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB AT APPROX FL190, THE CREW RECEIVED A LOW OIL PRESSURE WARNING AND PERFORMED A COMMANDED SHUTDOWN OF T	HE ENGINE. THE AC WAS DIVERTED TO AN ALTERNATE LANDING SITE.  POST FLIGHT INSP REVEALED NO INDICATION OF OIL ON THE SIGH	T GLASS. NO SIGNS OF EXTERNAL LEAKAGE. THE ENGINE HAS BEEN REMOVED AND RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL B	E PROVIDED TO TC WHEN AVAILABLE. (TC NR 20080206009)			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2008031900197	20080319	00197	NE  	2008	3	19	CA080206010      	2	20080123	G	7261		OIL SYSTEM      			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								AT0006			(CAN) THE CREW RECEIVED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUTDOWN THE ENGINE. SIGNS OF EXTERNAL LEAKAGE WERE FO	UND AT POST FLIGHT INSP. THE ENG HAS BEEN REMOVED FOR INVESTIGATION AND REPAIR.  MFG WILL CONTINUE INVESTIGATING THE EVE	NT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20080206010)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2008031900198	20080319	00198	NE  	2008	3	19	CA080206011      	2	20080124	G	7310	3035989	TUBE            			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					FUEL SYSTEM	PUNCTURED       	W				F	E	A		ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         	UNSCHED LANDING         		K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA								124341			(CAN) DURING CLIMB, AN ANTI-ICE WARNING FAULT WAS NOTED. 20 MINUTES LATER, AN ENGINE FIRE WARNING ANNUNCIATED. THE CREW 	FIRED ONE EXTINGUISHER BOTTLE AND SHUTDOWN THE ENGINE AND AN EMERGENCY WAS DECLARED. POST LANDING INVESTIGATION REVEALED	 THAT AN ENGINE SUPPLIED FUEL TUBE (PN 3035989) HAD BEEN PUNCTURED BY APPARENT FRETTING AND ABRASION AGAINST AN AIRFRAME	 SUPPLIED WIRING HARNESS.  THE SUSPECTED TUBE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE FURNISHED AS AV	AILABLE. (TC NR 20080206011)		2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2008031900199	20080319	00199	NE  	2008	3	19	CA080206012      	2	20080124	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA								70322			(CAN) THE CREW NOTED A LOW OIL PRESSURE WARNING DURING CRUISE AND ELECTED TO SHUTDOWN THE ENGINE. POST FLIGHT INSPECTION	 REVEALED OIL RESIDUE IN THE TAIL PIPE AND METAL PARTICLES ON THE OIL FILTER. THE ENGINE WAS REMOVED FOR INVESTIGATION. 	 MFG WILL CONTINUE TO INVESTIGATE THE EVENT AND REPORT FINDINGS ONCE ROOT CAUSE IS ESTABLISHED. (TC NR 20080206012)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008031900200	20080319	00200	NE  	2008	3	19	CA080206013      	2	20080129	G	7261		OIL CAP         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA								70730			(CAN) DURING CLIMB AT FL150, THE LOW OIL PRESSURE WARNING ANNUNCIATED AND PRESSURE WAS OBSERVED TO DROP TO 35 PSIG. THE 	ENGINE WAS SHUTDOWN BY THE CREW WHEN THE PRESSURE REDUCED TO 20 PSIG AND THE AC RETURNED TO BASE.  POST FLIGHT INVESTIGA	TION INDICATES THAT THE OIL FILLER CAP MAY NOT HAVE BEEN PROPERLY SECURED PRIOR TO THE FLIGHT. (TC NR 20080206013)				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008031900201	20080319	00201	EA  	2008	3	19	CA080206014      	2	20080104	G	8530	SL32006WA21P	CYLINDER HEAD   								LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			292  								(CAN) CYLINDER HEAD FOUND CRACKED AT OIL RETURN LINE BOSS, AT PIPE-THREADED FITTING HOLE. (TC NR 20080206014)											3	O			E274				 
2008031900202	20080319	00202	NE  	2008	3	19	CA080207005      	1	20080108	G	6410	SB7306102	BEARING         			SKRSKY	S92   	S92A        	       	NE  	GE    	CT7TS 	CT78A       	30136	NE  					T/R BLADE	DEBONDED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			42   			A11100355					(CAN) UPON A SCHEDULED 50HR INSP, A BOROSCOPING OF THE TAIL ROTOR BLADES HAD BEEN CARRIED OUT, TO CHECK PIVOT BEARINGS F	OR DEBONDING FROM TAIL ROTOR SPARE. ON ONE TAIL ROTOR BLADE A BEARING WAS SUSPECTED TO BE DEBONDED. UPON FURTHER INSPECT	ION WITH REMOVAL OF THE BEARING FROM THE TAIL ROTOR BLADE, IT WAS CONFIRMED THAT THE INNER PLATE OF THE PIVOT BEARING WA	S TOTALLY SEPARATED FROM THE BLADE SPAR. AFTER LOOKING AT THE BEARING PLATE IT WAS CLEARLY VISIBLE THAT THE ADHESIVE MAT	ERIAL USED TO BOND THE PLATE TO THE SPAR HAD ONLY ADHERED TO THE PLATE OF THE BEARING AND NOT TO THE SPAR. (TC NR 200802	07005)	2	G	7	2 	4U	4	U		R00024BO	E8NE				 
2008031900203	20080319	00203	NE  	2008	3	19	CA080207006      	2	20080129	G	7310	230360801	LINE            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL SYSTEM	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			30784	3062 							(CAN) THE ENGINE FUEL LINES WERE FOUND NOT TO BE CORRECTLY INSTALLED IAW AMM 73-10-08-401.  TUBES , FUEL SYS, REMOVAL / 	INSTALLATION.   AFFECTIVITY: ON AC ALL - DATE: EEP 01/02 (P).  THIS HAS RESULTED IN (3) OF THE (4) ENGINES FUEL LINES TO	 CHAFE WITH THE ENG INLET ANTI-ICE AIR SUPPLY TUBE. ONE OF THE ENGINE FUEL LINES WAS CHAFED THROUGH AND WAS ALLOWING FUE	L TO LEAK OUT. (TC NR 20080207006)			2	H	7	4 	4F	4	F		A49EU   	E6NE				 
	20080520			2008	5	20	CA080207007      	4	20080130	G	2562	ELT97A2560000000	ELT             			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  		FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			134  								(CAN) NUMEROUS UNCOMMANDED ELT ACTIVATIONS WITH ELT97.  HAVE HAD ACTIVATIONS WITH THE AC INFLIGHT AND PARKED ON THE APRO	N. THE LASTEST WAS WITH ELT S/N-4584 ON JANUARY 30, 2008.  THE AC HAD BEEN PARKED ON THE APRON FOR ROUGHLY 2 HOURS WHEN 	THE ELT SIGNAL WAS DETECTED. ALL ELTS HAVE BEEN CONFIRMED AS DEFECTIVE AFTER AN ACTIVATION BY REPLACEMENT OR BY SWAPPING	 WITH ANOTHER AC.  DEFECTIVE ELTS HAVE BEEN RETURNED TO THE MFG FOR REPAIR OR REPLACEMENT. ATTEMPTS TO GET SUPPORT FROM 	MFG HAVE YEILDED LIMITED RESULTS. (TC NR 20080207007)		2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2008031900204	20080319	00204	EA  	2008	3	19	CA080207010      	2	20080204	G	7322	105217	CARBURETOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	LOOSE           	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				731  							(CAN) CARB HEAT SEEMED TO HAVE A SLIGHTLY EXCESSIVE DROP AT HIGHER RPM. (TC NR 20080207010)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2008031900205	20080319	00205	EU  	2008	3	19	CA080207011      	1	20080131	G	6130	312089001	PROP BRAKE      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2	SEIZED          	W				F				ACTIVATE FIRE EXT.      				J	A		WARNING INDICATION        	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			CA								PCE120893			(CAN) AFTER ARRIVAL AT DESTINATION, THE AC TAXIED TO THE TERMINAL. PRIOR TO PASSENGER DEPLANING, THE CREW OBSERVED A MAS	TER WARNING (PROP UNLOCK). THE F/O REPORTED THAT THE NR 2 ENG WAS ON FIRE AND THE NR 2 CONDITION LEVER WAS SELECTED TO S	HUTOFF POSITION. THE F/O OBSERVED THAT THE FIRE CONDITION WAS STILL EVIDENT AND THUS THE GROUND ENGINE FIRE CHECK LIST W	AS CARRIED OUT. NO FIRE INDICATION WAS OBSERVED ON THE FLIGHT DECK AND INSPECTION OF THE ENG AND NACELLE BY MAINT FOUND 	NO INDICATION OF FIRE. THE PROP BRAKE REPLACEMENT PROCEDURE WAS COMPLETED, SYS CHECKED SERVICEABLE AND THE AC RETURNED T	O SERVICE. (TC NR 20080207011)	2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2008031900206	20080319	00206	CE  	2008	3	19	CA080208001      	1	20080206	G	5610	50420066317	WINDOW          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	LT COCKPIT	DEPARTED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) DURING CLIMBOUT AT APPROX 3PSI DIFFERENTIAL, THE LT COCKPIT SIDE WINDOW BLEW OUT OF AIRCRAFT.  IT IS DIFFICULT TO 	DETERMINE THE CAUSE AS THERE IS VERY LITTLE REMAINING OF THE ORIGINAL WINDOW. (TC NR 20080208001)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
	20080520			2008	5	20	CA080208002      	4	20080208	G	2562	AK450	ELT             			BEECH 	60    	60          	1153602	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  		FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN TESTING THE ELT AT ITS ANNUAL INSP THE ELT HAD NO MODULATION AND NO OUTPUT POWER. THE ELT REPLACED WITH A SER	VICEABLE UNIT. (TC NR 20080208002)					1	L	7	2 	3O	3	O		A12CE   	E10EA	5	C	P31EA	 
2008031900207	20080319	00207	NE  	2008	3	19	CA080208003      	2	20080204	G	7210	70BM052000	REDUCTION GB    			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  						MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5479 	2482 							(CAN) DURING DAILY INSPECTION SMALL FLAKES WERE FOUND ON THE NON-MAGNETIC CHIP PLUG ON (MODULE) MO 5.  ENGINE OIL WAS CH	ANGED OIL FILTER WAS CHANGED ALL MAG PLUGS INSPECTED AND CLEANED. A/C FLEW FOR 11.1 HRS AND SMALL FLAKES WERE FOUND ON S	AME PLUG. A/C WAS GROUNDED AT THIS TIME AND MFG WAS INFORMED.  A OIL SAMPLE WAS SENT FOR EVALUATION AND CAME BACK AS NOR	MAL. MFG HAS DECIDED TO REPLACE THE MO 5. (TC NR 20080208003)			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
2008031900208	20080319	00208	EA  	2008	3	19	CA080208005      	2	20080129	G	8530	734352	PUSHROD         			MAULE 	M5    	M5235C      	5460135	SO  	LYC   	O540  	O540J1A5    	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1235 								(CAN) THE INTAKE AND EXHAUST PUSHRODS LOCATED AT THE NR1 CYL POSITION WERE NOT DRILLED THROUGH ON ONE END. THIS WOULD NO	T ALLOW OIL TO TRAVEL UP THE PUSHROD TO THE ROCKER. (TC NR 20080208005)					1	H	7	1 	3O	3	O		3A23    	E295	5	C	P920	 
2008031900212	20080319	00212	CE  	2008	3	19	CA080211001      	1	20080207	G	2720	1303800033	TRANSDUCER      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	RUDDER BOOST	FAILED          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA			188  	188  							(CAN) THE AC WAS DISPATCHED ON A MEDIVAC FLIGHT AND UPON STARTING THE TAKEOFF ROLL AN UNCOMMANDED RUDDER INPUT WAS FELT 	BY THE PILOTS. THE AC RETURNED TO THE HANGER WHERE MAINT BEGAN TO TROUBLESHOOT THE PROBLEM. IT WAS DISCOVERED THAT THE L	T RUDDER BOOST TRANSDUCER (P/N130-380003-3) FAILED WHICH SIMULATED ENGINE FAILURE AND CAUSED THE RUDDER BOOST SYS TO ACT	IVATE. THE TRANSDUCER WAS REPLACED AND THE AC RETURNED TO SERVICE. (TC NR 20080211001)			2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
	20081222		CE  	2008	12	22	CA080211002      	1	20080205	G	2750	552500079	ROLLER          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CENTER FLAP AFT	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CAMPAIGN NOTICE 851-27-50-043, FLAP CTR AFT BEARING INSTALLATION, COMPLIED WITH. NO FAULTS FOUND ON LT FLAP INSTAL	LATION. RT FLAP AFT CENTER ROLLER BEARING FOUND TIGHT, BEARING WOULD NOT TURN UNLESS FLAP WAS HELD WITH PRESSURE APPLIED	. NO DAMAGE TO BEARING OR SUPPORT FOUND. AFT CENTER ROLLER BOLT ADJUSTED IAW MM 27-51-04, PG 208 PARA B-5-B(2).  WORK DO	CUMENTED ON ASD-MP-01 REPORT NR859-02/04/08.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008031900214	20080319	00214	EA  	2008	3	19	CA080211006      	2	20080208	G	7310	3011849	LINE            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUEL SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) PILOT REPORTED HEAVY GAS ODOR IN COCKPIT AFTER TAKEOFF,  ACCOMPANIED BY A MIST. MAINT ENGINEER FOUND A CRACKED FUE	L LINE IN THE  NR 2 ENGINE NACELLE THAT CONNECTS THE START CONTROL UNIT TO THE FUEL CONTROL UNIT CAUSING A FUEL LEAK THA	T WAS SUBSEQUENTLY SUCKED INTO THE ENGINE COMPRESSOR SECTION AND THEN TRANSMITTED TO THE CABIN OF THE AC THROUGH THE BLE	ED AIR SYS. (TC NR 20080211006)			1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
2008031900215	20080319	00215	NM  	2008	3	19	CA080211007      	1	20080207	G	3213	101683	ROLLER          	MESSIER     		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	STRUT	SEIZED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA						DEC128384					(CAN) AFTER SELECTING LANDING GEAR DOWN THE LT MAIN GEAR REMAINED UP, THE LANDING GEAR WAS CYCLED UP AND DOWN AGAIN, THE	 LT GEAR CAME DOWN NORMALLY, (3) GREENS. THE AC WAS FERRIED BACK TO BASE, GEAR DOWN, FOR MAINT.  AFTER CARRYING OUT (2) 	GEAR SWINGS ON JACKS THE LT GEAR REMAINED UP ON THE 2ND DOWN SELECTION, APPROX (1) MINUTE LATER THE LT GEAR RELEASED AND	 EXTENDED TO DOWN AND LOCKED. IT WAS DISCOVERED THAT THE UPLOCK ROLLER ON THE SHOCK STRUT ASSY WAS SEIZED, THE ROLLER WA	S REMOVED LUBRICATED AND RE-INSTALLED. FURTHER RETRACTIONS AND EXTENSIONS WERE CARRIED OUT WITHOUT ANY PROBLEMS, AC RETU	RNED TO SERVICE. (TC NR 20080211007)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080520		NM  	2008	5	20	CA080211009      	1	20080204	G	2710	19004212401	CONTROL CABLE   			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) C02 CHECK: DURING AILERON CONTROL CABLES INSP ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401 AND 	P/N 190-04209-401, RT P/N 190 -05550-401 AND P/N 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT	 LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 5 AND J/C 27-11-00-00	3-RT/2 . THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. FL	EET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211009)		2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20080520		NM  	2008	5	20	CA080211011      	1	20080111	G	2710	19004212401	CONTROL CABLE   			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) C02 CHECK: DURING AILERON CONTROL CABLES INSPECTION ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-40	1 AND P/N 190-04209-401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATE	D AT LT AND RT WINGS RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REF J/C 27-11-00-003-LT/1 AND J/C 27-11-00-003-RT	/2 . THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON THE FAIRLEAD. AIR CA	NADA FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211011)		2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20080520		NM  	2008	5	20	CA080211012      	1	20080123	G	2710	19004212401	CONTROL CABLE   			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AILERON CONTROL CABLES INSP ,ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401 AND PN 190-04209	-401, RT PN 190 -05550-401 AND PN 190-04209-401) WORN AND HAS SEVERAL WIRES BROKEN AT FAIRLEAD LOCATED AT LT AND RT WING	S RIB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL. REFERENCE J/C 27-11-00-003-LT/1 SNAGS NR 128, 165 AND J/C 27-11-00-0	03-RT/2 SNAGS NR 87, 166. THE WORN AREA WITH A FEW BROKEN STRANDS FOUND UNDER GROMMET NYLON (P/N PE49068-501) MOUNTED ON	 THE FAIRLEAD. SAME FINDING ON ERJ190 NR 00015 HRS5830 CYCLES 2643 C02 CHECK AND ALSO ERJ190 NR 00013 HRS5720 CYCLES 263	5 C02 CHECK. FLEET DEPARTMENT HAVE BEEN ADVISED (TC NR 20080211012)	2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20080520		EA  	2008	5	20	CA080211013      	1	20080210	G	2720	274001	PCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					RUDDER	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				4499 							(CAN) TASK NR RJ2-27-900-714 FOR THE BACKLASH AND FUNCTIONAL CHECK OF RUDDER CONTROL SYS WAS CARRIED OUT ON THIS AC DURI	NG A HEAVY MAINT CHECK. TEST RESULT PARAMETERS WERE FOUND BEYOND LIMITS. FURTHER INVESTIGATION DURING RECTIFICATION LEAD	 TO THE DISCOVERY OF THE NR 2 RUDDER PCU LINKAGE ROD BEING FOUND COMPLETELY SHEARED OFF.  THERE WERE ALSO DAMAGE TO THE 	RUDDER ATTACH FITTING AND THE VERTICAL STABILIZER BRACKET.  A NEW PCU IS ON ORDER AND THE FAILED UNIT WILL BE REPLACED B	EFORE AC IS RELEASED FROM HEAVY CHECK. ENGINEERING DEPART HAS BEEN CONTACTED FOR DAMAGE EVALUATION AND POSSIBLE ISSUE OF	 A REPAIR EO FOR THE RUDDER FITTING AND BRACKET. THOSE UNITS WILL BE REPLACED AS WELL IF THEY ARE FOUND BEYOND REPAIR. I	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080520		NM  	2008	5	20	CA080211014      	1	20080131	G	2710	17005825401	CONTROL CABLE   			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING CONTROL CABLES INSP ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401, P/N 170-05826-401, RT P	/N 170-05827-401, P/N 170-05828-401) WORN AND WITH WIRES BROKEN AT SEVERAL FAIRLEADS, LOCATED AT LT AND RT WINGS IB OF T	HE RIB 12, 15, 17 AND AT RIB 20.  FLEET ENGINEERING AS BEEN ADVISED (TC NR 20080211014)				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20080520		NM  	2008	5	20	CA080211015      	1	20080207	G	2710	17005825401	CONTROL CABLE   			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 170-05825-401, P/N 170-05826-401,	 RT PN 170-05827-401, PN 170-05828-401) WORN AND WITH WIRES BROKEN AT SEVERAL FAIRLEADS, LOCATED AT LT AND RT WINGS IB O	F THE 17  FLEET ENGINEERING HAVE BEEN ADVISED (TC NR 20080211015)				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
2008031900217	20080319	00217	SW  	2008	3	19	CA080211017      	1	20080208	G	2913	206076030101	PUMP            			BELL  	206   	206L3       	1182108	SW  										HYDRAULIC SYS	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, AC LOST HYDRAULICS. AC LANDED SAFELY. MAINT FOUND HYDRAULICS PUMP SPLINE ROUNDED OFF. TACH GENERATO	R SPLINES WORN AS WELL. (TC NR 20080211017)					1	G	7	1 	3U				H2SW    					 
2008031900219	20080319	00219	CE  	2008	3	19	CA080211018      	1	20080206	G	3233	508202085	ACTUATOR        			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA				1711 							(CAN) DURING DESCENT INTO INTENDED AIRPORT THE NLG INDICATOR INTRANSIT LIGHT STAYED ILLUMINATED WHEN LANDING GEAR EXTEND	ED. MAIN GEAR DOWN AND LOCKED LIGHT WERE GREEN. A FLY-BY WAS CARRIED OUT WITH GROUND MAINT VERIFYING THAT THE NLG WAS IN	DEED ONLY HALF WAY DOWN WITH MAINS FULLY DOWN. AN EMERGENCY EXTENSION WAS ATTEMPTED AND FAILED TO EXTEND THE NLG. THE CR	EW DECLARED AND EMERGENCY. A LANDING WAS CARRIED OUT WITH ENGINES SHUTDOWN AND PROPS FEATHERED. THE AC WAS LANDED WITH A	 TOTAL NLG COLLAPSE. THE AC WAS REMOVED FROM RUNWAY. (TC NR 20080211018)		1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
	20080520		CE  	2008	5	20	CA080211019      	1	20080104	G	2820	20282004500R	SELECTOR        			CESSNA	172   	172M        	2072418	CE  	THIELT	TAE125	TAE12501    	59300	EU  					FUEL SYS	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND I	NSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEA	DER TANK. THE B-NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE W	AS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REP	LACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAK	S WERE FOUND. THE OTHER (2) FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. (TC NR 20080211019)	1	H	7	1 	3O	3	B	NT	3A12    	E00069EN				 
2008031900221	20080319	00221	EA  	2008	3	19	CA080212001      	1	20080212	G	5711	C6WM10271	ADAPTER         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON COMPLIANCE WITH SB 6/540 (WING-FRONT SPAR ADAPTER ASSEMBLY (P/N C6WM1027-1) INSPECTION FOR CRACKS) A CRACK WA	S FOUND ON THE LT FRONT SPAR ADAPTER. REPLACED LT FRONT SPAR ADAPTER ASSY PN C6WM1027-1 WITH PN C6WM1027-3 IAW SB NR 615	42. (TC NR 20080212001)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081229		CE  	2008	12	29	CA080212003      	1	20080201	G	5753	55250007	SUPPORT         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A CAMPAIGN NOTICE OF THE RT FLAP CENTER BRG INSTALLATION, BOTH OF THE AFT FLAP BEARINGS WERE FOUND LOOSE AN	D WORN DUE TO THE LOCATING PIN ON THE BEARINGS NOT INSTALLED INTO MATING HOLES OF FLAP RIB EXTENSIONS.  FLAP ROLLER PN K	JS 112603 AND BOTH CENTER AFT FLAP ROLLER SUPPORT BRGS P/N 5525000-79 WERE REPLACED.FLAPS FUNCTION CHECK SERVICEABLE AND	 ACFT RETURNED TO SERVICE.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008031900223	20080319	00223	EA  	2008	3	19	CA080212004      	1	20080129	G	5411	C6WM10271	ADAPTER         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON COMPLIANCE WITH SB 6/540 (WING-FRONT SPAR ADAPTER ASSY (P/N C6WM1027-1) INSP FOR CRACKS) A CRACK WAS FOUND ON	 THE RT FRONT SPAR ADAPTER. REPLACED RT FRONT SPAR ADAPTER ASSY PN C6WM1027-1 WITH PN C6WM1027-3 IAW SB NO 61542.  ALSO 	REPLACED WEB SUB ASSY SPAR P/N C6W1030-S102 AND WEB NOSE SPAR C6W1056-62 SRM PSM 1-6-3, CHAPTER 51-10-00 AND 51-30-00. (	TC NR 20080212004)			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2008031900227	20080319	00227	EA  	2008	3	19	CA080212005      	2	20080208	G	7320		LINK            	BENDIX      		HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					FUEL INJECTOR	DISCONNECTED    	W				R				AUTOROTATION            				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE COTTER PIN SECURING THE IDLE MIXTURE LINK BLOCK TO THE MIXTURE CONTROL ARM BECAME DISLODGED. THIS ALLOWED THE 	MIXTURE LINK BLOCK TO BECOME DISCONNECTED FROM THE MIXTURE CONTROL ARM. RESULTING A LOSS OF CONTROL OVER FUEL FLOW TO TH	E ENGINE AND THE ENGINE RETURNED TO GROUND IDLE POWER. (TC NR 20080212005)				1	G	7	1 	3O	3	O		4H12    	1E10				 
2008031900229	20080319	00229	EU  	2008	3	19	CA080213001      	1	20080208	G	2421	729722C	GENERATOR       	HONEYWELL   		AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2A5   	 	NE  					APU	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			32488	19916		PP1269					(CAN) DURING TROUBLESHOOTING FOR HIGH OIL CONSUMPTION ON THE APU, FOUND A 7 INCHES CRACK ON THE GENERATOR HOUSING. THE I	DG WAS REPLACED AND THE UNIT WAS SENT TO THE VENDOR FOR INVESTIGATION. (TC NR 20080213001)					2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
	20080520		CE  	2008	5	20	CA080213002      	1	20080211	G	3250	MC09543022	TUBE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	NLG STEERING	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			828  								(CAN) PROBLEM WAS DISCOVERED DURING PRE-INSP RUN UP. WHEN FULL RUDDER DEFLECTION WAS APPLIED THE RUDDER MOVEMENT WAS RES	TRICTED AND WOULD ONLY RELEASE WHEN ALTNATE RUDDER PRESSURE WAS APPLIED. (TC NR 20080213002)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2008031900231	20080319	00231	NM  	2008	3	19	CA080213003      	1	20080120	G	5610	070303	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				B	I			EMER. DESCENT           	CABIN DEPRESSURIZATION  			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE FLIGHT, THE F/O HEATED WINDSHIELD SHATTERED WITH NO APPARENT WARNING. THE CREW DEPRESSURIZED THE C	ABIN AND DESCENDED IAW THEIR CHECKLISTS AND CONTINUED THE FLIGHT TO THEIR DESTINATION. THE AC WAS ON A NON REVENUE FLIGH	T TO A MAINT FACILITY FOR THE COMPLETION OF A C-CHECK. THE WINDOW HAS BEEN REPLACED AND NO DEFINITIVE REASON FOR THE FAI	LURE HAS BEEN DETERMINED. THE TT ON THE WINDOW CAN NOT BE ACCURATELY DETERMINED BUT THE WINDOW HAS A MANUFACTURE DATE OF	 JAN 20, 2000. (TC NR 20080213003)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080520		GL  	2008	5	20	CA080213004      	1	20080206	G	2133	811441A010302	OUTFLOW VALVE   			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					CABIN PRESSURE	FAILED          	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CL	CLIMB          	1			CA			607  								(CAN) DURING CLIMB, THROUGH FL270, CABIN ROC (RATE OF CLIMB) INCREASED TO 3000 FPM (FT PER MINUTE), CABIN ALTITUDE START	ED TO CLIMB.  MANUAL PRESSURIZATION WAS SELECTED RESULTING IN AN INABILITY TO REDUCE CABIN ALTITUDE.  AC DESCENDED, EICA	S (CABIN ALT) MESSAGE POSTED AND OXYGEN MASKS DEPLOYED.  AN EMERGENCY WAS NOT DECLARED. TROUBLESHOOTING WAS CARRIED OUT,	 RT SAFETY VALVE FAILED THE TEST. BOTH SAFETY VALVES WERE REMOVED, THE INVESTIGATION IS ONGOING. (TC NR 20080213004)			2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
	20080520		GL  	2008	5	20	CA080213005      	1	20080103	G	2133	811441A010302	OUTFLOW VALVE   			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					CABIN PRESSURE	MALFUNCTIONED   	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA			419  	419  							(CAN) DURING CRUISE AT 45,000 FEET, THE PILOT REPORTED THAT THE CABIN ALT CLIMBED TO 22 000 FT, OXYGEN MASKS DEPLOYED AN	D AN EMERGENCY DESCENT WAS CARRIED OUT.  WAITING MORE INFO FROM CUSTOMER. THE MFG HAS INSPECTED THE VALVES AND THEY CONC	LUDE THE VALVES WERE (NO FAULT FOUND). THE INVESTIGATION IS ONGOING. (TC NR 20080213005)				2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
2008031900234	20080319	00234	NM  	2008	3	19	CA080213006      	1	20080122	G	3246	314353	WHEEL           			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE DAILY INSP, IT WAS NOTED THAT THE LT MAIN WHEEL WAS LOOSING AIR ON A DAILY BASIS. THE WHEEL ASSY WAS RE	MOVED AND SENT FOR INSP. INSP REVEALED THAT THE INNER RIM HALF WAS CRACKED AT THE FUSE PLUG AND FURTHER INSP REVEALED CR	ACKING AT THE BRG RACE. THIS WHEEL WAS REMOVED FOR THE FIRST TIME OFF OF A RECENTLY PURCHASED AC AND TOTAL TIME ON THIS 	PART IS UNDETERMINED. (TC NT20080213006)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081229		CE  	2008	12	29	CA080213007      	1	20080131	G	2910	SEEDESCRIPTION	HOSE            			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					HYD SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1036 								(CAN) DURING INSP OF FLAP SYS FOUND 6 HYD HOSES FOR SPEED-BRAKE/LIFT-DUMP ACTUATORS WITH MINOR HYD FLUID SEEPAGE. THE FO	LLOWING PN HOSES WERE REPLACED. AE1011925E0087, AE1011925E0094, AE1011925E0121, AE1011888E0132, AE1011924E0103, AE101193	3E0086.				2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
	20080520		EU  	2008	5	20	CA080213008      	1	20080208	G	2913		PUMP            			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	HYD SYSTEM	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) SHORTLY AFTER DEPARTURE, THE CREW OBSERVED A LOW PRESSURE INDICATION ON THE BLUE HYDR SYS. THE AC RETURNED TO POIN	T OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE BLUE SYS PUMP AND THE AC WAS RETURNED TO SERVICE. 	(TC NR 20080213008)				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20080520		NE  	2008	5	20	CA080213010      	3	20080209	G	6114		SEAL            	HAMSTD      	54H60117    	LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	PUMP HOUSING	TORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON TAKEOFF FROM AIRPORT, THE CREW OBSERVED A LOW OIL INDICATION ON THE NR 1 PROPELLER. THE AC RETURNED TO POINT OF	 DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM.  MAINT REPLACED THE NR 1 PROPELLER ASSY. THE AC WAS RETURNED TO SERVICE A	FTER SATISFACTORY LEAK CHECK AND GROUND RUN. IT WAS DETERMINED THAT THE FLUID LOSS WAS DUE TO A DAMAGED FRONT PROPELLER 	PUMP HOUSING SEAL (TC NR 20080213010)			2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
	20080521		CE  	2008	5	21	CA080213013      	1	20080104	G	2823	20282004500R	SELECTOR        			CESSNA	172   	172M        	2072418	CE  	THIELT	TAE125	TAE12502114 		EU  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND I	NSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEA	DER TANK. THE B NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE W	AS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REP	LACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAK	S WERE FOUND. THE OTHER TWO FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. THIS IS THE SECOND PART. (TC	1	H	7	1 	3O	3	B	NT	3A12    	E00069EN				 
	20080522		CE  	2008	5	22	CA080213014      	1	20080104	G	2823	20282004500R	SELECTOR        			CESSNA	172   	172M        	2072418	CE  	THIELT	TAE125	TAE1250299  		EU  					FUEL SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AC WAS BEING RETRO-FITTED WITH A 2.0 TURBO DIESEL ENGINE IAW STC. THE FUEL SYS WAS COMPLETED, FUEL INSTALLED AND I	NSPECTED FOR LEAKS. A LEAK WAS DISCOVERED COMING FROM THE FUEL SELECTOR AT THE NIPPLE FOR THE FUEL LINE GOING TO THE HEA	DER TANK. THE B-NUT WAS CHECKED FOR TIGHTNESS BUT FUEL CONTINUED TO LEAK. THE SELECTOR WAS THEN REMOVED AND THE NIPPLE W	AS FOUND NOT TO HAVE A CORRECT MATING SURFACE FOR THE FLARE. AFTER BENCH CHECKING THIS SELECTOR ALONG WITH (2) OTHER REP	LACEMENTS ALL WERE FOUND TO HAVE THE SAME DEFECT. ONE FUEL SELECTOR NIPPLE WAS RESURFACED AND AFTER INSTALLATION NO LEAK	S WERE FOUND. THE OTHER (2) FUEL SELECTORS WERE SENT BACK TO THE FACTORY FOR INVESTIGATION. THIS IS THE THIRD PART. (TC 	1	H	7	1 	3O	3	B	NT	3A12    	E00069EN				 
2008031900237	20080319	00237	GL  	2008	3	19	CA080214001      	1	20080212	G	2720	2227271400	RUDDER PEDAL    			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	COCKPIT	CORRODED        	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			3435 								(CAN) IT HAS BEEN NOTICED THAT ALTHOUGH THIS AREA IS LUBRICATED IAW THE MFG MAINT SCHEDULE WITH LPS2, THIS AREA CONTINUO	USLY CORRODES TO THE POINT THAT IT AFFECTS THE POSITIONING OF THE RUDDER PEDALS. (TC NR 20080214001)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081104		SW  	2008	11	4	CA080214002      	1	20080213	G	7714		DRIVE SHAFT     			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110U   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	TACH GENERATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TROUBLESHOT NO RPM INDICATION. REMOVED TACH GENERATOR FROM RT ENGINE, DRIVE SHAFT WAS STILL STUCK IN THE ENGINE. I	T APPEARS THAT THE SHAFT SEPARATED FROM THE ARMATURE INSIDE. REMOVED THE SHAFT, NO DAMAGE TO THE ENGINE DRIVE. INSTALLED	 SERVICEABLE PART AND TESTED FINE.  (TC NR 20080214002)				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2008031900242	20080319	00242	CE  	2008	3	19	CA080214005      	1	20080214	G	2750	1013800005	DRIVE SHAFT     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	FLAP DRIVE	SEIZED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) FLAPS WOULD NOT RETRACT AFTER TAKEOFF AND CIRCUIT BREAKER OPENED. AIRCRAFT RETURNED TO AIRFIELD. FLAP DRIVE SHAFT 	WAS FOUND SEIZED AND BOUND UP NEAR MOTOR. MOTOR AND DRIVE SHAFT WERE REPLACED. (TC NR20080214005)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
	20080603		NM  	2008	6	3	CA080214007      	1	20080121	G	2910	82970009325	HYDRAULIC LINE  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			34968								(CAN) WHILE ENROUTE THE "IB ROLL SPL HYD" AND NR 1 "HYD ISO VLV" CAUTION LIGHTS ILLUMINATED. CHECKED THE HYD QUANTITY AN	D NOTICED NR 1 QUANTITY AT 1.0 AND DECREASING. COMPLETED THE QRH CHECKLIST AND THEN BRIEFED THE F/A AND PASSENGERS. MADE	 A VISUAL APPROACH AND LANDING WITHOUT ANY FURTHER EVENTS.  MAINT INVESTIGATION DETERMINED THE LEAK TO BE FROM THE NR 1 	HYD SYS PRESSURE MANIFOLD ENGINE DRIVEN PUMP INLET PRESSURE TUBE FLARE AND FITTING. THE FLARE WAS FOUND TO BE CRACKED AN	D THE FITTING HAD EVIDENCE OF PITTING CORROSION. THE TUBE AND FITTING WERE BOTH REPLACED IAW THE AIRCRAFT MM AND SUBSEQU	ENTLY TESTED SERVICEABLE. (TC NR 20080214007)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080521			2008	5	21	CA080214008      	4	20080213	G	2562	0010009C	ELT             																	CABIN	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1    								(CAN) BATTERY CASE FOUND CRACKED DURING ANNUAL RECERTIFICATION. BATTERY KNOWINGLY NEVER DROPPED. UNKNOWN CAUSE OF CRACK,	 LOCATED AT BOTTOM OF THE CASE IN ANTENNA STOWAGE CHANNEL. (TC NR 20080214008)																		 
	20080521		WP  	2008	5	21	CA080214009      	1	20080114	G	3260		DOWNLOCK SWITCH 			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	MLG	DEFECTIVE       	W				L				ABORTED APPROACH        				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) ON APPROACH, ON A FERRY FLIGHT AND WHEN GEARS SELECTED DOWN, THE LT GEAR DID NOT INDICATE DOWN AND LOCKED, LANDING	 WAS ABORTED.  AFTER COMPLETING THE INDICATION, MALFUNCTION CHECKLIST, FOUND IN FACT THAT THE LT GEAR WAS DOWN AND LOCKE	D.  FOR PRECAUTIONARY MEASURES IN THE COMPANY PROCEDURES AN EMERGENCY LANDING WAS DECLARED THAN PROCEEDED WITH NORMAL LA	NDING. FOLLOWING MAINT INVESTIGATION FOUND LT MLG DOWNLOCK SWITCH DEFECTIVE, THE SWITCH WAS REPLACED AND RIGGED IAW MM A	ND AC RETUNED TO SERVICE. (TC NR 20080214009)		2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
	20080521		NE  	2008	5	21	CA080214010      	1	20080209	G	5340	3322203	ATTACH FITTING  		3035941     	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					SEATBELT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SUBJECT AC CRASHED ON APPROACH TO LANDING.  OPERATOR REPORTED TO THAT AN AFT-FACING CABIN SEAT BELT ATTACH FITTING	 FAILED ON IMPACT, PERMITTING THE SEAT BELT TO DETACH.  INSP OF FAILURE SHOWS THAT UNEXPECTED PRYING LOADS CAUSED THE FA	ILURE OF THE ALUMINUM ATTACH FITTING.  A DESIGN CHANGE IS REQUIRED TO PREVENT SIMILAR OCCURRENCES. I AM THE APPROVAL HOL	DER FOR THE MODIFICATION THAT INTRODUCES THESE SEATS INTO THE AC.  HAVE RECOMMENDED THAT THE OPERATOR REFRAIN FROM USING	 THESE SEATS FOR TAKEOFF AND LANDING UNTIL A FIX CAN BE INCORPORATED. AC IS EN-ROUTE BY TRUCK TO MY FACILITY. I HAVE CON	TACTED THE SEAT MFG REQUESTING ENGINEERING ASSISTANCE TO ADDRESS THIS DEFECT. (TC NR 20080214010)	1	G	7	2 	3U	3	U		H1NE    	E1GL				 
	20081230		CE  	2008	12	30	CA080214011      	1	20080124	G	2510	05142121	SEAT BACK       	CESSNA      		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	COCKPIT SEAT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			4056 								(CAN) SEAT BACK FRAME BROKEN JUST ABOVE INSERT ON THE OTBD SIDE. NOTEWORTHY ITEM: THIS SEAT DID HAVE A STEAL BAR INSTALL	ED IAW AD 2007-05-10. WE DO NOT KNOW WHETHER THIS WAS A CONTRIBUTING CAUSE TO THE FAILURE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
	20080521			2008	5	21	CA080215001      	4	20080207	G	2370	4954200001	VIDEO MONITOR   			BOEING	767   	7673Y0      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					CABIN	FIRE            	W				O				OTHER                   				A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			CA											(CAN) AFTER LANDING AND AFTER PASSENGERS HAD DEPLANED, THE F/A STILL ONBOARD THE AC NOTICED ONE OF THE BULKHEAD INFLIGHT	 ENTERTAINMENT MONITORS HAD FLAMES AND SMOKE EMINATING FROM IT.  AFTER INSPECTION OF VIDEO MONITOR, MAINT FOUND A PLUG M	ELTED AT PIN.  HARNESS WAS DISCONNECTED FROM P1 DISCONNECT ABOVE NO SMOKING SEATBELT SIGN. COAX CABLE ALSO DISCONNECTED.	 MONITOR REMOVED. FOUND CB ON P-37 PANEL IN E/E COMPT POPPED. VIDEO MONITOR MFR P/N: 02190830-1, MFG CODE: P0173 (TC NR 	20080215001).		2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
	20081105			2008	11	5	CA080215002      	4	20080214	G	3130	7013348931	DAU             			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  						MALFUNCTIONED   	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THIS DAU WAS ORIGINALLY REMOVED FROM ANOTHER OPERATOR ACFT WITH THE FAULT, LOSS OF N1 AND N2 INDICATION. MFG TESTE	D THE UNIT AND RETURNED IT TO SERVICE WITH NO FAULT FOUND, WITH ALL THE APPROPRIATE CERTIFICATION. THE UNIT WAS INSTALLE	D ON OUR ACFT IN NR1 POSITION WITH THE PROPER FUNCTION CHECK CARRIED OUT. DURING ENGINES RUN, ALL ENGINES INDICATIONS WE	RE NORMAL. A FEW HOURS LATER, WHILE THE ACFT WAS TAXIING OUT THE NR1 ENGINE INDICATION STARTED TO FLICKER. ACFT RETURNED	 TO OUR HANGAR WHERE THE DAU NR1 WAS REPLACED. DAU WILL BE RETURNED TO  WILL ALL THE PROPER DOCUMENTATION TO MAKE SURE T	HIS UNIT GET FINALLY REPAIRED. (TC NR 20080215002)	2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2008032000011	20080320	00011	SO  	2008	3	20	CA080215003      	1	20080214	G	7820	9948200	MUFFLER         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND OVER THE PAST YEAR THAT USING PRESSURE TESTING VS VISUAL HAS CAUGHT MANY PIN HOLE LEAKS IN THE MUFFLER. IN TH	E PAST WE WERE FINDING LARGE CRACKS IN BEHIND WHEN WE PRESSURE TESTED EVERY 200 HOURS WHICH YOU COULD NOT SEE VISUALLY S	O WE BEGAN PRESSURE TESTING ALL THE TIME VERSUS VISUAL. ALSO FOUND THAT AFTER INSTALLATION OF NEW EXHAUST, PIN HOLES BEG	AN TO SHOW BETWEEN 800-1000 HOURS LATER AND THEN PIN HOLES WOULD BEGIN TO SHOW EVERY 100 HOURS AFTER THAT. REALIZED THAT	 IF WE HAD NOT PRESSURE TESTED THE SYS, WOULD NOT FIND THE PIN HOLES AND WE WOULD END UP WITH A MAJOR REPAIR 100 HOURS L	ATER. SO WE NOW PRESSURE TEST THE EXHAUST SYS EVERY 100 HRS COMMERCIAL AND ANNUALLY WITH PRIVATES. THIS HAS LOWER THE OV	1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
	20080521		GL  	2008	5	21	CA080215005      	2	20080215	G	7230		CASE HALF       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON SPLITTING THE COMPRESSOR CASE HALVES FOR AN INSPECTION, IT WAS NOTED THERE WERE AREAS OF THE PLASTIC COATING TH	AT WERE MISSING.  CASES REPLACED. (TC NR 20080215005)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2008032500003	20080325	00003	SO  	2008	3	25	CA080215007      	1	20080209	G	5520	486104	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ELEVATOR STOP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSP OF THE ELEVATOR STOPS. WHEN THE DOWN STOP WAS PHYSICALLY TEST FOR SECURITY THE BOLT HEAD POP	PED OFF. UPON CLOSER INSP THE BOLT WAS CRACKED AND WAS BEING HELD IN PLACE BY THE NORMAL ELEVATOR DOWN PRESSURE. NO OTHE	R DAMAGE WAS NOTED, BOLT REPLACED AC RETURNED TO SERVICE. (TC NR 20080215007)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20080521		EA  	2008	5	21	CA080215008      	2	20080209	G	7314	RG9080J4A	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SYSTEM	ERRATIC         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			482  								(CAN) RT ENGINE DRIVEN FUEL PUMP REPLACED DUE TO ERATIC PRESSURE INDICATIONS. (TC NR 20080215008)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20080521		WP  	2008	5	21	CA080215009      	1	20080111	G	2497		CONNECTOR       			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	CONTROL PANEL	DAMAGED         	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMBOUT, AT 5500FT, THE ADI, HSI AND VSI WENT UNSERVICEABLE AT THE SAME TIME, COMPLETE LOSS OF ELECTRICAL POWE	R, RT SIDE. AT THE SAME TIME, THE NR 2 ENGINE FIRE WARNING (ILLUMINATED) CAME ON ALL 3 ZONES. CREW COMPLETED ENGINE FIRE	 DRILL. ATC ADVISED OF THE EMERGENCY, THE AC LANDED WITH NO OTHER INCIDENT REPORTED.  AFTER INVESTIGATION FOUND THE RT A	C CONTROL PANEL CONNECTOR DAMAGED AT PIN NR 10.  BOTH THE AC CONTROL PANEL UNIT AND THE CONNECTOR WAS REPLACED AND TESTE	D SERVICEABLE. A FLEET CAMPAING WAS CARRIED OUT TO INSPECT ALL THE AC CONTROL PANEL CONNECTORS FOR CONDITION AND NO DEFE	CT DETECTED. (TC NR 20080215009)	2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
	20080521			2008	5	21	CA080215010      	4	20080214	G	2215	2R5310A	SERVO           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					AUTOPILOT	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			5702 	5702 							(CAN) AUTOPILOT UNSERVICEABLE, EICAS MESSAGE (AP FAIL) ON FOR APPROX 3-5 SECONDS, THEN DISAPPEARS.  AUTOPILOT AILERON SE	RVO FAILED. FAULT CODES 22110239PA1 AND 22110239PA2 RECORDED. (TC NR 20080215010)					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20080521		EA  	2008	5	21	CA080215011      	1	20080214	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			7867 	7867 							(CAN) DURING SELECTION OF FLAPS FROM 30 DEG TO 45 DEG ON APPROACH RECEIVED (FLAP FAI) MESSAGE ON EICAS. FLAPS FAILED TO 	MOVE WITH INDICATION OF 34 DEG. NORMAL LANDING. MAINT INSP FOUND NO ABNORMALITIES. FLAP DRIVE SHAFTS REMOVED AND LUBRICA	TED IAW  COMPANY POLICY. (TC NR 20080215011)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080521		EU  	2008	5	21	CA080215012      	1	20080214	G	3150	B19030W04	DISPLAY         			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  						MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA			1874 	1874 							(CAN) THERE HAS BEEN REPORTS OF NUMEROUS SYS FAILURE REPORTS FROM THE VEMD SUCH AS NF/NR, MODULE, OVERLIMITS, LANE FAILU	RES AND LIGHTING FAILURES AND NONE OF THESE FAILURES ACTUALLY OCURRED.  THIS IS A PROBLEM WITH THE SOFTWARE AND HAS BEEN	 A PROBLEM ON THESE UNITS WITH YELLOW FAILURES EVERY DAY. (TC NR 20080215012)				1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
	20081229		CE  	2008	12	29	CA080215013      	1	20080207	G	2810	S51812	LINE            	CESSNA      		CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	BLADDER VENT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7218 								(CAN) LT AND RT NACELLE FUEL BLADERS WERE FOUND COLLAPSED. GROUND HANDLER REPORTED AIR RUSHING INTO TANK AFTER FILLER CA	P REMOVAL WHILE PREPARING TO FUEL ACFT.  FUEL VENT LINES WITHIN INTEGERAL WING TANK WERE FOUND TO HAVE HARD/BRITTLE RUBB	ER COUPLER HOSES WHICH LEAKED FUEL INTO THE VENT SYS AND WAS TRAPPED IN A LOW SYS IN THE VENT LINES CAUSING BLOCKED VENT	 LINES AND COLLAPSING THE BLADDER TANKS DURING FLIGHT. RUBBERS REPLACED AND SYS OPS NORMAL.			1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
	20080521		EA  	2008	5	21	CA080217002      	1	20080211	G	5610	NP13932111	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			11342								(CAN) CAPTAINS WINDSHIELD BROKE CLIMBING THROUGH 19000 FT. FOLLOWED QRH AND RETURNED TO FIELD.  WINDSHIELD IS A POST SB 	CONFIGURATION (TC NR 20080217002)					2	L	7	2 	4F			RT	A21EA   					 
	20080521		EA  	2008	5	21	CA080217003      	1	20080211	G	5610	NP13932111	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			12616								(CAN) ON ROTATION CAPTAINS WINDSHIELD CRACKED. FOLLOWED QRH AND RETURNED TO THE FIELD.  WINDSHIELD IS A POST SB CONFIGUR	ATION. (TC NR 20080217003)					2	L	7	2 	4F			RT	A21EA   					 
	20080521		EA  	2008	5	21	CA080218001      	1	20080216	G	3241	90004433	CONTROL UNIT    			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C5     	30050	NE  					ANTI SKID SYS	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			8195 								(CAN) ON LANDING, CREW RECEIVED IB ANTI-SKID CAUTION MESSAGE. AFTER TAXIING CLEAR OF ACTIVE RUNWAY IT WAS DETERMINED BOT	H LT MAIN TIRES FLAT. MAINT FOUND MDC FAULT CODES INDICATED FAULTY ASCU. ASCU REPLACED, AXLE INSP. FOR OVERTEMP AND TIRE	S REPLACED. FUNCTION CHECKS C/O WITH NO FURTHER FAULTS. (TC NR 20080218001)				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
200805141    	20080514	1    	EU  	2008	5	14	CA080218002      	1	20080218	G	7130	0292827110	HEAT SHIELD     	TMECA       	ARRIEL2B    	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5478 	2479 							(CAN) WHILE REPLACING THE MO5, SEVERAL HOLES WERE NOTICED. THESE HOLES WERE DUE TO RUBBING AND WERE ONLY THROUGH THE OUT	ER LAYER OF THE HEAT SHIELD. (TC NR 20080218002)					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20081230		CE  	2008	12	30	CA080218003      	1	20080218	G	3260	30A01002203202	INDICATOR       			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	HARTZL	HCF3Y	HCF3YR1     	GL  	MLG FLOAT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) IT WAS FOUND DURING AN INSP OF THE FLOATS THAT THE MLG INDICATOR COVERS COULD BE INSTALLED ON THE WRONG FLOAT.  IF	 INSTALLED INCORRECTLY THE GEAR INDICATION IS REVERSED.					1	H	7	1 	3O	3	O	RT	A4CE    	E14EA	5	C	P31EA	 
	20081230		CE  	2008	12	30	CA080218004      	1	20080218	G	2820	051338216	SELECTOR        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					FUEL SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSP THE FUEL SELECTOR DRIVE ASSY WAS FOUND TO BE WORN OUT. THIS ALLOWED A TANK SELECTION TO BE MADE WITHOU	T THE SELECTOR POSITIONING BALL AND SPRING HSG REACHING THE DETENT IN THE FUEL SELECTOR HSG.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20080521		EU  	2008	5	21	CA080218005      	1	20080218	G	7720	955017820	THERMOCOUPLE    			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					ENGINE	GROOVED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			478  								(CAN) AFTER LESS THAN 500 HRS THERMOCOUPLES FOUND WITH A GROOVE WORN INTO TIPS. THIS IS THE SECOND TIME THIS DEFECT HAS 	BEEN FOUND. (TC NR 20080218005)					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20080521		EU  	2008	5	21	CA080218006      	1	20080218	G	7722	9550178220	THERMOCOUPLE    			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					ENGINE	GROOVED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			478  								(CAN) AFTER LESS THAN 500 HRS THERMOCOUPLES FOUND WITH A GROOVE WORN INTO TIPS. THIS IS THE SECOND TIME THIS DEFECT HAS 	BEEN FOUND. (TC NR 20080218006)					1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20081113		EU  	2008	11	13	CA080219002      	1	20080208	G	6730		SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					FLLIGHT CONTROL	MALFUNCTIONED   	W				L				ABORTED APPROACH        				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		AP	APPROACH       	1			CA			10128	2345 							(CAN) ALSO APPLIES TO SERVO SC5081-1 S/N 229 TSN 8917.4 TSO 2342.6 AND SERVO SC5082-1 S/N 361 TSN 5634.5 TSO 2345.1. A/C	 WAS APPOACHING FOR LANDING AND WHEN THE COLLECTIVE WAS REDUCED THERE WAS A VIOLENT VIBRATION, SEVERE ENOUGH TO CAUSE CO	NCERN ABOUT LOSS OF CONTROL OF THE HELICOPTER. COLLECTIVE WAS INCREASED AND THE VIBRATION LEVEL RETURNED TO A NORMAL LEV	EL. ALL M/R SERVOS WERE REPLACED AT ACRO HELIPRO AND SUBSEQUENT TEST FLYING HAS PROVEN THAT TO BE THE ROOT CAUSE. THERE 	WAS SOME LOW POWER VIBRATIONS EXPERIENCED IN THE PAST 12 MONTHS AND MOST OF THE RELATED DYNAMIC COMPONENTS HAD BEEN REPL	ACED AND INSPECTIONS PERFORMED. THE VIBRATIONS WERE WITHIN LIMITS AND NEVER REACHED A LEVEL OF IMMEDIATE CONCEARN LIKE T	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20080603		NM  	2008	6	3	CA080219004      	1	20080218	G	3270	65715611	SKID            			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TAIL SKID	DEFECTIVE       	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) UPON GEAR RETRACTION, TAIL SKID LIGHT REMAINED ILLUMINATED. A/C RETURNED TO STATION WHERE SKID TIP WAS REPLACED, S	WITCH CONTACT CONFIRMED AND A/C RETURNED TO SERVICE. (TC NR 20080219004)					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20080521		NM  	2008	5	21	CA080219005      	1	20080219	G	5320	654659244	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										BS 790	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLOOR CHANNEL AT BS 790, RBL 8 AFT CARGO PIT CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20080219005)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080219006      	1	20080219	G	5321	654659247	FLOOR PANEL     			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL CORRODED AT BS 767+6, LBL 3 AND REPAIRED IAW CUSTOMER EA. (TC NR 20080219006)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080219007      	1	20080219	G	5320	654659249	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727+8, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080219007)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		EA  	2008	5	21	CA080220001      	1	20080219	G	7603	3018024	ROD END         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 2 THROTTLE	BENT            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) THE PILOT REPORTED A DEFECT NR 2582A: ABOUT 10 MINUTES AFTER TAKEOFF, THE RT ENGINE NR 2 THROTTLE LEVER WAS STUCK.	  WORKED THE THROTTLE BACK  AND FORTH IN CRUISE 3 - 4 TIMES AND FOUND OK.  ON FINAL APPROACH INTO ARRIVAL AIRPORT, THE N	R 2 THROTTLE WAS DIFFICULT TO MOVE AGAIN.  MAINT LATER FOUND THE WIRE WITH A 1.5 INCH LONG RIGID SPOT AT 18 INCHES FROM 	THE ROD END ATTACHMENT. THE ROD END P/N: 3008787 WAS FOUND BENT ALSO. BOTH PART WERE REPLACED AND RE-RIGGED THE ENGINE I	AW MM. THE ENGINE WAS RECENTLY REPLACED AND HAS 3.4 HOURS SINCE LAST OVERHAUL.  (TC NR 20080220001)		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20080521		SW  	2008	5	21	CA080220002      	1	20080218	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	DELAMINATED     	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			4902 								(CAN) DURING THE CRUISE PORTION OF FLIGHT, THE CREW WITNESSED THE RT SIDE COCKPIT HEATED WINDSHIELD PHYSICALLY DELAMINAT	ING . THE CREW INDICATED THE AC WAS OPERATING AT A 6.0 PSI DIFFERENTIAL WHICH IS WITHIN THE MAXIMUM 7.25 PSI DIFFERENTIA	L FOR THE AC. NO ACTION WAS TAKEN BY THE CREW OR WAS DEEMED NECESSARY AND THE WINDOW DELAMINATION WAS MONITORED CLOSLY U	NTIL LANDING.  MAINT HAS REPLACED THE WINDSHIELD. (TC NR 20080220002)			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20080521			2008	5	21	CA080220003      	2	20080220	G	7414		BEARING         																	MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			122  								(CAN) MAG WAS RECEIVED FOR INSPECTION DUE TO ENGINE OVERSPEED. WHEN THE ROTATING MAGNET (ROTOR) WAS SPUN BY HAND THERE W	AS NOTICEABLE SIDE PLAY IN THE BEARINGS. THE END PLAY WAS MEASURED AND FOUND TO BE .003 NR.   MFG HAS A LIMIT OF NO SIDE	 PLAY ALLOWED. THE MAG WAS INSPECTED AND NO OTHER DEFECTS WERE FOUND. SHIMS WERE ADDED TO THE BEARINGS TO THE PROPER PRE	LOAD AND THE MAG WAS TESTED AND RETURNED TO SERVICE. THIS WAS A FACTORY NEW MAGNETO WITH ONLY 121.5 HOURS IN SERVICE. (T	C NR 20080220003)															 
	20080521		EA  	2008	5	21	CA080220005      	2	20080130	G	7200		ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  		MAKING METAL    	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) DURING DESCENT, THE PROPELLER AUTO-FEATHERED UNCOMMANDED. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND PERFORMED A 	SINGLE ENGINE LANDING. POST FLIGHT INSP REVEALED A GRINDING NOISE WHEN TURNING THE PROP BY HAND. REDUCTION GEARBOX WAS C	ONTAMINATED WITH OIL. THE ENGINE HAS BEEN SENT FOR INVESTIGATION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT A	ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080220005)			2	L	7	2 	4T	3	T	RT	A24CE   	E2NE	6	C	P56GL	 
200805141    	20080514	1    	NE  	2008	5	14	CA080220006      	2	20080206	G	7250		TURBINE BLADES  	PWA         	PW127       	AEROSP	ATR72 	ATR72212    	8680945	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE ITT WAS NOTED TO RISE TO 800 DEGREES C, FOLLOWED BY SMOKE IN THE CABIN. THE CREW ELECTED TO SHUT	DOWN THE ENGINE AND RETURN TO POINT OF DEPARTURE. POST FLIGHT INSPECTION INDICATED FRACTURED POWER TURBINE BLADES AND EV	IDENCE OF OIL LEAKAGE. THE ENGINE WILL BE RETURNED TO MFG FOR INVESTIGATION. UPDATES WILL BE PROVIDED. (TC NR 2008022000	6)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
	20080521		NM  	2008	5	21	CA080220007      	1	20080115	G	7931		OIL SYSTEM      			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  					ENGINE	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE OIL PRESSURE WAS NOTED TO DROP. THE CREW SHUTDOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LAND	ING. ENGINE IS BEING SENT FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ES	TABLISHED (TC NR 20080220007)				2	H	7	2 	4T	4	T	RT	A45NM   	E20NE				 
	20080521		NE  	2008	5	21	CA080220008      	2	20080211	G	7200		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						SEIZED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, WHEN SELECTING BLEED AIR ON, THE CREW HEARD TWO (2) LOUD BANGS FOLLOWED BY SEEING SPARKS FR	OM THE EXHAUST.  PILOT SECURED THE ENGINE AND RETURNED TO POINT OF DEPARTURE.  POST FLIGHT INSP REVEALED A SEIZED PROP A	ND IMPACT DAMAGE INSIDE EXHAUST DUCT.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISH	ED (TC NR 20080220008)			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
	20080521		NM  	2008	5	21	CA080220009      	1	20080220	G	5320	654659249	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220009)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220010      	1	20080220	G	5320	654659247	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220010)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220011      	1	20080220	G	5320	654659249	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 847+14 - 867+14, LBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220011	)					2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220012      	1	20080220	G	5340	650163312	STRINGER CLIP   			BOEING	737   	7374S3      	1384711	NM  										BS 294.5 S13L	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TIE CLIP AT BS 294.5, S13L CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220012)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220013      	1	20080220	G	5310	651768537	DOOR FRAME      			BOEING	737   	7374S3      	1384711	NM  										L1 DOOR	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) L1 DOOR CUTOUT FRAME AT STA 349, WL 216 GOUGED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220013)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220014      	1	20080220	G	4910	656612115	SHROUD          			BOEING	737   	7374S3      	1384711	NM  										APU	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) APU UPPER SHROUD CRACKED FWD OF FWD LATCH REPAIRED IAW CUSTOMER EA. (TC NR 20080220014)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220015      	1	20080220	G	5313	65617777	STRINGER SPLICE 			BOEING	737   	7374S3      	1384711	NM  										BS360 S15L	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STRINGER SPLICE AT BS 360, STR 15L CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220015)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220016      	1	20080220	G	5320	65465926	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS767+6, LBL11 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220016)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220017      	1	20080220	G	5320	654659247	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727 F +8, LBL 11 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220017)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220018      	1	20080220	G	5534	655484221	SKATE ANGLE     			BOEING	737   	7374S3      	1384711	NM  										VERTICAL STAB	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) V STAB TO FUSELAGE SKATE ANGLE LT CHAFED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220018)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220019      	1	20080220	G	5320	6546592503	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 727E+8, RBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220019)						2	L	7	2 	4F			RT	A16WE   					 
200805141    	20080514	1    	NM  	2008	5	14	CA080220020      	1	20080220	G	5320	6546592503	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+6 - BS247+14, RBL 3 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 2008022002	0)					2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220021      	1	20080220	G	5320	654659247	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 847+14 - 867, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220021)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080220022      	1	20080220	G	5320	654659247	CHANNEL         			BOEING	737   	7374S3      	1384711	NM  										AFT CARGO PIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO PIT FLOOR CHANNEL AT BS 767+4, LBL 8 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20080220022)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		EA  	2008	5	21	CA080221001      	1	20080212	G	2810	CT2P10011	FUEL TANK       			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FORWARD	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16085								(CAN) THIS FWD FUEL TANK ENCLOSURE WAS FOUND BADLY DETERIORATED DUE TO ITS AGE, THERE WERE OLD REPAIRS FOUND CARRIED OUT	. THIS ASSEMBLY HAD BEEN BULGING DUE TO THE FUEL, CAUSING CLOSER TOLERANCES TO THE ELEVATOR CONTROL PUSH/PULL TUBE.  THI	S ASSEMBLY HAS NOW BEEN REPLACED WITH A NEW CERTIFIED UNIT MADE FROM ALUMINUM IAW STC SA 06-51 MDL P/N VT2MK1555, ISSUE 	1. (TC NR 20080221001)			1	H	7	1 	3T	4	T		A806    	E4EA	6	C	P15EA	 
	20081230		CE  	2008	12	30	CA080221002      	1	20080208	G	7820	PN04504003	MUFFLER         			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	EXHAUST SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS IS AN ON GOING ISSUE. THIS EXHAUST MUFFLER PASSED THE VISUAL INSP AS CF90-03. WHEN PRESSURE TESTED WITH AIR A	ND WATER, 3 PIN HOLES SHOWED. 2 WERE IN OPEN BARE METAL SURFACE. ONE WAS IN THE LONGITUDINAL SEAM. ANOTHER EXPERIENCED A	ME WAS IN MY SHOP FOR OTHER REASONS.  ASKED HIM TO VISUALLY INSPECT IAW CF90-03. EVEN THOUGH HE KNEW THERE WERE LEAKS, S	O HE LOOKED MORE INTENSELY, HE WAS UNABLE TO FIND ANY, VISUALLY. THIS IS A 50 PERCENT FAILURE RATE FOR ACFT IN MY SHOP. 	 AGAIN, THIS SHOP ONLY DOES BUBBLE TESTS AS THE VISUAL TEST, IAW CF90-03.		1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
	20080521		EA  	2008	5	21	CA080221003      	1	20080220	G	2913	601R751547	PUMP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					HYD SYSTEM	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			8050 								(CAN) CREW RECEIVED A GEAR DISAGREE MESSAGE AFTER TAKEOFF WITH AN APPLICABLE RED NOSE GEAR INDICATION AND 2 MAIN GEAR AM	BER MESSAGES. CREW ACTIONED THEIR QRH AND DO AN ALTERNATE EXTENSION, A/C RETURNED. PSEU CODES RETRIEVED AND THE AC WAS R	OUTED WHERE MAINT WILL INVESTIGATE FURTHER. NOSE GEAR OLEO SERVICED TO C/O AND 3A HYD PUMP TO BE REPLACED. MORE INFORMAT	ION TO FOLLOW. (TC NR 20080221003)			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080603		SW  	2008	6	3	CA080221004      	1	20080209	G	6320	PT6T3B	GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR	MISMANUFACTURED 	W				O				OTHER                   				J			WARNING INDICATION        			HO	HOVERING       	1			CA			37   								(CAN) MAINT WAS TROUBLESHOOTING OIL PRESSURE PROBLEMS. THE POWER SECTION ALWAYS APPEARED THAT IT HAD LOTS OF OIL. VISUAL	 INDICATION. THE OIL PRESSURE FLUCTUATIONS OCCURRED FEB. 5TH.  IN THE TROUBLESHOOTING PROCESS A LITTLE OIL WAS BEING DRA	INED AND YET THE VISUAL INDICATION THERE WAS LOTS OF OIL. ON FEB. 9TH THE PWR SECTION WAS REMOVED DUE TO LOSS OF OIL PRE	SSURE. A TECH REP WAS BROUGHT TO THE BASE AND IT WAS NOTICED THAT THE LOWER HOLE INTO THE GEARBOX OF THE OIL LEVEL INDIC	ATOR WAS NOT DRILLED INTO THE CASE. SINCE THE OIL COULD NOT DRAIN OUT OF THE VISUAL INDICATOR THE OIL LEVEL APPEARED FUL	L. (TC NR 20080221004)	1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081104		SW  	2008	11	4	CA080221005      	1	20080216	G	5302	206031327101	FITTING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6996 								(CAN) LOWER LT TAILBOOM ATTACH FITTING FOUND CRACKED IN WEB AREA ON SCHEDULED INSPECTION. POSSIBLE ALIGNMENT ISSUES FROM	 THE MFG. REPLACED WITH UPGRADED ONE PIECE FITTING AND LONGERON. (TC NR 20080221005)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20080603		NE  	2008	6	3	CA080221007      	2	20080208	G	7200	PT6A68	ENGINE          								PWA   	PT6   	PT6A68      	 	NE  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	E	A	WARNING INDICATION        	VIBRATION/BUFFET          	FLAME/FIRE                	NR	NOT REPORTED   	1			CA											(CAN) DURING A TRAINING MISSION, THE PILOT REPORTED HIGH ITT, VIBRATION AND FLAME FROM THE ENGINE EXHAUST AND ELECTED TO	 SHUTDOWN THE ENGINE. LANDED WITHOUT INCIDENT. ENGINE WILL BE REMOVED AND RETURNED FOR INVESTIGATION. MFG WILL CONTINUE 	INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221007)									4	T			E26NE				 
	20080521		NE  	2008	5	21	CA080221008      	2	20080213	G	7200		ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW121 	PW121       	52124	NE  						FLAMED OUT      	W				O				OTHER                   				R	X		PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           		AP	APPROACH       	1			CA											(CAN) DURING APPROACH, ENGINE SHUTDOWN UNCOMMANDED AS FLAPS WERE BEING EXTENDED FOR LANDING. POST FLIGHT INSP REVEALED U	NSTABLE FUEL FLOW AND LOW ITT AT IDLE POWER. FUEL PUMP AND FUEL CONTROL ARE BEING RETURNED FOR INVESTIGATION. MFG WILL C	ONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221008)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20080521		NE  	2008	5	21	CA080221009      	2	20080214	G	7320		EEC             			AEROSP	ATR72 	ATR72202    	8680940	EU  	PWA   	PW120 	PW124B      	 	NE  					ENGINE	FAULTED         	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, AN EEC FAULT WAS FOLLOWED BY AN ENGINE POWER LOSS AND VIBRATION. THE CREW SHUT THE ENGINE DOWN AND 	DIVERTED THE FLIGHT ACCORDINGLY. POST FLIGHT INVESTIGATION REVEALED BOTH OIL FILTERS TO BE CONTAMINATED WITH DEBRIS AND 	THAT THE PROPELLER COULD NOT BE ROTATED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLI	SHED (TC NR 20080221009)			2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
	20080521		NE  	2008	5	21	CA080221010      	2	20080214	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  						FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, A LOUD NOISE WAS HEARD FOLLOWED BY REDUCTION IN ENGINE POWER TO ZERO. THE AC LANDED ON A PUBLIC ROA	D. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221010)					1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20080603			2008	6	3	CA080221011      	4	20080217	G	6122		GOVERNOR        			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					PROPELLER	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING WAS ACTIVATED. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND DIVERT THE 	AIRCRAFT TO AN ALTERNATE LANDING SITE. INITIAL INVESTIGATION REVEALED SIGNIFICANT EXTERNAL OIL LEAKAGE FROM THE PROPELLE	R OVERSPEED GOVERNOR AREA. THE COMPONENT WAS REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUS	E ONCE ESTABLISHED (TC NR 20080221011)			2	H	7	2 	4T	4	T	RT	        	E20NE				 
200805141    	20080514	1    	NE  	2008	5	14	CA080221012      	2	20080214	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			936  								(CAN) DURING THE PREFLIGHT CHECK THE ENGINE DRIVEN FUEL PUMP FOUND LEAKING OIL. (TC NR 20080221012)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081104			2008	11	4	CA080221013      	4	20080214	G	3416	066030620010	ALTIMETER       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA				112  							(CAN) FLAG CAME INTO VIEW IN PILOTS ENCODING ALTIMETER AND NEEDLE FROZE. RETURNED TO NORMAL MOMENTS LATER. MAINT WAS NOT	 ABLE TO DUPLICATE THE SNAG. THERE IS AN SDR 20070914001 PERTAINING TO THE SAME DEFECT ON THIS SN UNIT, AS INSTALLED IN 	A DIFFERENT PC12. THE REPAIR REPORT AT THAT TIME INDICATED THE DEFECT HAD BEEN CONFIRMED AND REPAIRED. (TC NR 2008022101	3)			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080521		NM  	2008	5	21	CA080222001      	1	20080219	G	3246	L8121482629	BEARING         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	MLG WHEEL	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19373	233  							(CAN) DURING SERVICE CHECK ON THE RAMP, LINE MAINT OBSERVED THAT NR3 MAIN WHEEL ASSY HUB CAP WAS MISSING AND NOTICED THE	 PRESENCE OF METAL CHIPS. THE AC WAS REMOVED FROM SERVICE.  MAIN WHEEL ASSY WAS REMOVED AND THE FOLLOWING DAMAGES WERE O	BSERVED: BOTH WHEEL BRGS WERE DISINTEGRATED ALONG WITH DAMAGE TO THE WHEEL HUB AND BRAKE KEYS, BRAKE DISKS, WHEEL NUT AN	D MLG AXLE.  FOLLOWING OBSERVATIONS WERE NOTICED DURING THE INITIAL INVESTIGATION: THE WHEEL NUT WAS IN PLACE AND SECURE	D WITH THE TWO LOCK BOLTS. THERE WAS NO LOCKING WIRE OBSERVED. THE WHEEL HUB CAP WAS MISSING BUT (2) OF THE (3) HOLDING 	SCREWS WERE STILL FIXED TO THE WHEEL FRAME. INSP OF THE INNER BEARING CLEARLY INDICATES THE CORRECT PN L713049*2-629. PN	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080521		SO  	2008	5	21	CA080222002      	2	20080221	G	8530	655475A	CYLINDER        								CONT  	O470  	O470*       	17026	SO  					ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FACTORY NEW CYLINDER ASSY RECEIVED FROM MFG WITH INCORRECT EXHAUST AND INTAKE VALVE GUIDES INSTALLED. INTAKE GUIDE	 P/N 655166 AND EXHAUST GUIDE P/N 636242 ARE REQUIRED IAW SB 04-11. UNABLE TO DETERMINE P/N OF GUIDES ACTUALLY INSTALLED	 IN NEW CYLINDER. SUSPECT INTAKE AND EXHAUST VALVE GUIDES INSTALLED IN WRONG LOCATIONS. CYLINDER SUBJECT TO WARRANTY THR	OUGH MFG. (TC NR 20080222002)								3	O			E273				 
	20080521		EU  	2008	5	21	CA080222003      	1	20080220	G	2897		WIRE HARNESS    			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	BOOST PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING OF A FUEL BOOST PUMP SNAG, MAINT DISCOVERED THE RELATED WIRING HARNESS HAD BEEN DAMAGED DUE	 TO CHAFING ON THE EDGE OF THE FIXED CARGO LINER PANEL AT THE AFT SIDE OF THE 91VU SHELF. THE CARGO LINER PANEL IS PART 	OF THE FIRST AIR CLASS C INTERIOR, STC SA22-122 NOT AN OEM COMPONENT. THE WIRING WAS REPAIRED AND CLEARANCE ADJUSTED TO 	PRECLUDE FURTHER ISSUE. THE COMPANY HAS INITIATED A FLEET CAMPAIGN TO INSPECT FOR SIMILAR ANOMALIES. (TC NR 20080222003)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20080521		NM  	2008	5	21	CA080222004      	1	20080215	G	2497	284T3501315	ELECTRICAL BOX  			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					CARGO HANDLING	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) WIRING DAMAGE FOUND IN FWD CARGO HANDLING ACCESS PANEL P35 DURING THE (XM) VISIT.  57 WIRES BURN, 3 WIRES MAJOR DA	MAGED, 1 FOUND CUT, FOUND LUG DAMAGE ON TERMINAL A1,B1,C1 OF RELAY K245 (P35).  FOUND WIRES DAMAGE ON CONNECTOR D5886P. 	 AFTER AN INVESTIGATION , FOUND CARGO PDU P/N 43104-14 AT POSITION 7R FAULTY (FOUND INTERNAL WIRES BURNED) ROOT CAUSE , 	THE FAULTY PDU CAUSED A SHORT IN THE P35 PANEL DAMAGING WIRES AND RELAY (TC NR 20080222004)			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
	20080521		EA  	2008	5	21	CA080222005      	1	20080222	G	3234	3620377	O-RING          			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	R2800CA3    	52026	NE  	HAMSTD	43E	43E60       	NE  	MLG	DETERIORATED    	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) O-RING LOCATED BEHIND INDICATED SCREW IN DIAGRAM, DETERIORATED CAUSING A HYDRAULIC LEAK. THERE ARE (6) LOCATIONS O	N THE AC THAT INCORPORATES THIS VALVE. THIS LEAK WAS DISCOVERED ON THE NLG SELECTOR VALVE LOCATED UNDER CO-PILOTS SIDE. 	 (TC NR 20080222005)				2	H	7	2 	4R	4	R	RT	A14EA   	5E8	6	C	P871	 
	20080530		EA  	2008	5	30	CA080222006      	1	20080219	G	2910		LINE            			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					HYD SYSTEM	PUNCTURED       	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			K	A		FLUID LOSS                	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			CA			17426								HYDRAULIC PUMP SUPPLY LINE IN THE COCKPIT DEVELOPED A PIN-HOLE FAILURE IN THE WALL OF THE TUBING.  THE HYDRAULIC FLUID A	T A PRESSURE OF 1650 PSI WAS RELEASED INTO THE CABIN, ATOMIZING AS IT DID SO, THE DIRECTION OF THE SPRAY WAS DIRECTLY AT	 THE PILOT.  THE POWER WIRE FOR THE HYDRAULIC PUMP ARCED AGAINST THE TUBING, IGNITING THE HYDRAULIC MIST AND IGNITING A 	FLASH FIRE.  THE FIREBALL WAS UNABLE TO SUSTAIN ITSELF AND DID NOT IGNITE THE AIRCRAFT ALTHOUGH THE PILOT WAS SET ON FIR	E, SUFFERED 1ST AND 2ND DEGREE BURNS TO HIS FACE AND RIGHT HAND.  THE PASSENGER DID NOT RECEIVE ANY INJURIES AND WAS INS	TRUMENTAL IN EXTINGUISHING THE PILOT,  THE SYSTEM HAS BEEN IN THE ACFT SINCE MANUFACTURING, BUT DOES NOT MATCH ROUTING S	1	H	7	1 	3T	4	T		A806    	E4EA				 
	20080603		EU  	2008	6	3	CA080222007      	1	20080215	G	3211	201660001010	BOLT            			AIRBUS	A321  	A321211     	3930370	EU  	CFMINT	CFM56 	CFM565B3P   	13006	NE  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20789								(CAN) CORRODED FAIL SAFE BOLTS THAT SECURE MAIN LANDING GEAR SIDE STAY ATTACH PINS TO UPPER AND LOWER CARDAN PINS. BOLTS	 ARE ITEMS 290 AND 296 IN A321 IPC 32-11-18-02E. ITEM 290 IS AN AN6-56A AND ITEM 295 IS AN AN6-62. THE LOWER BOLT ITEM 2	95 IS HEAVILY CORRODED.  (TC NR 20080222007)				2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
	20080603		NM  	2008	6	3	CA080222008      	1	20080222	G	2710	19004209401	CONTROL CABLE   			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					AILERON	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 190-04212-401, P/N 190-04209-401	, RT P/N 190 -05551-401, P/N 190-04209-401) WORN AND WITH SEVERAL WIRES BROKEN AT FAIRLEAD, LOCATED AT LT AND RT WINGS R	IB 4A WS -3025.80 MIL. SPAR 2 IN MLG WHEEL WELL.  THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/	N PE49068-501) MOUNTED ON THE FAIRLEAD. MFG WILL COME UP WITH AN SB END OF MARCH (TC NR 20080222008)			2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20080530		NM  	2008	5	30	CA080222009      	1	20080221	G	2710	17005825401	CONTROL CABLE   			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401, P/N 170-05826-401, RT P	/N 170-05827-401, P/N 170-05828-401) WORN AND WITH WIRES BROKEN AT FAIRLEADS, LOCATED AT LT AND RT WINGS INB OF THE RIB 	17.  THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROMMETS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD.  EMBR	AER WILL ISSUE A SB END OF MARCH (TC# 20080222009)			2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20080603		NM  	2008	6	3	CA080222010      	1	20080221	G	5315		FLOORBEAM       			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272.0 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18 AND ON FLOORBEAM 	LOCATED AT Y = -272.0 AND Z = -490.0 AND ON FRAME NR 14 AT Y = -337.0 AND Z = -490.0 ALSO (3) SILL PLATES CORRODED BEYON	D LIMITS. CORROSION WAS ALSO FOUND ON FRAME 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT FLOOR STRUCTUR	E. REFERENCE: PICTURE, AFT FUSELAGE, FORWARD FUSELAGE DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURAL	 REPAIR MANUAL) , ALL AFFECTED PARTS WHERE REPLACED OR REPAIRED AS MFG INSTRUCTION. THE ROOT CAUSE SEEMS TO BE THE LACK 	OF FLOOR PROTECTION UNDER THE FWD AND AFT GALLEYS. (TC NR 20080222010)	2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
200805141    	20080514	1    	NE  	2008	5	14	CA080225001      	2	20080212	G	7321	78639114	HMU             			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW121 	PW121       	52124	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA				1578 							(CAN) AFTER CONFIGURING FOR LANDING (FLAP 35, CONDITION LEVERS MAX) CO-PILOT COMMENTED THAT HE HAD NOTICED A SIGNIFICANT	 POWER LOSS ON THE NR 2 ENG AND POINTED OUT A REDUCTION IN TORQUE. THE NR 2 TORQUE GAUGE WENT TO 0 PERCENT, CREW DECIDED	 TO SHUTDOWN THE NR 2 ENG. FUNCTIONAL CHECK OF THE ENG WAS CARRIED OUT BY MAINT STAFF. THE ENG WAS ABLE TO BE STARTED WI	TH VERY SLOW ACCELERATION REPORTED AND LOW IDLE OF 60 PERCENT ONLY ACHIEVED - NP 168, FUEL FLOW 160, ITT 550 DEGREES. FO	LLOWING COMMUNICATION OF THIS DATA WITH THE ENG MFG, IT WAS DETERMINED THAT THE MOST LIKELY CAUSE OF THE DEFECT WAS HYDR	O MECHANICAL FCU (HMU) FUEL SCHEDULE. THE HMU AND FUEL PUMP ASSY WAS REPLACED IAW THE AC MM 72-01-40 AND SUBSEQUENTLY GR	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20080521		NM  	2008	5	21	CA080225002      	1	20080122	G	3260	83260024101	ROLLER          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG	SEIZED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			8236 								(CAN) AFTER RETRACTING LANDING GEAR ON TAKEOFF, NOSE GEAR AMBER DOOR LIGHT REMAINED ILLUMINATED. CONDUCTED CHECKS IAW QR	H (LANDING GEAR DOOR MALFUNCTIONS) UNABLE TO RECTIFY PROBLEM, RETURNED TO BASE WITH LANDING GEAR EXTENDED FOR NORMAL APP	ROACH AND LANDING. INSP OF THE AC BY MAINT AFTER RETURN OF THE AC TO THE TERMINAL DETERMINED THAT THE NLG DOORS WERE CLO	SED BUT THE CORRESPONDING INDICATION WAS OF AN UNSAFE CONDITION. FUNCTIONAL CHECK OF THE NLG DOORS AND INDICATING SYS CA	RRIED OUT. THE ALTERNATE RELEASE ROLLER TRIPPING ARM BRG WAS DISCOVERED TO BE SEIZED AND THE CLEARANCE BETWEEN THE ROLLE	R AND OB TOGGLE LINK OUT OF ADJUSTMENT. ROLLER PN 83260024-101 WAS REPLACED AND THE ALTERNATE RELEASE CABLE ADJUSTED IAW	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080521		NM  	2008	5	21	CA080225003      	1	20080219	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	NR 2 ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NR 2 EDP FAILED IN FLIGHT WITH A BANG FOLLOWED SHORTLY AFTER BY NR1 HYD FLUID HOT CAUTION LIGHT ILLUMINATING, FOLL	OWED BY THE 1 HYD ISO VALVE TO CLOSING. THE AC MADE A FLAPLESS EMERGENCY LANDING. INITIAL INVESTIGATION BY MAINT FOUND T	HAT THE NR2 HYD SYS HAD LOST ITS FLUID, THE NR2 EDP PORT CAP HAD SEPARATED FROM THE EDP PUMP BODY, THE PTU WAS INOPERATI	VE (OVERSPEED AND EVIDENCE OF OVERHEAT), PTU FLEX HOSES EVIDENCE OF OVERHEAT.  MAINT ACTIONS: REPLACEMENT OF NR1 AND NR2	 EDP`S, PTU, PTU SELECTOR VALVE, NR1 AND NR2 HYDR SYS FILTERS, REPLACEMENT OF PTU FLEX HOSES, FLUSHING/BLEEDING OF THE A	PPLICABLE HYDR LINES. (TC NR 20080225003)	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE	 
	20080521		EA  	2008	5	21	CA080225005      	1	20080222	G	2421	731579	SHAFT           			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A2     	30067	NE  					IDG	BROKEN          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) 3 MINUTES AFTER TAKEOFF, GENERATOR FAILED, AC RETURNED TO BASE.  GENERATOR REMOVED, FOUND BROKEN SHAFT INSIDE THE 	IDG (NOT THE MAIN SHAFT).   IT BROKE, MELTED THE COVER AND CAME OUT (TC NR 20080225005)					2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
	20080603		GL  	2008	6	3	CA080225006      	3	20080221	G	6114		HUB             	HARTZL      	HCE4A3D     	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			CA			663  								(CAN) PROPELLER REMOVED DUE TO EXCESSIVE GREASE LEAK FROM BLADE CLAMPS. (TC NR 20080225006)						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080603			2008	6	3	CA080225007      	4	20080221	G	2330	6009580001	MONITOR         			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					CABIN	MALFUNCTIONED   	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) CREW REPORTED A BURNING SMELL IN THE CABIN JUST BEFORE LANDING. IN-FLIGHT ENTERTAINMENT WAS SELECTED OFF AND SMELL	 DISSIPATED. MAINTENANCE DETERMINED THAT THE SMELL WAS COMING FROM THE NR 7 MONITOR. (TC NR 20080225007)					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
	20081230		CE  	2008	12	30	CA080225009      	1	20080221	G	2730	0510105125	CONTROL CABLE   			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140, WHERE CABLE RIDES ON THE PHENOLIC BLOCK.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
	20081230		CE  	2008	12	30	CA080225010      	1	20080204	G	2730	0510105125	CONTROL CABLE   			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA140 AT PHENOLIC BLOCK.						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
	20081230		CE  	2008	12	30	CA080225011      	1	20080211	G	2730	0510105125	CONTROL CABLE   			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LWR ELEVATOR CABLE FRAYED AT BULKHEAD STA 140 AT THE PHENOLIC BLOCK.						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
	20080530		EA  	2008	5	30	CA080225012      	1	20080222	G	5343	19064104	FITTING         			CNDAIR	CL604 	CL604       	1900301	EA  										MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4481 								DURING LANDING GEAR 96 MONTH DETAIL INSPECTION HEAVY PITTING CAUSED BY CORROSION.  FOUND ON MAIN LANDING GEAR MAIN FITTI	NG TRAILING ARM ATTACHMENT INBOARD LUG BUSHING AREA AND BORE, RESULTING CONSIDEABLE AMOUNT OF MATERIAL FROM AFFECTED LOC	ATION, LEADING MAIN FITTINGTO REDUCED LOAD CARRYING CAPACITY				2	L	7	2 	4F			RT	A21EA   					 
	20090102		CE  	2009	1	2	CA080225013      	1	20080220	G	3230	26410148	SPRING          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3808 	3808 							(CAN) ON JACKING THE ACFT, THE RT MAIN SPRING WAS FOUND TO BE LOOSE IN THE CTR SPRING TO SUCH AN EXTENT THAT MAINWHEEL C	OULD BE MOVED BACK AND FORTH .1250 ON AN INCH BEFORE THE REMOVAL BEGAN. UPON DISASSEMBLY THE MAIN SPRING WAS REMOVED BY 	HAND FROM THE CTR SPRING WITHOUT ANY PULLERS BEING USED. AMOUNT OF PLAY WHILE THE MAIN SPRING WAS STILL ASSEMBLED TO THE	 CTR SPRING SEEMED TO BE EXCESSIVE AND WAS NOT SOMETHING THAT WE HAD EXPERIENCED IN THE PAST.  AFTER REMOVAL OF THE MAIN	 SPRING THE CTR SPRING WAS FOUND TO BE WITHIN LIMITS ON THE LT SIDE BUT OUT OF LIMITS ON THE RT SIDE. MAXIMUM DIAMETER M	EASURED AT THE RT CENTER SPRING WAS 2.807 INCH, THE LIMIT IN THE MM IS 2.794 INCH. DURING A SEARCH OF THE ACFT RECORDS N	1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20080530		NM  	2008	5	30	CA080225014      	1	20080222	G	2750		CLUTCH          			BOEING	737   	737200      	1384453	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					TE FLAP	DISENGAGED      	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											DEPARTING YOW THE AIRCRAFT EXHIBITED AN UNCOMMANDED ROLL TO THE LEFT REQUIRING 2-3 UNITS OF RUDDER TRIM TO CORRECT.  THE	 CREW OBSERVED NO ASSYMMETRY INDICATION IN THE FLIGHT DECK BUT IT WAS VISUALLY CONFIRMED THAT THE RIGHT INBOARD AFT FLAP	 WAS PARTIALLY EXTENDED.  MAINTENANCE FOUND THE INBOARD TRAILING EDGE FLAP CLUTCH DISENGAGED.  THE MECHANISM WAS INSPECT	ED, THE CLUTCH BELLCRANK RESET AND THE SYSTEM FUNCTION CHECKED SERVICEABLE. (TC# 20080225014)			2	L	7	2 	4F	4	F		A16WE   	E2EA				 
200805141    	20080514	1    		2008	5	14	CA080225015      	2	20080225	G	7414		BEARING         		106006169   															MAGNETO	EXCESS PLAY     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			930  								(CAN) MAG WAS RECEIVED FOR A 500 HR INSP.  BEFORE THE MAG WAS DISASSEMBLED THE ROTATING MAGNET (ROTOR) WAS SPUN TO CHECK	 FOR BRG ROUGHNESS OR END PLAY. SOME SIDE PLAY WAS NOTICED (MFG DOES NOT ALLOW ANY) AND THE END PLAY WAS MEASURED AT .00	3 INCH. THE BRGS WERE INSPECTED, SHIMS WERE ADDED, THE REST OF THE 500 HOUR INSP WAS CARRIED OUT, AND THE MAG WAS RETURN	ED TO SERVICE. THE MAG HAD 473.8 HRS SINCE ITS PREVIOUS 500 HR INSP. (TC NR 20080225015)																 
	20081104		EA  	2008	11	4	CA080226001      	2	20080222	G	7322		THROTTLE BODY   			PIPER 	PA18  	PA18A135    	7101822	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	CARBURETOR	LOOSE           	W				K				NONE                    				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		IN	INSP/MAINT     	1			CA				279  							(CAN) DURING GROUND RUN UP PRIOR TO ANNUAL INSPECTION, ENGINE OBTAINED A MAXIMUM RPM OF 1900. INSPECTION FOUND CARBURETO	R THROTTLE BODY SCREWS LOOSE AND FUEL STAINS ON BOWL. CARBURETOR REMOVED AND FORWARDED TO REPAIR FACILITY. (TC N 2008022	6001)				1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
	20090102		CE  	2009	1	2	CA080226002      	1	20080219	G	3245	0923150	TUBE            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	NLG TIRE	DESTROYED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA											(CAN) NOSE WHEEL BLEW OUT ON LANDING. TIRE AND RIM WERE INSPECTED FOR ANOMALIES WHICH WOULD CAUSE A BLOW OUT. NONE FOUND	. THE TUBE IS SUSPECTED TO BE THE CAUSE OF CONCERN. ALSO UPON LANDING WITH A FLAT THE FENDER WAS DESTROYED AND THE TAXI 	LIGHT NEEDED TO BE REPLACED.				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
	20081104		EU  	2008	11	4	CA080226003      	1	20080224	G	3110		ANNUNCIATOR     			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  						MALFUNCTIONED   	W				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			CA			1403 								(CAN) ON A ROUTINE CHECK FOLLOWING START, THE ANNUNCIATOR LIGHT FOR GOV FAILURE (RED) FAILED TO ILLUMINATE WHEN THE ENGI	NE GOV SWITCH WAS MOVED FROM AUTO TO MANUAL. OTHER FUNCTIONS ASSOCIATED WITH MOVING TO MANUAL (SOLENOID, VEMD FAILURE CO	DES) OPERATED NORMALLY. THE WARNING LIGHT ILLUMINATED DURING THE ANNUNCIATOR (ALL LIGHTS) PUSH TO TEST. THE ANNUNCIATOR 	PANEL WAS REPLACED WITH THE REPLACMENT UNIT OPERATING NORMALLY. (TC NR 20080226003)			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20080521		SW  	2008	5	21	CA080226004      	1	20080222	G	2420	ALX8403	ALTERNATOR      			GULSTM	112   	112         	0144701	SW  	LYC   	O360  	IO360C1D6   	41514	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	ELECTRICAL	UNSERVICEABLE   	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) ALTERNATOR FAILED, CAUSING MAIN BATTERY TO DRAIN RESULTING IN COMMUNICATION DIFFICULTIES WHICH CAUSED PILOT TO CON	TACT TOWER BY CELL PHONE FOR CLEARANCE TO LAND. NEW UPGRADED ALTERNATOR INSTALLED PN ALX8521R (TC NR 20080226004)					1	L	7	1 	3O	3	O		A12SO   	1E10	5	C	P9EA	 
	20080521		EU  	2008	5	21	CA080227001      	1	20080131	G	2121		BEARING         			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F26 	NE  	BLOWER MOTOR	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				74   							(CAN) CABIN CREW NOTED AN ABNORMAL ODOR IN THE CABIN AND ADVISED THE COCKPIT CREW. IT WAS DECIDED TO LAND AT THE CLOSEST	 AIRPORT AS A PRECAUTION. PRIOR TO LANDING THERE WERE SEVERAL WISPS OF SMOKE OBSERVED IN THE FLOOR/SIDEWALL AREA. THE AC	 LANDED UNEVENTFUL. MAINT DETERMINED THAT THE SMELL WAS CAUSED BY A FAILED RECIRCULATION BLOWER MOTOR. IT IS BELIEVED TH	AT A FAILED BEARING IN THE ASSEMBLY IS THE CAUSE OF THE FAULT. (TC NR 20080227001)			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
	20080521		CE  	2008	5	21	CA080227002      	1	20080226	G	5210	SL51043	SPINDLE         			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					MAIN CABIN DOOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1583 								(CAN) CREW SNAGGED MAIN CABIN DOOR OUTER HANDLE AS BEING SLOPPY. DISASSEMBLED DOOR HANDLE AND FOUND OUTER DOOR HANDLE SP	INDLE TO BE EXESSIVELY WORN WHERE PIN FOR ATTACHING OUTER HANDLE FITS. MEASURED REMAINING MATERIAL AND FOUND TO BE 0.028	 INCH ON ONE SIDE AND 0.031 INCH ON THE OTHER. REMOVED AND REPLACED SPINDLE WITH NEW AS IT WAS FELT THAT THIS PIECE WOUL	D FAIL SOON AND ALLOW THE HANDLE (OUTER) TO COME OFF AND POSSIBLY BE INGESTED BY THE LT ENGINE. (TC NR 20080227002)			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20080521		EA  	2008	5	21	CA080227003      	1	20080219	G	7931		OIL SYSTEM      			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					ENGINE	LOW PRESSURE    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LOW OIL PRESS WARNING ON NR 2 ENGINE APPROX 3 MINS AFTER TAKEOFF AT 6000FT MSL ON DEPARTURE CLIMBOUT. AFTER IDENTI	FICATION OF FAULT AND CONFIRMATION THAT THE FAULT WAS NOT AN INDICATION PROBLEM NR 2 ENGINE WAS SHUTDOWN AND SECURED. RE	TURNED SAFELY.  THE CAUSE HAS YET TO BE DETERMINED. (TC NR 20080227003)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081104		SW  	2008	11	4	CA080227004      	1	20080201	G	5311	20631308015S	FRAME           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE UPPER RT ATTACH POINT ON THE AIRFRAME SIDE CRACKED ON THE FRAME RING ONLY.  PART REPLACED WITH NEW FROM MFG. (	TC NR 20080227004)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20080521		SW  	2008	5	21	CA080227005      	1	20080131	G	5320	206031322003	STIFFENER       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT STIFFENER UNDER THE OIL COOLER HANGER BEARING CRACKED FROM FWD ANCHOR NUT WHOLE. REPLACED WITH NEW PART. (TC NR	 20080227005)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20080521		NE  	2008	5	21	CA080227006      	2	20080122	G	7414	10885435	CAM             			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				320  							(CAN) DURING A 500 HR MAG INSPECTION IT WAS NOTED THE CAM WAS TIGHT TO SHAFT, COULD NOT BE REMOVED BY HAND. CAM WAS TAPP	ED OFF SHAFT WITH BRASS PUNCH AND HAMMER. WHEN CAM CAME OFF SHAFT IT BROKE INTO 4 PIECES. (TC NR 20080227006)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080530		GL  	2008	5	30	CA080227007      	2	20080227	G	7230	6898607	BEARING RACE    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	SPALLED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1399 								DURING FLIGHT THE PILOT HAD A CHIP LIGHT INDICATION.  UPON INSPECTION, THE CHIP PLUG HAD LITTLE DEBRIS AND SMUDGE.  THE 	CHIP WAS CLEANED, REINSTALLED AND FURTHER GROUND RUNS WHERE CARRIED OUT PRIOR TO FLIGHT.  NO FURTHER ISSUES WERE NOTED A	ND THE FLIGHT CONTINUED.  A FEW HOURS LATER ANOTHER CHIP LIGHT HAD ILLUMINATED.  THE AIRCRAFT WAS RETURNED TO THE BASE V	IA TRUCK AND TRAILER.  FURTHER INVESTIGATION REVEALED FWD CHIP PLUG HAD METAL EVIDENT ON THE PLUG.  THE COMPRESSOR WAS R	EMOVED AND THE NR 1 BEARING INNER RACE SHOWED EVIDENCE OF SPALLING.  THE GEARBOX ALSO HAD AN ISSUE ADDRESSED BY ANOTHER 	SDR RELATED TO THIS AIRCRAFT.  WILL SUBMIT PICTURES WHEN THEY ARE AVAILABLE. (TC# 20080227007)	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20080530		SW  	2008	5	30	CA080227008      	1	20080227	G	6320	23034787	BEARING RACE    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GEARBOX	SPALLED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			6794 								(CAN) METAL WAS FOUND ON ENGINE LOWER CHIP PLUG.  THE 2 1/2 BEARING IN THE GEARBOX WAS REMOVED AND FOUND THE SPALLING ON	 THE OUTER RACE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20080603		NM  	2008	6	3	CA080228001      	1	20080119	G	3230	C247300016	UPLOCK          			AIRBUS	A319  	A319114     	3930350	NM  	GE    	CFM56 	CFM565A     	13802	NE  					NLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			29460								AFTER TAKEOFF, THE CREW COULD NOT RETRACT THE NOSE GEAR.  THE GEAR WAS RECYCLED WITH NO SUCCESS.  THE CREW RETURNED TO L	AND AT DEPARTURE AIRPORT.  THE NLG UPLOCK ASSEMBLY WAS REPLACED AND A LANDING GEAR SWING CARRIED OUT.  DESCRIPTION/ROOT 	CAUSE, THE UNIT WAS SENT FOR REPAIR WITH THE REQUEST FOR A TEARDOWN REPORT.  THE UNIT WAS PRE-TESTED AND FAILED THE LOCK	ING TEST.  THE LOCK MECHANISM INSIDE THE UNIT FAILED TO LOCK THE HOOK.  THE REPAIR FACILITY CONCLUDED THAT THE DRIED GRE	ASE CAUSED THE LOCKING MECHANISM TO HANG UP AND PREVENTED THE HOOK FROM LOCKING THE NOSE LANDING GEAR.  THE WEAR TO THE 	UNIT WAS NORMAL AND NO OTHER MECHANICAL DIFFICULTIES WERE OBSERVED.  AT TIME OF THIS REPORT THE REPAIR ORGANIZATION WAS 	2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
200805141    	20080514	1    	NM  	2008	5	14	CA080228002      	1	20080222	G	5315	17003264001	FLOORBEAM       			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18 . ALSO (3) SILL PLA	TES CORRODED BEYOND LIMITS. CORROSION WAS ALSO FOUND ON FR 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT AT	 FLOOR STRUCTURE. REFERENCE: PICTURE NR AFT FUSELAGE FRAME 87, 89, 90 NR FLOORBEAM FRAME 18 POSSIBLE ROOT CAUSE: FLOOR P	ROTECTION UNDERNEATH THE GALLEY NOT ADEQUATE. (TC NR 20080228002)			2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20080521		NM  	2008	5	21	CA080228003      	1	20080215	G	2150	18279018	ACM             			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  		FAILED          	W				G	A			O2 MASK DEPLOYED        	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			12421								(CAN) DURING CLIMB, CREW NOTICED A SMELL OF SMOKE IN THE FLIGHT DECK. CREW DONNED OXYGEN MASKS AND COMPLETED THE (OXYGEN	 DRILL). UNSCHEDULED LANDING COMPLETED. ENGINEERING ONSITE INVESTIGATION CONFIRMED FAILURE OF THE AFT AIR CYCLE MACHINE 	(ACM). THE AFT ACM WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. ACM HAS BEEN DISPATCHED T	O THE MFG FOR REPAIR/OVERHAUL WITH A REQUEST TO PROVIDE A STRIP REPORT. (TC NR 20080228003)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080521		NM  	2008	5	21	CA080228004      	1	20080219	G	3230	483025	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			93   								(CAN) AN OPERATOR COMPLETED AN EMERGENCY LANDING DUE TO NLG DOOR OPEN INDICATION AFTER SELECTING GEAR UP. UNSCHEDULED LA	NDING, CREW FOLLOWED THEIR QRH, PERFORMED ALTERNATE GEAR EXTENSION. NLG SOLENOID SEQUENCE VALVE REPLACED. (TC NT 2008022	8004)				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE	 
	20081104		SW  	2008	11	4	CA080228007      	1	20080124	G	3246	206050297105	SKID            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8330 								(CAN) UPON INSTALLATION OF GROUND HANDLING WHEELS IT WAS DISCOVERED THAT THE MOUNTING LUGS ON THE FWD LT SIDE WAS DETACH	ED AND LOOSE DUE TO LARGE PERFORATION (HOLE) IN THE ATTACHMENT AREA. FURTHER VISUAL INSPECTION REVEALED CIRCUMFERENTIAL 	CRACK APPROXIMATELY (3) QUARTERS AROUND THE SKID TUBE, SLIGHTLY FWD OF THE SADDLE LOCATION AND RUNNING AROUND THE BOTTOM	 PORTION OF THE TUBE. EXTENSIVE CORROSION ALSO DETECTED IN AND AROUND AFFECTED AREA. SKID TUBE REPLACED WITH NEW UNIT. (	TC NR 20080228007)		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20080521		NM  	2008	5	21	CA080228009      	1	20080225	G	3260		SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	MLG DOWNLOCK	FAULTED         	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) AFTER DEPARTURE, AN ABNORMAL GEAR INDICATION WAS OBSERVED. DECISION TO CONTINUE TO NEXT BASE IAW MCC AND OCM. ON A	RRIVAL, ALTERNATE GEAR EXTENSION, ACCORDING PROCEDURE PERFORMED. NORMAL INDICATION (3 GREEN) ON MAIN AND ALTERNATE SYS. 	DURING FINAL: GEAR UNSAFE-INDICATION ON MAIN INDICATION AGAIN, NORMAL INDICATION ON ALTERNATE SYS. UNEVENTFUL LANDING AN	D NORMAL DISEMBARKATION ON THE RUNWAY FOLLOWED. PSEU FAULT CODES AS FOLLOWS: LEG 00: LGDLK 1 PROX SENSOR OPEN, LGDLK 1 P	ROX SENSOR SHORT, PSEU CHANNEL D FAIL CHANNEL INOP, LGDLK1 UNREASONABLE NEAR, NLGLK2 UNREASONABLE NEAR, NLGLK1 UNREASONA	BLE NEAR, NGDRCL UNREASONABLE NEAR, NGWOFW2 UNREASONABLE NEAR NGWOFW1 UNREASONABLE NEAR, NGDN2 UNREASONABLE FAR, NGDN1 U	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE	 
	20080521		NM  	2008	5	21	CA080228010      	1	20080225	G	2750	734386B	TORQUE TUBE     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAPS	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) A/C WAS ON APPROACH INTO AIRPORT, THE FLAPS WERE LOWERED TO 15 DEG WHEN THE (FLAP DRIVE CAUTION LIGHT) CAME ON. TH	E A/C LANDED WITHOUT INCIDENT. MAINT INSP REVEALED THAT THE LT OB TORQUE TUBE WAS SHEARED OFF. AFTER FURTHER INSP, IT WA	S DETERMINED THAT THE TORQUE TUBE WAS SHEARED OFF BY CLAMP INSTALLED ON A DRAIN LINE THAT HAD BEEN CHAFING. THE TORQUE T	UBE WAS REPLACED, THE TORQUE SENSOR RIGGED AND THE FLAPS WERE FUNCTION CHECKED SERVICEABLE. (TC NR 20080228010)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080602		SW  	2008	6	2	CA080228011      	1	20080227	G	3230	2752003042	BELLCRANK       			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING MAINTENANCE GEAR RETRACTION A "CLICKING" NOISE WAS HEARD FROM THE NOSE GEAR WHEELWELL.  THE ROLLER BEARING ON THE	 RT NOSE GEAR BELLCRANK WAS BROKEN AND ONLY THE INNER RACE REMAINED ON THE BOLT. THE BELLCRANK WAS REPLACED, GEARSWINGS 	CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE (TC NR 20080228011)				2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE	 
	20080602		SW  	2008	6	2	CA080228012      	1	20080220	G	3222	MS171536	PIN             	FRCHLD      		SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RH TORQUE KNEE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											PIVOT PIN FOR RT MAIN GEAR TORQUE KNEE WAS PROTRUDING FROM THE TORQUE KNEE.  SPRING PIN REMOVED AND INSPECTED.  NO DAMAG	E FOUND.  NEW SPRING PIN INSTALLED.  NO FURTHER PROBLEMS SINCE REPLACEMENT OF SPRING PIN (TC NR 20080228012)					2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE	 
	20080602		EA  	2008	6	2	CA080229001      	1	20080218	G	5610	NP1393222	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			10959								FLT NR 6671 - FIRST OFFICER SIDE WINDOW CRACKED ON DESCENT INTO PSP.  WINDOW REPLACED (TC NR 20080229001)						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080602		NE  	2008	6	2	CA080229002      	2	20080221	G	7200	4129T17G04	ACTUATOR        			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF348C1     	30049	NE  					LT ENGINE	CRACKED         	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA											"925 PWM, LT ENG FAILURE ON SHORT FINAL. ON SHORT FINAL (APPROX 1500 FT) CAPT REPORTED LT ENGINE FAILURE.  N1 WENT TO 32	 PERCENT AND EICAS DISPLAYED LT FADEC AND LT BLEED CAUTION ME PERCENT.  CAPT SAW NO OTHER ENGINE RELATED ANOMALIES, IE N	O PROBLEMS WITH FUEL FLOW, ITT, OIL PRESSURE OR WARNINGS.  CVR AND FDR CIRCUIT BREAKERS HAVE BEEN PULLED.  AIRCRAFT VERI	FIED NOT IMPOUNDED BY THE NTSB.  CONTRACT MX INTERROGATE MDC.  MDC REVEALED LH PS3 SENSE LINE, L FMU FAILED AND VG CMD\P	OSN DISAGREE.  MX INSPECT INLET FOR POSSIBLE INGESTION, NO FINDINGS.  EXHAUST AREA LOOKED GOOD AS WELL.  OPENED COWLING 	AND INSPECTED VG ACTUATORS AND AREA.  MX THOROUGHLY INSPECTING AREA.  WE HAVE SENT MM/IPC REFERENCES OF AREAS TO INSPECT	2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
200805141    	20080514	1    	NM  	2008	5	14	CA080229003      	1	20080221	G	3260	864202	PROXIMITY SENSOR			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	INTERMITTENT    	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) GEAR UNSAFE (NOSE GEAR) ILLUMINATED DURING TAXI-IN WITH ASSOCIATED GEAR WARNING HORN. AC WAS STOPPED AND SHUTDOWN,	 EMERGENCY SERVICES REQUESTED FROM TOWER. F/O INSERTED NOSE GEAR LOCK IMMEDIATELY AFTER SHUTDOWN. ENGINEERING INSPECTED 	THE AC AND TOWED IT TO BAY. MAINT CARRIED OUT INDUCTANCE, CONTINUITY AND MEGGER CHECK OF THE NLG DOWNLOCK SENSOR AND NLG	 DRAG STRUT SENSOR. THE NLG DRAG STRUT SENSOR 3261-S10 (WDM REF NR) WAS FOUND TO HAVE VARIABLE INSULATION OF 100 MEGA OH	MS. THE NLG DRAG STRUT SENSOR WAS REPLACED IAW THE AC MM 32-20-11. NLG RETRACTION AND EXTENSION CHECKS/ TESTS CARRIED OU	T IAW AC MM 32-30-00, ALL INDICATIONS CHECKED SERVICEABLE. AC RETURNED TO SERVICE. (TC NR 20080229003)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080521		CE  	2008	5	21	CA080229004      	1	20080228	G	2420		PULLEY          			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ALTERNATOR	SEPARATED       	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA				51   							(CAN) WHILE IN FLIGHT, NR1 ALTERNATOR FAILED,  NR1 ALT AMBER LIGHT CAME ON, ON THE GROUND, INSP REVEALED THAT THE DRIVE 	PULLEY HAD SEPARATED FROM ALTERNATOR, PULLEY FOUND DAMAGED WITH OTHER BROKEN PULLEY PIECES ON THE BUTTOM OF COWLING.  RE	TAINING NUT HAD GONE AWAY. END SHAFT (ARMATURE) WAS NOT SEIZED.  SUSPECT A QC PROBLEM IN THIS CASE. ALTERNATOR REPLACED 	WITH O/H UNIT. (TC NR 20080229004)			1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
	20080521		CE  	2008	5	21	CA080229005      	1	20080229	G	5753	0512128	BRACKET         			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	TE FLAPS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7402 								(CAN) ON PREFLIGHT INSPECTION, PILOT FOUND WHEN FLAPS EXTENDED, LT FLAP HAD NO TENSION, AND COULD BE LIFTED TO THE RETRA	CT POSITION, POTENTIALLY CAUSING DISIMILAR LIFT WHEN ACTIVATED IN FLIGHT.  INSPECTED AREA, AND FOUND LT BRACKET BROKEN A	T F.S. 65.33, IB MOUNTING TABS BROKEN. SIMILAR OCCURANCE  INSPECTED AREA EACH 100 HRS SINCE, NO INDICATION OF CRACKS PRE	VIOUSLY DETECTED.  SUSPECT THAT FAILURE IS IMMEDIATE AS BREAKS LOOK NEW. POORLY DESIGNED PART FOR LOADS THAT ARE IMPOSED	. (TC NR 20080229005)		1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
	20080521			2008	5	21	CA080229007      	4	20080220	G	2565	416T28243	LEVER           			BOEING	767   	76735H      	1385208	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					OVERWING SLIDE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) OVER-WING SLIDE COMPARTMENT DOOR OPENING ACTUATING MECHASIM - LEVER DESCRIPTION: A LEVER THAT JOINS THE FIRING PIN	 CLEVIS OF THE OFF-WING ESCAPE SLIDE COMPARTMENT DOOR OPENING ACTUATOR TO THE ACTUATING ROD IS BEING INSTALLED UPSIDE-DO	WN. THIS APPEARS TO CAUSE THE LEVER TO BIND WITH THE FIRING PIN CLEVIS AND COULD PREVENT NORMAL DOOR OPENING ACTUATION I	N A REAL SITUATION.  IT SEEMS THAT NO SDR WAS RAISED FOR THE PREVIOUS FINDING. LEVER ORIENTATION CORRECTED IAW DIAGRAMS 	SUPPLIED IN THE IPC AS WELL AS THOSE DIAGRAMS INCLUDED WITH THE RIGGING INSTRUCTIONS IN THE AMM. ENGINEERING APPROACHED 	TO ADDRESS A POSSIBLE AMENDMENT TO THE AMM. (TC NR 20080229007)	2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
	20080521		GL  	2008	5	21	CA080229008      	2	20080206	G	7200		ENGINE          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  						VIBRATION       	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) EXCESSIVE ENGINE NOISE AND HIGH VIBRATION FELT BY PILOT AT GROUND IDLE. VERFIED BY ENGINEER. COMPLETE ENGINE REMOV	ED AND SENT FOR INVESTIGATION. WILL FWD REPORT WHEN AVAILABLE. (TC NR 20080229008)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20080521		GL  	2008	5	21	CA080229010      	2	20080227	G	7230		SCROLL          	ALLSN       		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPRESSOR 390.6 SINCE 2000 HOUR INSP.  CRACK LOCATED BY ENGINEER DURING GROUND RUN UP FOLLOWING SCHEDULED INSP. L	OCATED BY AIR LEAK FOUND BY BARE HAND CHECK. CRACK LOCATED SLIGHTLY BELOW SCROLL ARMPIT REINFORCEMENT PATCH AREA, NOT IN	 NORMAL CRACK LOCATION. A SMALL PIECE OF PATCH MATERIAL ALSO FOUND MISSING. COMPRESSOR REMOVED AND SENT FOR REPAIR. (TC 	NR 20080229010)			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20080521		SO  	2008	5	21	CA080229011      	1	20080226	G	8120	4091701	SHAFT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	SHEARED         	W				A				UNSCHED LANDING         				B	R		SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA				3    							(CAN) SHORTLY AFTER TAKEOFF, WHEN SETTING CRUISE POWER, THE LT ENGINE WOULD NOT STAY AT CRUISE POWER.  AFTER A COUPLE OF	 ADJUSTMENTS THE POWER DROPPED FROM 31IN TO AS LOW AS 12IN OF MANIFOLD PRESSURE. THE AIRCRAFT RETURNED FOR LANDING. MAIN	T FOUND THE SHAFT THAT CONNECTS THE EXHAUST AND INTAKE TURBINE WHEELS ON THE TURBOCHARGER WAS BROKEN AT THE EXHAUST TURB	INE WHEEL. NO REASON COULD BE FOUND FOR THE FAILURE. THE TURBOCHARGER HAD 2.7 HOURS SINCE OVERHAUL. (TC NR 20080229011)			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20080521		EA  	2008	5	21	CA080229012      	2	20080229	G	8530	LW12966	CYLINDER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	UNSERVICEABLE   	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA			150  								(CAN) PILOT HEARD A BANG WHILE IN CRUISE AND NOTICED A LOSS OF POWER. TURNED BACK TO THE NEAREST AIRPORT TO LAND. UPON I	NSPECTION THE AME FOUND THAT THE NR1 INTAKE VALVE WAS MISSING. THE ENGINE WAS REMOVED. WHEN WE REMOVED THE NR1 CYLINDER,	 WE FOUND THAT THE INTAKE VALVE HAD BROKEN OFF AT THE KEEPERS AND A PIECE HAD SHOT OUT THE SIDE OF THE PORT AND LODGED I	TSELF IN THE FINS OF THE NR3 CYLINDER. THERE WAS CONSIDERABLE DAMAGE TO BOTH CYLINDERS. THE REST OF THE VALVE HAS YET TO	 BE SEEN BUT IT IS EXPECTED TO BE FOUND ONCE WE REMOVE THE INDUCTION COVER. (TC NR 20080229012)		1	L	7	1 	3O	3	O		2A13    	E14EA				 
	20080521		NM  	2008	5	21	CA080303001      	1	20080228	G	5315		FLOORBEAM       			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3948 								(CAN) CORROSION FOUND ON FLOORBEAM LOCATED AT Y = 272.0 AND Z = -490.0 JUNCTION WITH FRAMES 16, 17, 18, 19 AND ON FLOORB	EAM LOCATED AT Y = -272.0 AND Z = -490.0 AND ON FRAME NR12 AND 14 , 14 AT Y = -337.0 AND Z = -490.0 ALSO THREE SILL PLAT	ES CORRODED BEYOND LIMITS. CORROSION WAS ALSO FOUND ON FRAME 87, 88, 89 AND 90 UNDER THE AFT RT GALLEY ATTACHMENT POINT 	AT FLOOR STRUCTURE. REFERENCE: PICTURE NR AFT FUSELAGE, FORWARD FUSELAGE DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN 	THE SRM (STRUCTURAL REPAIR MANUAL) , ALL AFFECTED PARTS WHERE REPLACED OR REPAIRED AS IAW MFG INSTRUCTION.  (TC NR 20080	303001)	2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20080602		NM  	2008	6	2	CA080303002      	1	20080228	G	2710	17005825401	CONTROL CABLE   			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					AILERONS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3948 								DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT P/N 170-05825-401) WORN AND WITH WIRES BRO	KEN AT FAIRLEADS, LOCATED AT LT WINGS INB OF THE RIB 17.  THE WORN AREAS AND BROKEN STRANDS ARE LOCATED UNDER NYLON GROM	METS (P/N PE49068-501) MOUNTED ON THE FAIRLEAD.  EMBRAER HAVE BEEN ADVISED (TC NR 20080303002)				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20080603		SO  	2008	6	3	CA080303003      	1	20080229	G	2421		BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ALTERNATOR	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				1093 							IN CRUISE, THE PILOT NOTICED THE RT ALTERNATOR WARNING LIGHT CAME ON.  CHECKED THE BREAKER BUT IT HAD NOT BLOWN.  PULLED	 BREAKER AND LANDED UNEVENTFULLY.  MAINTENANCE INSPECTED THE RT ALTERNATOR AND DISCOVERED THAT THE ALTERNATOR BEARING HA	D SEIZED AND BROKEN THE BELT. (TC NR 20080303003)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081104		SW  	2008	11	4	CA080303004      	1	20080303	G	6510	327211	DISC PACK       			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					T/R DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2562 								(CAN) DISC PAC WAS REMOVED FOR INSPECTION DURING A SCHEDULED 1200 HOUR INSPECTION. CRACKED DISC WAS DISCOVERED DURING DI	SASSEMBLY. ONE DISC OF TEN IN PAC WAS COMPLETELY CRACKED ON BOTH SIDES ON ATTACHEMENT BOLT HOLE SO THAT A PIECE OF THE D	ISC WAS BROKEN AWAY. THE REMAINDER OF THE DISCS WERE CORRODED ON BOTH SIDES OF THE DISC IN THE SAME AREA CLOSEST TO THE 	BOLT HOLE.			1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20080603		GL  	2008	6	3	CA080303005      	2	20080302	G	7322	23034702	FUEL CONTROL    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2936 							AFTER INSTALLING THE FCU, IT WAS NOTED THAT FUEL WAS LEAKING FROM LOWER THROTTLE ARM HOUSING.  FCU WAS REMOVED. (TC NR 2	0080303005)					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20090102		CE  	2009	1	2	CA080303006      	1	20080303	G	3411		STATIC PORT     			BEECH 	23    	B23         	1151240	CE  	LYC   	O360  	O360A2G     	41514	EA  	SNSNCH	76E	M76EMMS     	EA  	RT	OBSTRUCTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2312 	2312 							(CAN) WHILE DOING A PRE-PURCHASE INSP, DISCOVERED A PIECE OF TAPE COVERING THE RT STATIC PORT.						1	L	7	1 	3O	3	O	RT	A1CE    	E286	5	N	P4EA4	 
	20081104		SW  	2008	11	4	CA080303008      	1	20080229	G	6520	476400751	GEARBOX         			BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1D    	41516	EA  					TAIL ROTOR	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3110 	948  							(CAN) UPON WALK AROUND OIL IN GEARBOX LOOKED DIRTY, OIL WAS DRAINED AND METAL WAS FOUND ON MAGNETIC PLUG, TAIL ROTOR GEA	RBOX WAS REMOVED FROM SERVICE AND OH ONE INSTALLED AND ACFT WAS RELEASED. MORE INFO WILL BE POSTED AS THE GEARBOX IS DIS	ASSEMBLED.				1	G	7	1 	3O	3	O		H1      	E279				 
	20080521		EA  	2008	5	21	CA080303009      	2	20080301	G	8550	77517	SUMP            			FOUND 	FBA   	FBA2C1      	3640103	EA  	LYC   	O540  	IO540L1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE OIL SYS	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1100 								(CAN) OIL SUMP WAS REMOVED TO INSPECT SUMP BAFFLE IAW SB. INTERNAL CRACK IN THE SUMP WAS FOUND NEAR ONE OF THE MOUNTING 	LUGS.  IAW THE SB, THE OIL SUMP BAFFLE HAD A LACK OF CLEARANCE AND HAD BEEN RUBBING THE BOTTOM OF THE SUMP. BAFFLE, AND 	SUMP HAD SIGNS OF WEAR. BAFFLE WAS LOOSE, AND HAD (2) BROKEN CONTACT POINTS.  ENGINE REMOVED TO FURTHER DETERMINE CONTAM	INATION AND SERVICEABILITY. (TC NR 20080303009)			1	H	7	1 	3O	3	O	NC	A7EA    	1E4	5	C	P25EA	 
200805141    	20080514	1    		2008	5	14	CA080304001      	4	20080204	G	3418	543036B29	COMPUTER        			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF343A2     	30067	NE  					STALL WARNING	FAULTY          	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) IT TOOK (3) STALL WARNING COMPUTER BEFORE GETTING ONE THAT WAS SERVICEABLE , THEY ALL FAIL THE TEST IAW TEST PROCE	DURE MM PSP601-2 CHAP 27-39-00 P 206 207 NB MFG PRODUCTS (TC NR 20080304001).					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080602		NM  	2008	6	2	CA080304003      	1	20080229	G	2497	IN3311B	DIODE           			BOEING	737   	737522      	138449F	NM  	CFMINT	CFM56 	CFM563C1    	13802	EU  						OPEN            	W				O				OTHER                   				P			NO WARNING INDICATION     			CR	CRUISE         	1			CA											EN ROUTE, AFTER SHUTTING OFF CENTER TANK BOOST PUMPS, LEFT CENTER, LEFT AFT AND RIGHT FORWARD LOW PRESSURE LIGHTS DID NO	T ILLUMINATE.  WINDOW HEAT LIGHTS FOR THE LEFT SIDE WINDOW AND RIGHT FORWARD WINDOW WERE NOT ILLUMINATED.  INITIALLY NO 	MASTER CAUTION, THEN ANTI-ICE MASTER CAUTION.  THERE WAS NO LE DEVICES INDICATION.  ON DOWNWIND FOR LANDING, THE PRESSUR	IZATION WENT FROM AUTO TO STANDBY AND DUMPED PRESSURE.  UPON LOWERING GEAR, NO GREEN LIGHTS.  THE CREW OVERSHOT AND USED	 THE GEAR VIEWERS AND A FLY BY TO DETERMINE THE GEAR STATUS.  AFTER SPEAKING WITH DISPATCH, THE LIGHTS WERE CYCLED THROU	GH BRIGHT/DIM/TEST AND THE GEAR INDICATION RETURNED.  THE AIRCRAFT WAS LANDED WITHOUT FURTHER INCIDENT.  MAINTENANCE WAS	2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
	20080602			2008	6	2	CA080304004      	4	20080303	G	3416	5035PP41	ENCODER         																	ALTIMETER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											WHEN RECEIVED FOUND WITH TIN BETWEEN CASE AND PIN ON CONNECTION RECEPTACLE.																			 
	20080602		EU  	2008	6	2	CA080304005      	1	20080227	G	2910	A3248021101100	LINE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C      	 	GL  					HYD SYSTEM	SPLIT           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											WHILE AIRCRAFT WAS UNDER MAINTENANCE IN THE HANGAR, THE HYDRAULIC RETURN LINE FOR YELLOW SYSTEM ALTERNATE BRAKE FAILED W	ITH A SPLIT IN THE TUBING APPROX 1.5 INCHES IN LENGTH.  AT THE TIME OF THE FAILURE THERE WAS NO HYDRAULIC PRESSURE OR OP	ERATION OF THE SYSTEM.  THE LINE WAS REPLACED AND SYSTEM TESTED SERVICEABLE.  LINE WAS SENT TO AIRBUS FOR ANALYSIS. (TC 	NR 20080304005)			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20080602			2008	6	2	CA080304006      	1	20080304	G	8011		STARTER         																	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											AFTER INSTALLATION TEST FOR FUNCTIONAL START, THE ENGINE LIGHT STAY ON IN THE COCKPIT.  FOUND BY OUR TECHNICIAN THAT THE	 RECEPTACLE PLUG ON THE STARTER PIN B GROUNDED ALL THE TIME. (TC NR 20080304006)																		 
	20080521		EA  	2008	5	21	CA080304007      	2	20080205	G	8500		ENGINE          			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  		MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED INSP, LARGE QUANTITIES OF FERROUS PARTICLES WERE DISCOVERED IN THE PAPER ELEMENT OF THE ENGINE 	OIL FILTER. LARGER PIECES WERE ALSO DISCOVERED IN THE OIL SUCTION SCREEN FINGER. THE AC IS GROUNDED PENDING REPLACEMENT 	OF THE AFFECTED ENGINE. ANALYSIS OF THE FILTER ELEMENT REVEALED FINES AND FLAKES OF CARBON STEEL AMS NR 6440 OR 6444 WHI	CH INDICATES CAMSHAFT AND FOLLOWERS, ALTHOUGH THIS IS NOT AS YET SUBSTANTIATED. THE ENGINE HAS BEEN OPERATED FOR 88.1 HO	URS SINCE OVERHAUL FOR AN IDENTICAL FAULT WHERE THE NR 5 CAM LOBE WAS FOUND WORN BEYOND LIMITS. THE ENGINE IS CURRENTLY 	EN ROUTE FROM INDIA TO THE ORIGINAL ENGINE OVERHAUL SHOP FOR PRECISE FAULT IDENTIFICATION. (TC NR 20080304007)	1	L	7	1 	3O	3	O	RT	A20SO   	E14EA	5	C	P33EA	 
	20080521		WP  	2008	5	21	CA080304009      	2	20080303	G	7321	8978017	FUEL CONTROL    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3518 								(CAN) ENGINE HAD BEEN REMOVED IN RUNNING CONDITION FOR SCHEDULED HOT SECTION/GEARBOX INSP. ENG SENT TO ENGINE SHOP. UPON	 INITIAL START UP FOR THE TEST CELL RUN, THE ENGINE WOULD NOT START. FUEL CAME OUT THE DRAINS AND THE BACK OF THE ENGINE	. THE FUEL PUMP PRESSURE WAS TESTED AND WITHIN LIMITS. THE FUEL CONTROL WAS REMOVED AND THE DRIVE SHAFT TURNED WITH NO R	ESISTANCE, LIKE SOMETHING HAD FAILED INSIDE. THIS FUEL CONTROL IS POST AD 2006-15-08 COMPLIANT AND THE FIRST FAILURE OF 	THIS TYPE SEEN BY THE OPERATOR OR THE ENGINE SHOP ON ONE OF THESE PN.  UNIT TBO IS 7000 HOURS NORMALLY. UNIT HAS BEEN SE	NT FOR REPAIR AND A TEARDOWN REPORT REQUESTED. (TC NR 20080304009)	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
	20080521		EA  	2008	5	21	CA080304010      	1	20080303	G	3230	533407	SELECTOR VALVE  			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF700 	CF7002D2    	30010	NE  					MLG	FAILED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN)  DISC LANDING GEAR WOULD NOT EXTEND. PERFORMED MANUAL/EMERGENCY EXTENTION. ENG HYDR PUMP PRESSURE WAS NORMAL. REMO	VED AND REPLACED  LANDING GEAR SELECTOR VALVE IAW AMM 32-32-10. ADDITIONAL INFORMATION: ATTEMPTED TO EXTEND GEAR 3 TIMES	 BUT FAILED. DID GET A LG DISAGREE WARNING. HAD TO DO A GO AROUND TO GET GEARDOWN. (TC NR 20080304010)				2	L	7	2 	4F	4	F	RT	A21EA   	E7EA				 
	20080521		CE  	2008	5	21	CA080304011      	1	20080118	G	3233	99101399	ACTUATOR        			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG	FAILED          	W				O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			LD	LANDING        	1			CA											(CAN) AIRCRAFT INDICATED (3 GREEN) ON APPROACH, UPON LANDING, NOSE GEAR RETRACTED RESULTING IN AC DAMAGE. UPON ARRIVAL, 	MAINT NOTED GEAR INDICATION REMAINED (3 GREEN) AND AC WAS SITTING ON ITS NOSE. THE AC WAS RAISED AND THE NOSE GEAR WAS P	ULLED INTO THE DOWN AND LOCKED POSITION. INITIAL INSP OF THE GEAR SYS FOUND ALL TO BE IN WORKING ORDER, GEAR SWINGS PERF	ORMED NORMALLY. THE ACTUATOR`S INTEGRAL POSITION INDICATION SWITCH MALFUNCTIONED CAUSING THE HYD SYS PRESSURE TO THE NOS	E GEAR ACTUATOR TO STOP PREMATURELY BEFORE THE NOSE GEAR WAS FULLY EXTENDED AND IN THE OVER CENTER POSITION. (TC NR 2008	0304011)	1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
	20081104		WP  	2008	11	4	CA080304012      	1	20080302	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			289  								(CAN) STARTER - COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BRE	AKING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE	 CASTING IN THE ATTACHED FLANGE IS TOO WEAK.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081104		WP  	2008	11	4	CA080304013      	1	20080228	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14   								(CAN) STARTER -COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BREA	KING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE 	CASTING IN THE ATTACHED FLANGE IS TOO WEAK. (TC NR 20080304013)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081104		WP  	2008	11	4	CA080304014      	1	20080217	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			62   								(CAN) STARTER - COLD WEATHER MACHINES ARE EXPERIENCING SIMILAR DIFFICULTIES WITH STARTER HOUSING (CASING CRACKING OR BRE	AKING OFF) RENDERING THE STARTER U/S AND LEAVING THE MACHINE UNABLE TO START. COLD WEATHER MAY BE A FACTOR OR SIMPLY THE	 CASTING IN THE ATTACHED FLANGE IS TOO WEAK. (TC NR 20080304014)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080602		GL  	2008	6	2	CA080305001      	2	20080303	G	7261		PRESSURE SWITCH 			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C      	 	GL  					ENGINE OIL	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA			47993	1630 							DURING CLIMB AT 18000 FEET, NR 1 ENGINE OIL FILTER CLOGGED LIGHT CAME ON.  AS PER QRH, NR 1 ENGINE WAS SHUT DOWN.  AIRCR	AFT RETURNED TO STATION WITH NO FURTHER PROBLEM.  THE OIL FILTER WAS REPLACED.  NO SIGNIFICANT CONTAMINATION WAS NOTICED	.  THE OIL SYSTEM WAS DRAINED AND SERVICED AS PER MM.  THE OIL DIFFERENTIAL PRESSURE SWITCH WAS REPLACED.  A TEST FLIGHT	 WAS PERFORMED AND THE ENGINE OIL INDICATION SYSTEM WAS NORMAL.  AIRCRAFT WAS RETURN TO SERVICE.			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20080521		CE  	2008	5	21	CA080305002      	1	20080303	G	2121	C4140070102	COOLING FAN     			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	COCKPIT	NOISY           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) ON CLIMBOUT FLIGHT CREW HEARD A LOUD SQUEALING NOISE FROM THE AVIONICS COOLING FAN. IN COLD TEMPERATURES THIS IS T	YPICAL OF THE COOLING FAN AND THE FLIGHT CREW DECIDED TO ALLOW THE FAN TO WARM UP. AFTER A COUPLE MINUTES THE FLIGHT CRE	W DECIDED TO RETURN. APPROX 5 MINUTES LATER DURING VECTORS BACK THE FLIGHT CREW BEGAN TO SMELL A BURNED SMELL IN THE COC	KPIT AND PULLED THE AVIONICS FAN CIRCUIT BREAKER, THE SMELL STOPPED. AT THE TIME, THE FLIGHT CREW ALSO COMMENTED ON SMOK	E LIGHT, SMOKE IN THE COCKPIT. THE FLIGHT WAS CONTINUED AND LANDED WITHOUT FURTHER INCIDENT. MAINT REPLACED THE AVIONICS	 COOLING FAN AND GROUND RUN THE AC WITHOUT ANY ADDITIONAL FAULTS. THE AC WAS RELEASED. (TC NR 20080305002)	1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20081104		NE  	2008	11	4	CA080305003      	2	20080228	G	7200		PIN             			SKRSKY	S92   	S92A        	       	NE  	GE    	CT7TS 	CT78A       	30136	NE  					ENGINE	FOD             	W				O				OTHER                   				C	R		F.O.D.                    	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) ON RETURN FLIGHT AN EPAC (POWER CHECK) WAS ATTEMPTED BUT WOULD NOT COMPLETE (A USUAL CASE IN PARTICULAR ACFT) NRS 	WERE NOTED FOR MAINT STAFF AND ON RETURNING TO BASE ANOTHER EPAC WAS RUN AND COMPLETED. MAINT STAFF WAS NOTIFIED UPON AR	RIVAL AT AIRPORT AND DAMAGE IN ENGINE PARTICLE SEPARATOR WAS NOTICED. SMALL HANDLE. PIN FROM HINGE ASSY FOUND TO HAVE BE	COME DETACHED FROM ASSY AND ENTERED THE ENGINE INTAKE RESULTING IN FOD DAMAGE TO ENGINE.			2	G	7	2 	4U	4	U		R00024BO	E8NE				 
200805141    	20080514	1    	NM  	2008	5	14	CA080305004      	1	20080221	G	3810	14C3308	COUPLER         			BOEING	737   	7378Q8      	13844BX	NM  	CFMINT	CFM56 	CFM567B26US 	 	NE  					POTABLE WATER	CRACKED         	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			Z	S		SIGNIFICANT FAILURE REPORT	AFFECT SYSTEMS            		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, CREW NOTED CABIN ALTITUDE WARNING. UNABLE TO CLOSE OUTFLOW VALVE EITHER ELECTRICALLY OR MANUALLY. E	MERGENCY DESCENT PERFORMED, OXYGEN MASKS DROPPED. OUTFLOW VALVE WOULD CLOSE TO THE .2500 POSITION ON GAUGE. ATTEMPTED TO	 CLOSE VALVE MANUALLY AT 10000FT (OAT +13 DEG C), NO RESPONSE. VALVE CLOSED SUCCESSFULLY AFTER 10 MIN. ON INSP FOUND POR	TABLE WATER LEAKING AT FITTING AND FITTING PARTLY SEPARATED WITH WIGGENS COUPLING OPEN. UPON INSP OF REMOVED COUPLING FO	UND CRACKED. (TC NR 20080305004)		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
	20080521		EU  	2008	5	21	CA080305008      	1	20080225	G	2421	ALU8521R	ALTERNATOR      			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  		FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			1034 								(CAN) PILOT EXPERIENCED A COMPLETE ELECTRICAL FAILURE. SUBSEQUENT INVESTIGATION REVEALED A MELTED INSULATOR ON THE (BATT	) TERMINAL OF THE ALTERNATOR. THE (BATT) WIRE TERMINAL END WAS MELTED AND BROKEN WITH THE FREE END CONTACTING THE ALTERN	ATOR CASE. THE FREE WIRE ENABLED A RAPID DISCHARGE OF THE BATTERY. (TC NR 20080305008)				1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
	20080521		SO  	2008	5	21	CA080305011      	1	20080305	G	2140	CD21252	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2B   	 	NE  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HEATER	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			31   								(CAN) THE PILOT REPORTED THAT THE HEATER DID NOT WORK. MAINT INVESTIGATED AND DETERMINED THAT THE CYCLING SWITCH WAS DEF	ECTIVE AND REPLACED THE SWITCH. THE CREW AGAIN REPORTED THAT THE HEATER DID NOT WORK PROPERLY. MAINT DID MORE TROUBLESHO	OTING AND DETERMINED THAT THE CYCLING SWITCH FUNCTIONED PROPERLY INSIDE A HEATED HANGAR. HOWEVER WHEN LEFT OUTSIDE AT AB	OUT -20 DEGREES CELSIUS THE SECOND SWITCH ALSO FAILED TO FUNCTION PROPERLY. THE HEATER WAS INSTALLED NEW ABOUT 218 HRS A	GO AND THE FIRST CYCLING SWITCH FAILED AFTER 188.3 HRS.  (TC NR 20080305011)		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20080521		NE  	2008	5	21	CA080305012      	2	20080219	G	7320		EEC             			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL, THE ENGINE ELECTRONIC CONTROL DROPPED OFF LINE. THE CREW ADVANCED THE THRUST LEVER TO ACHIEVE	 REQUIRED THRUST, BUT THE POWER LEVEL REMAINED 10 PERCENT LESS THAN THE REQUIRED LEVEL.THE FLIGHT WAS ABORTED AND THE AI	RCRAFT RETURNED TO THE GATE. TROUBLESHOOTING IS ONGOING.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT C	AUSE ONCE ESTABLISHED (TC NR 20080305012)			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20080521		NE  	2008	5	21	CA080305013      	2	20080219	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  						FLAMED OUT      	W				D				RETURN TO BLOCK         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE DEICING THE AC AND PERFORMING SYSTEMS CHECKS, THE ENGINE FLAMED OUT WHEN BROUGHT TO IDLE POWER. THE ENGINE F	LAMED OUT (2) ADDITIONAL TIMES UNDER SIMILAR CIRCUMSTANCES DURING TROUBLESHOOTING. ATTENTION IS FOCUSING ON THE FUEL CON	TROL AND AIRFRAME RIGGING.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 	20080305013)			1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
200805141    	20080514	1    	NE  	2008	5	14	CA080305016      	2	20080301	G	7200		ENGINE          	PWC         	PW545B      	CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  						POWER LOSS      	W				E				ENGINE SHUTDOWN         				R	F	J	PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         	WARNING INDICATION        	DE	DESCENT        	1			CA											(CAN) DESCENDING THROUGH FL370, THE ENGINE ELECTRONIC CONTROL REVERTED TO MANUAL AND ENGINE N2 SPEED REDUCED TO 41 PERCE	NT ASSOCIATED WITH VIBRATION. THE ENGINE DID NOT RESPOND TO THRUST LEVER INPUT AND THE CREW ELECTED TO SHUTDOWN THE ENGI	NE. TROUBLESHOOTING IS ONGOING. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC 	NR 20080305016)			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20081104		WP  	2008	11	4	CA080305017      	1	20080220	G	6710	369A7304	BRACKET         			HUGHES	369   	369A        	4470503	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ROTOR CONTROL	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON REMOVAL OF DUAL CONTROLS, A GENERAL INSPECTION OF THE UNDERSEAT AREA REVEALED A CRACK ON THE BEARING CAP OF THE	 BRACKET ASSEMBLY WHICH IS USED TRANSFERING CONTROL INPUTS FROM CABIN BACK TO THE ROTORS. THE PART WAS REPLACED WITH NO 	INCIDENT.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
	20080521		EU  	2008	5	21	CA080306002      	1	20080304	G	2910	HTE400005	VALVE           			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	HYD SYSTEM	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) THE RT NON RETURN VALVE ASSEMBLY DOWNSTREAM OF THE RT HYDRAULIC PUMP FAILED. NON RETURN VALVE ASSEMBLY IS A UNIT T	HAT IS SWAGED TOGETHER. THE SWAGE LET GO, ALLOWING HYDRAULIC FLUID TO VENT OVERBOARD. THIS VALVE IS INSTALLED TO PREVENT	 PRESSURE FROM EITHER ENGINE DRIVEN PUMP GOING TO THE OPPOSITE PUMP IN THE EVENT OF A PUMP FAILURE OR ENGINE SHUTDOWN. T	IME AND CYCLES ON PART ARE UNKNOWN BUT IT IS VERY LIKELY ORIGINAL EQUIPMENT. (TC NR 20080306002)			2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
	20081104			2008	11	4	CA080313002      	4	20080312	G	3197		CONNECTOR       			SNIAS 	350   	AS350BA     	8680817	EU  										INSTRUMENT LIGHT	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING THE FLIGHT THE PILOT SELECTED THE INSTRUMENT LIGHTS ON. FIVE MIN LATER THE LIGHTS BEGAN TO CYCLE ON AND OFF	. THE PILOT TOUCHED THE CONNECTOR AND ELECTRICAL FLAME CAME FROM THE CONNECTOR. THERE WAS A BURNING ODOR BUT NO VISIBLE 	SMOKE. THE PILOT SHUT THE LIGHTS DOWN AND CONTINUED THE FLIGHT. THE PROBLEM COULD NOT BE REPRODUCED ON THE GROUND, BUT T	HE UNIT IS UNSERVICABLE. (TC NR 20080313002)			1	G	7	1 	3U			NC	H9EU    					 
	20080602		EU  	2008	6	2	CA080313004      	2	20080311	G	7200		ENGINE          			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 2	MALFUNCTIONED   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											DURING APPROACH IN ICING CONDITIONS AND HEAVY PRECIPITATION, WHEN THE PILOT THROTTLED BACK, ENGINE NR 2 FLAMED OUT AND A	UTO FEATHERED. THE PILOT DID NOT ATTEMPT TO RE-LIGHT AND LANDED WITH ONE ENGINE OPERATING. MAINTENANCE CHECKED THE OIL S	CREEN, FUEL SCREEN AND FUEL TANK SUMPS. NO CONTAMINATION WAS FOUND. MAINTENANCE CONDUCTED HIGH AND LOW POWER ENGINE RUNS	 AS WELL AS AUTO-FEATHER CHECKS AND FOUND NO PROBLEM WITH THE ENGINE.  ROLLS-ROYCE NOTICE TO OPERATES NO. 1142 IS DIRECT	ED TO THE FLIGHT CREWS TO "SWITCH ON THE ENGINE IGNITION SWITCHES WHEN MODERATE OR SEVERE ICING IS ENCOUNTERED". THE PIL	OT DID NOT HAVE THE ENGINE IGNITION SWITCHES SELECTED TO "ON" DURING THIS EVENT.  THE PILOTS HAVE BEEN REMINDED OF THIS 	2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
	20080521		EA  	2008	5	21	CA080314001      	1	20080206	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7038 								(CAN) FLT NR 3874  DISCREPANCY: (CAPT`S SIDE WINDOW FWD UPPER CORNER, MIDDLE PANE CRACKED DURING APPROACH)  REQUESTED TH	E PN/SN, TSN/CSN INFORMATION. UPDATE 2/6: REPLACED THE WINDOW. (TC NR 20080314001)					2	L	7	2 	4F			RT	A21EA   					 
200805141    	20080514	1    	NE  	2008	5	14	CA080314002      	2	20080313	G	7200	CF343B1	ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NR 2	FIRE            	W				A	F	B		UNSCHED LANDING         	ACTIVATE FIRE EXT.      	EMER. DESCENT           		B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AC LANDED, AFTER THE PILOT HAD DECLARED AN EMERGENCY FURTHER TO A FIRE ON ENG NR 2. THE AC FLEW IN CRUISE AT FL 22	0, WHEN THE PILOT GOT A FIRE ALARM ON ENG 2. THE TEMP (ITT) OF ENGINE SHOWED CLEARLY THAT AN ACTUAL FIRE HAD BROKEN OUT.	 PILOT DECLARED AN EMERGENCY, APPLIED THE FIRE DRILL, ACTIONED THE FIRE PROTECTION SYS (BOTH BOTTLES) AND WENT IN AN EME	RGENCY DESCEND TOWARDS AIRPORT. DURING DESCEND, THE TEMP OF ENG NR 2 STAYED AT A HIGHER LEVEL (760 DEGREE C) THAN ENG NR	 1 (600 DEGREE C). THE AC LANDED SAFELY, ATC PERSONNEL WITNESSED A SLIGHT BLACK SMOKE COMING FROM THE ENGINE. THE FIRE B	RIGADE WENT INTO ACTION AND USED FIRE EXTINGUISHING AGENT, BUT DID NOT REPORT HAVING ACTUALLY SEEN FLAMES. (TC NR 200803	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080521		NM  	2008	5	21	CA080314003      	1	20080307	G	5320	19093649001	BRACKET         			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					FUSELAGE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3018 	3018 							(CAN) EXCERPT FROM MESSAGE RECEIVED FROM MAINT ON THAT FINDING:  NOTE THE CRACK RUNNING FROM THE HIGHLOCK. FOUND WHILE T	/S ON SNAG L4438921. THIS IS THE MAIN SUPPORT FOR THE LOWER END OF THE CONTROL QUADRANT IN THE LT WHEEL WELL THE FLANGE 	IS SUPPORTING THE BULHEAD THAT CONCERNS FLEXING AND CONTACTING THE LOWER FWD SECTION OF THE CONTROL QUADRANT.  MFG INFOR	MED OF THE FINDING, REPAIR SUGGESTED TO FLEET ENGINEERING.  MORE INFO TO BE PROVIDED. (TC NR 20080314003)			2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081104		SW  	2008	11	4	CA080314004      	1	20080306	G	2510	STCSH0631	INERTIA REEL    	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COCKPIT SEAT	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CO-PILOT SEAT SHOULDER HARNESS INERTIAL REEL CABLE FOUND BINDING AGAINST VERTICAL REFERENCE SEAT KIT - PLATE ASSY 	P/N AAL-292-031-001. FOUND TO BE COMMON PROBLEM WHEN CHECKED ON OTHER ACFT. WILL CONTACT MFG.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20080521		EU  	2008	5	21	CA080314005      	1	20080311	G	3244	542K694	TIRE            			AIRBUS	A330  	A330*       	       	EU  	RROYCE	RB211 	RB211*      	54555	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			LD	LANDING        	1			CA											(CAN)THE AC BLEW THE NR (4) MAIN TIRE ON DEPARTURE. THE FLIGHT CREW ELECTEDTO DIVERT, AND ULTIMATELY LANDED APPROXIMATEL	Y 15000 KGS OVER THE MAXIMUM STRUCTURAL LANDING WEIGHT OF 185000KGS. DURING TAXI, THE NR (3),  RT FWD IB MAIN TIRE DEFLA	TED AND THE AC WAS SUBSEQUENTLY SERVICED BY MAINT, BEFORE BEING ABLE TO POSITION TO THE GATE. INVESTIGATION IS ONGOING. 	SDR WILL BE UPDATED ACCORDINGLY. (TC NR 20080314005)			2	L	7	2 	4F	4	F	RT	A46NM   	A12EU				 
	20080521		NM  	2008	5	21	CA080314006      	1	20080312	G	2150	78279018	ACM             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  		CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33905	23037							(CAN) WHILE CARRYING OUT WORK CARD TO REMOVE COMPONENT IT WAS DISCOVERED THERE WAS A 6 INCH CRACK ON THE INNER SIDE OF T	HE CHAMBER. (TC NR 20080314006)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080603		GL  	2008	6	3	CA080314007      	2	20080312	G	7261		ENGINE          			EMB   	135   	EMB135ER    	3260203	SO  	ALLSN 	AE300 	AE3007A     	 	GL  						LEAKING         	W				A				UNSCHED LANDING         				K	M	Y	FLUID LOSS                	OVER TEMP                 	ENGINE STOPPAGE           	CR	CRUISE         	1			CA											OIL IMPENDING BYPASS INDICATION ILLUMINATED ALONG WITH OIL TEMPERATURE RISING TO 141 DEGREES.  THE PILOT COMMANDED THE S	HUT DOWN OF THE ENGINE DUE TO OIL TEMPERATURE AND QUANTITY INDICATING THREE QUARTS.  AIRCRAFT RETURNED TO CMH WITHOUT IN	CIDENT.  MAGNETIC INDICATING PLUGS WERE FOUND CLEAN.  A SMALL PUDDLE OF OIL IN FAN SECTION AND A LOT OF OIL IN THE EXHAU	ST WAS REPORTED.  THE OIL FILTER WAS FILLED WITH CARBON DEBRIS.  ENGINE HAS ACCUMULATED 0.8 HOURS SINCE LAST REPAIR AND 	THIS WAS THE 1ST FLIGHT SINCE REPAIRS.  ENGINE UNDER INVESTIGATION, FURTHER REPORT WILL BE SUBMITTED AFTER ENGINE TEARDO	WN. (TC NR 20080314007)	2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
	20080603		NE  	2008	6	3	CA080314008      	2	20080313	G	7200		ENGINE          			AIRBUS	A319  	A319114     	3930350	NM  	GE    	CFM56 	CFM565A     	13802	NE  						FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA			30804	14183							DURING CLIMB A LOUD BANG AND VIBRATION WAS FELT, FOLLOWED BY ENG 2 FAIL ON ECAM AT 8300 FT AND CLIMBING.  LANDED SAFELY 	WITH NO ISSUE WITH LANDING.  AFTER LANDING DEBRIS WAS FOUND IN ENGINE EXHAUST AND AFT CENTER BODY WAS DAMAGED.  INVESTIG	ATION INTO CAUSE OF ENGINE FAILURE IS ON GOING AND SDR WILL UPDATED ACCORDINGLY.  ENGINE HAS BEEN CHANGED. (TC NR 200803	14008)			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
	20080603		GL  	2008	6	3	CA080314009      	2	20080310	G	7230		BEARING         			EMB   	145   	EMB145LR    	3260212	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					NR 4	FAILED          	W				K				NONE                    				B	M		SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 		IN	INSP/MAINT     	1			CA											ENGINE REMOVED FOR ITT EXCEEDANCE, AUTO IFSD, SMOKE IN COCKPIT/CABIN, OIL DEBRIS ON ALL CHIP DETECTORS.  TEARDOWN OF ENG	INE REVEAL NR 4 BEARING FAILURE AND ALSO NR 3 BEARING FAILURE.  EXCESSIVE DAMAGE IN COMPRESSOR AREA DUE TO BOTH SUPPORTI	NG BEARING FAILURE.  FAILED COMPONENTS WILL BE SENT TO THE OEM FOR INVESTIGATION. (TC NR 20080314009)				2	L	7	2 	4T	4	F	RT	T00011AT	TE6CH				 
	20081219		CE  	2008	12	19	CA080314010      	1	20080306	G	3245	G195X6758	TUBE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TIRE	FLAT            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) TIRE WENT FLAT SITTING IN HANGAR.  CRACK FOUND IN TUBE AT BASE OF VALVE STEM.						1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20080603		CE  	2008	6	3	CA080314011      	1	20080306	G	8011	200SGL119Q2	BRUSHES         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	STARTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1181 								SLOW SPOOLING OVER ENGINE, ENGINE STARTER BRUSHES WORN OUT (TC NR 20080314011)						1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20081104		NE  	2008	11	4	CA080314012      	1	20080310	G	7921	84300207	THERMOSTAT      			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					OIL COOLER	STUCK           	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THERMOSTAT STUCK AND ENGINE OIL TEMPERATURE INCREASED TO RED LINE. (TC NR 20080314012)						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
	20080521		SO  	2008	5	21	CA080314013      	2	20080307	G	8500	TSIO520EB	ENGINE          			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  		MAKING METAL    	W				E				ENGINE SHUTDOWN         				O			OTHER                     			AP	APPROACH       	1			CA				714  							(CAN) ON FINAL APPROACH INTO AIRPORT THE RT ENGINE MANIFOLD PRESSURE STARTED CHANGING. THE PILOT THEN NOTICED THAT THE R	T OIL PRESSURE HAD DROPPED TO THE RED LINE. THE RT PROP WAS FEATHERED AND THE ENGINE WAS SHUTDOWN. SMALL BITS OF METAL W	ERE FOUND UNDER THE OIL PRESSURE RELIEF VALVE. THE ENGINE WAS REMOVED AND SENT FOR WARRANTY. (TC NR 20080314013)				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
	20081105		SW  	2008	11	5	CA080314014      	1	20080307	G	3246	205050400063	CROSSTUBE       			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) HELICOPTER WORKING HELI-SKIING. THE PASSENGERS WERE LOADING INTO THE HELICOPTER. ALMOST ALL THE SEATS WERE OCCUPIE	D WHEN A SUDDEN SETTLING WITH A METALLIC NOISE ON THE REAR OF THE MACHINE OCCURRED. IT WAS NOTED THAT THE REAR CROSS TUB	E WAS CRACKED ALL THE WAY AROUND OR BROKEN UNDERNEATH THE RIGHT HAND CROSS TUBE SADDLE. (ABOUT 1" INSIDE THE SADDLE AREA	)			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081104		WP  	2008	11	4	CA080314015      	1	20080313	G	6320	369D2512311	GEAR            			HUGHES	369   	369         	4470702	WP  	ALLSN 	250C  	250C20      	03013	GL  					M/R TRANSMISSION	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			616  								(CAN) ACFT WAS BROUGHT IN WITH XMSN NOISE AND CHIP LIGHT. XMSN WAS OPENED AND A PIECE OF GEAR TOOTH 7/8 OF AN INCH LONG 	WAS FOUND MISSING. THIS IS THE SECOND OCCURENCE OF THIS TYPE THAT WE HAVE ENCOUNTERED. THE LAST SDR WAS APRIL OF 2005. (	TC NR 20080314015)				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
200805141    	20080514	1    	EU  	2008	5	14	CA080314016      	1	20080309	G	2751	A275704050400	SWITCH          			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					KRUEGER FLAP	CONTAMINATED    	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, ECAM WARNING "FLAP KRUEGER NOT RETRACTED LIGHT" CAME ON. FLIGHT RETURNED TO THE STATION. SFCC INDICA	TED FAULT COMING FROM THE LT KRUEGER RETRACT SWITCH. MAINT FOUND THE SWITCH BACK SHELL CONTAMINATED WITH WATER.  CONNECT	OR AND SWITCH CLEANED OUT AND SYS TESTED SERVICEABLE.  AC DEPARTED AND SAME SNAG REOCCURRED DURING CLIMB. THE AC RETURNE	D TO THE STATION AND WAS REMOVED FROM SERVICE FOR TROUBLESHOOTING. DURING INSP, FOUND SLIGHT DAMAGE ON WIRE, 2 INCHES FR	OM CONNECTOR. WIRE PROTECTION CARRIED OUT IAW ESPM 20-53-00 AND SWITCH ASSY REPLACED. SYS TESTED SERVICEABLE. AC WAS RET	URN TO SERVICE WITH NO REOCCURRENCE. (TC NR 20080314016)	2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20080521		EA  	2008	5	21	CA080314017      	1	20080306	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) FLAP FAIL MESSAGE SHORT FINAL WHEN CREW WERE SELECTING FROM FLAP 8 TO FLAP 20 POSITION, FLAPS REMAINED AT 8 DEGREE	S AND LANDED NORMAL. MAINT REPORTED THAT THE LIST OF FAULTS IN MDC ARE :  1- JAM 2- FECU 3- L MOTOR BRAKE  THE FAULT COD	ES WERE RETRIEVED FROM THE FECU AND POINT TOWARDS POWER LOSS DUE TO THE SDS LT SKEW DETECTOR FLAGGED. MAINT RESET THE SD	U AND FECU. RAN THE FLAPS UP AND DOWN 2 TIMES. THEN THE SDU FLAGGED THE LT SKEW DETECTOR AGAIN. DUMMY BOX INSTALLED, SYS	TEM TESTED AND IT WAS CONFIRMED THE SKEW DETECTION IS AT FAULT. MAINT HAS CONFIRMED THAT THE SDU FECU POWER 1 AND 2 LIGH	TS FLAGGED, AND THE LT OB PANEL SKEW L4 AND L3 LIGHTS FLAGGED. SKEW DETECT SYS BOUND AT FAULT. SKEW DETECT SYS DEACTIVAT	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080521		EU  	2008	5	21	CA080314018      	1	20080307	G	3250	5325012004	BEARING         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG STEERING	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8888 								(CAN) FORK BEARING ON NOSE LANDING GEAR STEERING FOUND TWISTED. THIS DEFECT WAS FOUND ON NOSE LANDING GEAR SHOCK ABSORBE	R REPAIR AND SERVICE. (TC NR 20080314018)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080521		GL  	2008	5	21	CA080314019      	2	20080304	G	7250	6871505	BEARING         			HILLER	UH12  	UH12E       	4360122	WP  	ALLSN 	250C  	250C20      	03013	GL  					NR 5	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			169  								(CAN) CHIP LIGHTS METAL CONTAMINATION ENGINE SHOP DETERMINED NR 5 BEARING FAILURE.  (TC NR 20080314019)						1	G	7	1 	3O	3	U		4H11    	E4CE				 
	20080603		NE  	2008	6	3	CA080314021      	2	20080209	G	7200		ENGINE          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  						MAKING METAL    	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			4581 	1456 							ON THE FIRST GROUND RUN OF THE DAY DURING GROUND WARM UP, A NOISE WAS EMITTED FROM THE ENGINE AND IMMEDIATLEY AFTER NOIS	E WAS HEARD THE ENGINE CHIP LIGHT ILLUMINATED.  PILOT SHUT ENGINE DOWN.  METAL PARTICLES WERE FOUND ON MOS CHIP PLUG AND	 SOME ON THE ELECTRIC CHIP PLUG.  ENGINE WAS REMOVED AND SENT TO TURBOMECA MONTREAL FOR INSPECTION AND REPAIR. WE WERE L	UCKY THIS DID NOT HAPPEN IN THE AIR AS WE WOULD BE LOOKING AT A TOTAL ENGINE FAILURE. (TC NR 20080314021)			1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20080521		SO  	2008	5	21	CA080314022      	1	20080309	G	2400	W23X1A1G40	CIRCUIT BREAKER 			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	COCKPIT	OPEN            	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) CIRCUIT BREAKER FOUND IN OPEN CIRCUIT AND ALSO FOUND ONE FAULTY WIRE WHICH WAS REPLACED. (TC NR 20080314022)						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
200805141    	20080514	1    	EU  	2008	5	14	CA080317003      	1	20080311	G	2435		COOLING FAN     		160SG140Q   	UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					STARTER GEN	SEPARATED       	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			128  								(CAN) DURING THE ENGINE START SEQUENCE, AN UNUSUAL NOISE WAS HEARD BY THE PIC. THE NOISE WAS MOMENTARY AND OCCURRED SEVE	RAL SECONDS AFTER STARTER GENERATOR ENGAGEMENT AND JUST PRIOR TO ENGINE LIGHT OFF. ENGINE PARAMETERS REMAINED NORMAL SO 	THE START SEQUENCE WAS COMPLETED.  AFTER ENGINE STABILIZATION THE ENGINE WAS SHUTDOWN FOR INVESTIGATION AND THE FLIGHT W	AS CANCELLED.  MAINT WERE ABLE TO DUPLICATE THE NOISE BY ENGAGING THE STARTER FOR SEVERAL SECONDS. THE STARTER GENERATOR	 WAS REMOVED TO THE BENCH AND THE COVER WAS REMOVED. IT WAS NOTED IMMEDIATELY THAT THE COOLING FAN HAD BECOME SEPARATED 	FROM THE ARMATURE SHAFT AND WAS ABLE TO SPIN FREELY. BY QUICKLY SPINNING THE FAN AROUND THE SHAFT, THE NOISE HEARD DURIN	1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
	20080521			2008	5	21	CA080317004      	4	20080214	G	8300		GEAR            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	ACCESSORY G/B	FAILED          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) LOW OIL PRESSURE LIGHT CAME ON IMMEDIATELY AFTER TAKEOFF.  PWR WAS BROUGHT BACK AND AC RETURNED FOR SAFE LANDING. 	ENGINE WAS SHUTDOWN OFF RUNWAY, PROP FEATHERED AUTOMATICALLY. BOTH SUCTION SCREEN AS WELL AS OIL FILTER INSPECTED, NO ME	TAL CONTAMINANTS FOUND. PROP DID NOT TURN FREELY. ALTERNATOR PULLED OFF ON THE BACK OF THE ENGINE. GEAR FOUND LYING LOOS	E IN ACCESSORY CASE WITH MULTIPLE BROKEN TEETH ON OTHER GEARS. (TC NR 20080317004)			1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920	 
	20080521		EA  	2008	5	21	CA080317005      	2	20080304	G	8520		PISTON PIN      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	NR 1 CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ALUMINUM FOUND IN OIL FILTER DURING 100 HOUR INSP. CYLINDER BOROSCOPED, SUSPECT CYLINDER REMOVED, FWD PISTON PIN F	OUND WORN ON NR 1 CYLINDER. (TC NR 20080317005)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081222		EA  	2008	12	22	CA080317006      	2	20080222	G	8530		CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ALUMINUM FOUND IN OIL FILTER DURING 100 HR INSP. CYLINDER BOROSCOPED, SUSPECT CYLINDER REMOVED, FWD PISTON PIN FOU	ND WORN ON NR 1 CYLINDER.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081222		CE  	2008	12	22	CA080317009      	1	20080302	G	2720	04115261	RUDDER BAR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11625								(CAN) PILOT NOTED LT PILOTS RUDDER PEDAL WAS NOT IN IT`S CORRECT POSITION. THE RUDDER BAR WHICH IS A WELDMENT WAS FOUND 	TO BE CRACKED AT THE ATTACHMENT POST FOR THE LT RUDDER PEDAL.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081230		CE  	2008	12	30	CA080318001      	1	20080306	G	7160		BRACKET         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					CARB HEAT	DETACHED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ROUTINE INSP TECH NOTICED NO CARB HEAT DROP ON IN-COMING RUN-UP. TECH DISCOVERED THAT ONE OF THE 2 CARB AIR	 BOX BUTTERFLY VALVE BRACKETS HAD BECOME DETACHED FROM SHAFT AND VALVE WAS NOT OPENING OR CLOSING PROPERLY.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20080603		EA  	2008	6	3	CA080318002      	2	20080226	G	8530		STUD            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	CYLINDER	BROKEN          	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA				3495 							DURING WALK AROUND, PILOT NOTICED ENGINE OIL COVERING LT SIDE OF FUSELAGE AND EMPENNAGE.  MAINTENANCE INSPECTED ENGINE A	ND FOUND ON NR 2 CYLINDER, ONE BROKEN THROUGH STUD.  OIL WAS RUNNING DOWN THROUGH STUD AND EXITING CYLINDER BASE WHERE A	TTACH NUT USED TO BE.  OIL LEAK WAS NOT DISCOVERED DURING OR AFTER PREVIOUS NIGHT FLIGHT. (TC NR 20080318002)				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
	20080521		EA  	2008	5	21	CA080318008      	2	20080317	G	7310	252429710	SERVO           			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUEL SYSTEM	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				193  							(CAN) CHECKED IAW EMERGENCY AWD 2008-06-51. FOUND, DID NOT APPLY BY DATE BUT WHEN VISUALLY INSPECTED FOUND SAME PROBLEM 	AS REPORTED IN AWD. O/H DATE WAS JANUARY 28, 2005. AWD STATED AUGUST 22, 2006. ALL SERVOS MAY NEED TO BE CHECKED. (TC NR	 20080318008)				1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
	20080602		WP  	2008	6	2	CA080319003      	2	20080311	G	7313	31038294	NOZZLE          								GARRTT	TPE331	TPE33111U   	01514	WP  					FUEL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1791 							THE A/C CAME INTO THE HANGER FOR A ROUTINE FUEL NOZZLE AND BOROSCOPE INSPECTION.  DURING THE BOROSCOPE INSPECTION OUR NI	GHT MAINTENANCE FOUND SOME DISCREPANCIES IN THE ENGINE.  FURTHER INSPECTION FROM THE TURBINE SHOP IT WAS NOTED THAT THE 	NOZZLE SEGMENTS THAT MAKE UP THE NR 1 STATOR ASSEMBLY HAD SOME DAMAGE TO THEM.  THE NOZZLE SEGMENTS WERE OVERHAULED FROM	 SOUTHWEST TURBINE.  THE ENGINE WAS REPLACED AND FORWARDED TO THE ENGINE SHOP FOR FURTHER REPAIR. (TC NR 20080319003)								4	T			E4WE				 
	20080603		NM  	2008	6	3	CA080319004      	1	20080307	G	5310	19093649001	SUPPORT         			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					MLG WW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3018 	3018 							ON AIRCRAFT A CRACK WAS FOUND TO MLG WELL BULKHEAD SUPPORT.  THE CRACK STARTS AROUND ONE OF THE ATTACHMENT HOLES AND GOE	S UP TO THE MIDDLE OF DISTANCE BETWEEN THE TWO ATTACHMENT HOLES.  THE BULKHEAD IS ALSO FLEXING AND CONTACTING THE LOWER 	SECTOR OF THE AILERON CONTROL QUADRANT.  PROBLEM ALSO FOUND ON THE FOLLOWING A/C FIN NUMBER: 307, 309, 311, 313, 315, 31	7, 318, 319, 320, 322, 323, 324, 326, 332 (TC NR 20080319004)			2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20080602			2008	6	2	CA080319005      	1	20080319	G	8011	EBB131A	DRIVE SYSTEM    																	STARTER	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				97   							STARTER RECEIVED DUE TO DRIVE ASSEMBLY FAILURE.  ENGINE COULD NOT BE STARTED BECAUSE DRIVE WOULD NOT ENGAGE.  WHEN INSPE	CTED THE DRIVE COULD NOT BE TURNED OUT OR SPUN BY HAND TO EXTEND THE GEAR SECTION OF THE DRIVE.  STARTER WAS RETURNED TO	 KELLY AEROSPACE FOR WARRANTY REPLACEMENT. (TC NR 20080319005)																	 
	20080602		SW  	2008	6	2	CA080319007      	1	20080306	G	3260	EN516	SWITCH          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT MLG	INTERMITTENT    	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											ON APPROACH, THE CREW NOTICED THAT THE LT GEAR HAD NO "GREEN" SAFE LIGHT.  FLY BY WAS CARRIED OUT CONFIRMED GEAR DOWN.  	AIRCRAFT LANDED WITHOUT INCIDENT.  SWITCH WAS FOUND STICKY.  SWITCH REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20	080319007)				2	L	7	2 	4T	3	T	RT	A8SW    	E2WE	6	C	3PNE	 
	20080602		NE  	2008	6	2	CA080319008      	2	20080306	G	7200		ENGINE          			PAC   	CRESCO	CRESCO      	       	CE  	PWA   	PT6   	PT6A34AG    	52053	NE  						POWER LOSS      	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											DURING TAKEOFF ROLL, A NOISE WAS HEARD ACCOMPANIED BY LOSS OF ENGINE POWER.  THE TAKEOFF WAS ABORTED.  INITIAL INSPECTIO	N REVEALED FRAGMENTS SIMILAR TO COMPRESSOR BLADE MATERIAL DISTRIBUTED THROUGHOUT THE INLET.  TEARS IN THE INLET SCREEN W	ERE NOTED.  THE ENGINE HAS BEEN REMOVED AND WILL BE INVESTIGATE ROOT CAUSE ONCE ESTABLISHED.				1	L	7	1 	4T	4	T	NT	EXPA1L71	E4EA				 
	20080602		EA  	2008	6	2	CA080320002      	1	20080318	G	2797	MS27473T20B4	CONNECTOR       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					FLUTTER DAMPER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			19157								TASK NR 27-34-05-710-801 WAS BEING PERFORMED ON THE ELEVATOR FLUTTER DAMPERS.  IT FAILED THIS TASK FOR LOW FLUID LEVEL T	RANSMITTER SWITCHES.  THIS TASK WAS CALLED UP DURING THE AIRCRAFT`S PLANNED HEAVY INSPECTION. T HERE WERE NO REPORTED FA	ILURES WHILE THE AIRCRAFT WAS IN-SERVICE PRIOR TO THIS HEAVY MAINTENANCE VISIT.  DURING THE COURSE OF TROUBLE SHOOTING, 	THE AME FOUND THE CONNECTORS P300 AND J300 CORRODED TO THE EXTENT THAT THE PINS M AND N BROKE OFF WHEN THEY WERE DISCONN	ECTED.  SEVERAL OTHER PINS WERE ALSO FOUND DISCOLORED.  CONNECTOR P/N MS27497T20B41S, BACKSHELL P/N HEX41-AB90-21A9-1, C	ONNECTOR P/N MS27473T20B41P AND BACKSHELL P/N HEX41-AB00-21A9-1 WERE REPLACED AND SYSTEM FUNCTION CHECKED "SERVICEABLE".	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080602		SW  	2008	6	2	CA080320003      	1	20080312	G	5230	2724050083	FRAME           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					CARGO DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			43129								DURING AN AGING AIRCRAFT INSPECTION A CRACK WAS DETECTED VISUALLY EXTENDING FROM THE LOWER AFT LATCH (POSITION 8).  WHEN	 THE DOOR WAS REMOVED FOR REPAIR FURTHER CRACKS WERE DISCOVERED TO THE ATTACHING STRUCTURE FOR BOTH LOWER LATCHES (POSIT	IONS 7 AND 8).  THIS FAILURE IS BELIEVED TO BE THE RESULT OF FATIGUE, AND IF REMAINED UNDETECTED COULD EVENTUALLY RESULT	 IN FAILURE OF THE CARGO DOOR.  IT SHOULD ALSO BE NOTED THAT AD 98-06-25 REQUIRES AN INSPECTION OF THE LATCHING SYSTEM. 	(TC NR 20080320003)		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20080602		CE  	2008	6	2	CA080320004      	1	20080314	G	5320	365533	GASKET          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					SERVO PLUG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1861 								SERVO PLUGS FOUND LOOSE UPON INSPECTION.  SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRM	OTIVE REPRESENTATIVE.  ENGINE REMANUFACTURE DATE OF JULY 14, 2004 DOES NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFE	CTED BY THE AIRWORTHINESS DIRECTIVE.  HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC NR 20080320004)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080602		EA  	2008	6	2	CA080320005      	2	20080314	G	7321	365533	GASKET          	PRECISIONWND		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FCU	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1745 								AD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION.  SERVO PLUG SEALS REPLACED WITH NEW AS	 PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE.ENGINE REMANUFACTURE DATE OF SEPT. 8, 2005 DOES NOT FALL W	ITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LOOSE. RIGHT M	AGNETO P-LEAD WIRE BROKEN. (TC NR 20080320005)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080602		EA  	2008	6	2	CA080320006      	2	20080314	G	7321	365533	GASKET          	PRECISIONWND		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FCU	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1367 								SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMO	TIVE REPRESENTATIVE.  ENGINE REMANUFACTURE DATE OF AUG 18, 2005 AND THE FUEL SERVO WAS REPAIRED JULY 28, 2006 AND BOTH D	O NOT FALL WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE. HOWEVER, THE SERVO PLUGS WERE LO	OSE. (TC NR 20080320006)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20080602		EA  	2008	6	2	CA080320007      	2	20080314	G	7321	365533	GASKET          	PRECISIONWND		CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	FCU	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			293  								AD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION.  SERVO PLUG SEALS REPLACED WITH NEW AS	 PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE.  ENGINE REMANUFACTURE DATE OF SEPT 8, 2004 DOES NOT FALL 	WITHIN THE DATES SPECIFIED THAT ARE AFFECTED BY THE AIRWORTHINESS DIRECTIVE.  HOWEVER, THE SERVO PLUGS WERE LOOSE. (TC N	R 20080320007)			1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
	20080602		CE  	2008	6	2	CA080320010      	1	20080307	G	2750	S16612	SWITCH          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					TE FLAPS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											INTERNAL RETURN SPRING OF SWITCH BROKEN.  TOGGLE NOT RETURNING TO NEUTRAL POSITION.  SWITCH REPLACED WITH NEW. (TC NR 20	080320010)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081105		EU  	2008	11	5	CA080320011      	1	20080320	G	6230	350A37118322	LOCK            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  CRACKED MAIN ROTOR MAST LOCK.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
	20081105		WP  	2008	11	5	CA080320012      	1	20080312	G	6310	C1883	CROSS TIE       			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					SPRAG CLUTCH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			911  								(CAN) DURING A IN-HOUSE 1000 HR CLUTCH INSPECTION THE SPRAG CLUTCH CAGE CROSSBAR WAS FOUND CRACKED. NEW PARTS WERE INSTA	LLED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080602		CE  	2008	6	2	CA080320013      	1	20080319	G	3245	891250	TUBE            			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					TIRE	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			626  								ON TAXI PILOT FELT AIRCRAFT PULLING TO ONE SIDE AND DISCOVERED FLAT TIRE.  TIRE WAS CHANGED AND FLOWN BACK TO BASE.  TIR	E ASSY WAS DISASSEMBLED AND TUBE WAS FOUND BLOWN WITH ABOUT A FOUR INCH SPLIT IN IT.  THE TUBE WAS ALSO FUSED TO THE INS	IDE OF THE TIRE IN THE AREA OF THE BALANCE PATCH.  THIS WAS THE ORIGINAL TIRE INSTALLED AT CESSNA FACTORY WHEN AIRCRAFT 	WAS DELIVERED.  I AM REPORTING THIS DUE TO AN ABNORMAL NUMBER OF TUBES THAT WE HAVE HAD LET GO IN THE LAST MONTH.  TALKI	NG TO OTHER OPERATORS HAS INDICATED THAT OTHERS ARE HAVING THE SAME PROBLEM.  I HAVE BEEN TOLD BY A TIRE COMPANY THAT TH	E BUTYL RUBBER TUBES ARE NOT WORKING WELL IN OUR COLDER CLIMATE. (TC NR 20080320013)	1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
	20080521			2008	5	21	CA080324001      	1	20080324	G	3245	600X6	TUBE            																	TIRE	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BELIEVE TO HAVE ENCOUNTERED A DEFECTIVE TIRE TUBE BATCH. THE TUBES IN QUESTION ARE MFG 6.00 X 6, SOLD UNDER BATCH 	NR 032358. WE HAVE HAD 5 INSTANCES OF TIRE TUBE FAILURE OUT OF 6, WITH THE CONCERNED TUBE BATCH. (TC NR 20080324001)																		 
	20080521		CE  	2008	5	21	CA080325006      	1	20080312	G	5312	12127071	BULKHEAD        			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BULKHEAD CRACK 1.25 IN LONG AT RT SIDE FROM LIGHTNING HOLE.  NEAR STAB ATTACH POINT. (TC NR 20080325006)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P25EA	 
	20080521		NM  	2008	5	21	CA080325008      	1	20080325	G	5315	654681163	FLOORBEAM       			BOEING	737   	737490      	1384715	NM  										BS 986 RBL43	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLOORBEAM FOUND CORRODED DURING VISUAL INSP AND REPAIRED WITH REPAIR PART IAW EA AND SRM. (TC NR 20080325008)						2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080325009      	1	20080325	G	5315	654681179	FLOORBEAM       			BOEING	737   	737490      	1384715	NM  										BS 986 RBL 35-40	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLOORBEAM CAP AT BS 986.5, RBL 35 AND 40 FOUND CORRODED DURING VISUAL INSPECTION AND REPAIRED WITH REPAIR PART IAW	 CUSTOMER EA AND SRM. (TC NR 20080325009)					2	L	7	2 	4F			RT	A16WE   					 
	20080521		NM  	2008	5	21	CA080325010      	1	20080325	G	5315	654681179	FLOORBEAM       			BOEING	737   	737490      	1384715	NM  										BS 986 RBL 27	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLOORBEAM AT BS 98605, RBL 27, WL 207.5 CORRODED UNDERSIDE UNDER CLIP NUT. REPAIRED WITH REPAIR PART IAW CUSTOMER 	EA AND SRM. (TC NR 20080325010)					2	L	7	2 	4F			RT	A16WE   					 
	20080521			2008	5	21	CA080325011      	1	20080325	G	2410	ALV9510R	ROTOR           																	ALTERNATOR	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN INSTALLING DRIVE HUB, THE CUSTOMER NOTICED COTTER PIN COULD NOT BE INSERTED WITH NUT TORQUED AND NUT ALIGNED 	WITH COTTER PIN HOLE LOCATION. WHEN INSPECTED IN-HOUSE THE COTTER PIN HOLES WERE FOUND DRILLED TOO FAR DOWN THE SHAFT. A	LSO THE O-RING BETWEEN THE SPACER AND WASHER UNDER THE DRIVE HUB WAS FOUND TO BE TOO BIG TO ALLOW THE WASHER TO SEAT AGA	INST THE SPACER.  HAS INFORMED US THAT THEY HAD SOME ROTORS LEAVE THEIR FACILITY WITH THIS ISSUE AND THE ALTERNATOR WAS 	RETURNED TO THEM FOR WARRANTY PURPOSES. (TC NR 20080325011)															 
	20080521		GL  	2008	5	21	CA080325013      	2	20080320	G	7250	23038136	SHAFT           								ALLSN 	250C  	250C47B     	 	GL  					TURBINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3823 								(CAN) ENGINE NOISE WAS NOTED AT GROUND IDLE. THE NOISE WAS REDUCED WHEN IN HOVER BUT CONSISTENTLY APPEARED DURING SPOOL 	DOWN TO GROUND IDLE. THE ENGINE WAS REMOVED AND RETURNED TO THE OVERHAULER FOR REPAIR. THE NOISE WAS CONFIRMED DURING AN	 ENGINE TEST WITH VIBRATION MEASUREMENTS. ENGINE DISMANTLE AND INSP ON THE 26TH OF FEBRUARY 2008 REVEALED A CRACKED POWE	R TURBINE SHAFT. THE CRACK LOOSENED THE FIT AT THE TURBINE 4TH WHEEL CURVIC COUPLING AND CAUSED FRETTING AND THE LOSS OF	 A COUPLING TOOTH.   PT OUTER SHAFT P/N 23038136, S/N KU95766 AND 4TH TURBINE WHEEL RETURNED TO MFG FOR INVESTIGATION. (	TC NR 20080325013)						3	U			E1GL				 
	20081105		WP  	2008	11	5	CA080325015      	1	20080304	G	5100		UNKNOWN         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						UNKNOWN         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) UPON TAKE OFF AND AT A SPEED OF 30 KTS AND 10-15FT ALTITUDE (AGL), ACFT YAWED RT WITH ENGINE BACKFIRE AND DECELERA	TION AND IMMEDIATE LOW ROTOR HORN. THE PILOT DROPPED THE COLLECTIVE & CONDUCTED EMERGENCY RUN-ON LANDING IN A FIELD SOUT	H OF THE HANGAR. UPON SAFE LANDING, THE ENGINE WAS STILL RUNNING AND ACCELERATING AND ROTOR RPM WAS AT 90% AND RISING. A	FTER MATCHING THE ENGINE AND ROTOR RPM NEEDLES, THE ACFT WAS LIFTED IN A HOVER AND HOVER TAXIED BACK TO THE HANGAR.  NO 	MECHANICAL PROBLEMS WERE FOUND. THE ACFT WAS GROUND RUN AND HOVERED FOR 30 MINS AT VARIOUS POWER SETTINGS WITH NO FURTHE	R INCIDENT. AT THE TIME OF THIS INCIDENT, THIS ACFT HAD THE DART COLD WEATHER BAFFLES INSTALLED.  WE HAVE IMPLEMENTED A 	1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081105		SW  	2008	11	5	CA080326001      	1	20080325	G	8097		WIRE            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					STARTER	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START UP THE STARTER RELAY CIRCUIT BREAKER WAS POPPING NOT ALLOWING THE STARTER TO START.  IT WAS FOUND THA	T THERE WERE 2 WIRES LABELED K2D20 AND K3C20 CHAFFED INSIDE THE CO-PILOTS COLLECTIVE. K3C20 HAD BEEN SOLDER SPLICED AND 	CHAFED AT THE SPLICE AND K2D20 WAS CHAFFED THROUGH THE WIRE.				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20080521		SW  	2008	5	21	CA080326002      	1	20080324	G	7810	3101582	EXHAUST DUCT    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN THE ENG WAS UNDERGOING A PHASE 6 INSP, A CRACK APPROX 3 INCH LONG WAS DISCOVERED IN THE ENGINE EXHAUST DUCT N	EAR THE EGT PROBE BOSSES.  IT APPEARED TO BE ON A PREVIOUS WELD.  REMOVED AND REPLACED THE DUCT. (TC NR 20080326002)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
	20080521		CE  	2008	5	21	CA080326003      	1	20080324	G	2161		COUPLING        			CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					TEMP CONTROL	MISINSTALLED    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CREW WROTE UP, CABIN PAC STUCK ON FULL COLD. TROUBLESHOOTING CARRIED OUT AND FOUND THAT THE COUPLING FOR CABIN TEM	P CONTROL HAD DISCONNECTED FROM THE ENVIROMENTAL CONTROL UNIT. BOTH CLAMPS AND THE COUPLING WERE INTACT HOWEVER THE COUP	LING HAD BEEN INSTALLED INCORRECTLY. COUPLING WAS REINSTALLED AND LEAK CHECKED SERVICEABLE. (TC NR 20080326003)				2	L	7	2 	4F	4	F		A9NM    	E6WE				 
	20081105		WP  	2008	11	5	CA080326004      	1	20080304	G	2435		ARMATURE        			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER GEN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				543  							(CAN) HOLES MELTED THROUGH ARMATURE CASE IN STARTER.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081105		WP  	2008	11	5	CA080327005      	1	20080317	G	2435		GEAR            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER GEN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27   								(CAN) STARTER AND RING GEAR TEETH FOUND DAMAGED DURING A DI						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081105		WP  	2008	11	5	CA080327006      	1	20080304	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			203  								(CAN) STARTER INTERMITTENT						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081105		WP  	2008	11	5	CA080327007      	1	20080307	G	6520	C0211	GEARBOX         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					TAIL ROTOR	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				4    							(CAN) TAILROTOR GEARBOX FOUND LEAKING FROM THE INPUT SEAL DURING DI						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080521		NE  	2008	5	21	CA080328001      	2	20080320	G	7250	310703301	BEARING RACE    								PWA   	PW120 	PW123       	 	NE  					NR 15	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				11000							(CAN) EIR PW100 2008-025, METAL CONTAMINATION OF THE RGB OIL SYS. (TC NR 20080328001)											4	T			E20NE				 
	20080603		NE  	2008	6	3	CA080328002      	2	20080309	G	8530	399353	CYLINDER HEAD   			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					NR 2	SEPARATED       	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA				5    							HEAD SEPERATED FROM NR 2 CYLINDER AFTER 4.9 HRS AIRTIME.  CYLINDER HEAD SEPARATION OCCURRED DURING CRUISE FLIGHT.  UNEVE	NTFUL LANDING CARRIED OUT.  REPLACEMENT CYLINDER HEAD INSTALLED AND AIRCRAFT COMPLETED ITS MISSION. (TC NR 20080328002)					1	H	7	1 	3R	3	R	RC	A806    	5E1				 
	20080603		CE  	2008	6	3	CA080328003      	1	20080319	G	5514	12326231	BRACKET         			CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520J      	17032	SO  					HORIZONTAL STAB	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3218 								DURING THE ANNUAL INSPECTION REINFORCEMENT BRACKET (P/N 12 32623-1) WAS FOUND TO HAVE A CRACK RUNNING FROM THE BOTTOM BO	LT HOLE TO THE EDGE OF THE BRACKET.  THE BRACKET IS ATTACHED TO THE REAR SPAR OF THE LT HORIZ STABILIZER.  AFFECTED PART	 REPLACED. (TC NR 20080328003)				1	H	7	1 	3O	3	O		3A21    	E5CE				 
	20080603		CE  	2008	6	3	CA080328004      	1	20080319	G	5312	12120031	DOUBLER         			CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520J      	17032	SO  					BULKHEAD	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3218 								DURING THE ANNUAL INSPECTION A CRACK WAS DETECTED RUNNING FROM THE ANCHOR NUT RIVET HOLE TO THE EDGE OF THE DOUBLER PLAT	E, THIS BRACKET IS ATTACHED TO THE REAR FRAME AT STN 209, P/N 12120402-3.  AFFECTED PART REPLACED.  (TC NR 20080328004)					1	H	7	1 	3O	3	O		3A21    	E5CE				 
	20080603			2008	6	3	CA080328005      	2	20080328	G	7414	10357586	DISTRIBUTOR GEAR																	MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2000 								MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL.  WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS F	OUND LOOSE AND HAD ALMOST WORN TO THE POINT THAT IT COULD HAVE COME OFF THE END OF THE SHAFT AND RUBBED AGAINST THE COIL	 TAB OR CARBON BRUSH.  THIS CONDITION HAS BEEN NOTICED IN MANY OTHER MAGS AND IN CONVERSATION WITH TCM WE HAVE BEEN TOLD	 TO PUT THE GEAR IN A PRESS AND FLARE THE END OF THE SHAFT OVER MORE TO RETAIN THE WASHER IF IT IS FOUND LOOSE.  THE WAS	HER IN THIS CASE WAS WORN AND THIS PROCEDURE COULD NOT BE ACCOMPLISHED.  THE DATE CODE (BATCH CODE) ON THE GEAR WAS `94`	.  THE GEAR WAS REPLACED DURING THE OVERHAUL AND THE MAG WAS RETURNED TO SERVICE. (TC NR 20080328005)														 
	20080603			2008	6	3	CA080328006      	2	20080328	G	7414	10357586	DISTRIBUTOR GEAR																	MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2000 								MAG WAS RECEIVED TIME EXPIRED FOR OVERHAUL.  WHEN DISASSEMBLED THE WASHER THAT RETAINS THE NYLON GEAR ON THE SHAFT WAS F	OUND LOOSE AND HAD ALMOST WORN TO THE POINT THAT IT COULD HAVE COME OFF THE END OF THE SHAFT AND RUBBED AGAINST THE COIL	 TAB OR CARBON BRUSH.  THIS CONDITION HAS BEEN NOTICED ON MANY OTHER MAGS AND IN CONVERSATION WITH TCM WE HAVE BEEN TOLD	 TO PUT THE GEAR IN A PRESS AND FLARE THE END OF THE SHAFT OVER MORE TO RETAIN THE WASHER IF IT IS FOUND LOOSE.  THE WAS	HER IN THIS CASE WAS WORN AND THIS PROCEDURE COULD NOT BE ACCOMPLISHED.  THE DATE CODE (BATCH CODE) ON THE GEAR WAS `94`	.  THE GEAR WAS REPLACED DURING THE OVERHAUL AND THE MAG WAS RETURNED TO SERVICE. (TC NR 20080328006)														 
	20080603		CE  	2008	6	3	CA080328007      	1	20080327	G	5280	150450018	ARM             			CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					MLG DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING PILOT WALKAROUND THE RT MAIN GEAR DOOR WAS HANGING SLIGHTLY DOWN FROM RETRACTED POSITION.  MAINTENANCE TO REPLACE	 PART. (TC NR 20080328007)					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
	20081105		WP  	2008	11	5	CA080328008      	1	20080308	G	2410		BRUSHES         	KELLY       		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ALTERNATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			847  								(CAN) DURING A POST FLIGHT DI THE ALTERNATOR BELT WAS FOUND DAMAGED. CARRIED OUT AN INSPECTION OF THE ALTERNATOR AND FOU	ND THE BRUSHES AND SLIP RINGS WORN.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080521		EA  	2008	5	21	CA080328010      	1	20080327	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAP	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			29317	29317							(CAN) ON APPROACH WHEN MAKING INITIAL FLAP SELECTION CREW RECEIVED FLAP FAULT MESSAGE, FLAPS FAILED TO OPERATE. CREW PER	FORMED FLAP (0) LANDING. CREW ADVISE OAT WAS -57 TO -59 FOR ABOUT AN HOUR AT FLIGHT LEVEL 260 PRIOR TO COMMENCING DESCEN	T. ON GROUND FLAPS POSITIONED TO 8 DEG AND AC FERRIED WITH FLAPS AT 8 DEG TO MAINT BASE FOR CORRECTIVE ACTION. FLAP FAUL	T CODE INDICATED FLAP JAM.  MAINT FOLLOWING COMPANY POLICY IS REPLACING ALL FLAP ACTUATORS, CLEANING AND LUBRICATING ALL	 FLAP DRIVES, NO OBVIOUS ABNORMALITIES NOTED.  (TIMES PROVIDED ARE AC TT AS NO SPECIFIC COMPONENT IDENTIFIED AS TO CAUSE	) (TC NR 20080328010)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080521		NM  	2008	5	21	CA080328011      	1	20080328	G	7500		DUCT            			BOEING	727   	727200      	138407E	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					BLEED AIR	LEAKING         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF OUT, NR 2 ENGINE FIRE WARNING CAME ON. THE THROTTLES WERE RETARDED AND THE WARNING EXTINGUISHED. THE	 AC RETURNED TO AIRPORT.  AFTER INVESTIGATION, MAINTENANCE FOUND THE DUCT FOR THE FUEL HEAT VALVE HAD COME OUT OF ITS SL	EEVE CAUSING A DUCT LEAK. THE DUCT WAS REPAIRED AND LEAK CHECKED SERVICEABLE. (TC NR 20080328011)				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
	20080521		EA  	2008	5	21	CA080331001      	1	20080317	G	5711	21531062212	FRAME           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	FS 434.80	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2531 	2531 							(CAN) WHILE PERFORMING AD CF-1997-07R2, NDT INSP OF FRONT AND REAR SPAR WING TO FUSELAGE FRAME ANGLES A CRACK WAS DETECT	ED ON THE REAR LT OB ANGLE. THE CRACK ORIGINATED AT THE TOP HI-LOK AND WAS HEADED UP ABOUT .1250 TH OF AN INCH. IT COULD	 NOT BE DETECTED BY THE NAKED EYE.  THE AD WAS ACTUALLY DUE AT A/F TIME 2573.4 AND WATER DROPS 9726.  WE PERFORMED IT DU	RING WINTER MAINT AT A/F 2530.8 AND 9521 WATER DROPS.  APPROVED REPAIRS WILL BE CARRIED OUT AND THE AC RELEASED FOR SERV	ICE. (TC NR 20080331001)		2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
	20080521		CE  	2008	5	21	CA080331002      	1	20080312	G	2510	505530401	CABLE ASSY      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSTALLATION OF SERVICE KIT SK210-175 - SECONDARY SEAT STOP, IT WAS FOUND THAT THE THREADS ON THE HOUSING F	OR THE ADJUSTMENT CABLE WERE CRACKED. (TC NR 20080331002)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20080521		EA  	2008	5	21	CA080331003      	1	20080317	G	5711	2151003268	SPAR CAP        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2531 	2531 							(CAN) WHILE PERFORM AD CF-1992-26R1, ULTRA SONIC INSPECTION OF THE WING REAR SPAR CAP, CRACKS WERE INDICATED ON BOTH REA	R SPAR CAPS. VISUAL INSPECTIONS WERE CARRIED OUT AND CRACKS DISCOVERED ON BOTH SPAR CAPS AT WS 51.00 FS 434.80.   THIS A	D WAS DUE AT A/F TIME 2651.3 AND WATER DROPS 9820. WE CARRIED IT OUT DURING WINTER MAINT AT A/F TIME 2530.8 AND WATER DR	OPS 9521.  THE AC MFG WAS CONTACTED AND APPROVED DRAWINGS SENT SHOWING REPAIRS. (TC NR 20080331003)			2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
	20081105		NE  	2008	11	5	CA080331004      	2	20080319	G	7314	C8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					AUX FUEL	NOISY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			860  								(CAN) AUX FUEL PUMP HAD EXCESSIVE NOISE THE PUMP WAS REPLACED. (TC NR 20080331004)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080521		EA  	2008	5	21	CA080331006      	1	20080328	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			25226	25226							(CAN) FLAP FAILED ON APPROACH , LT FLAP INDICATING 3 DEG , RT INDICATING 4 DEG  PARTIAL FLAP LANDING CARRIED OUT.  MAINT	 ACTIONS : ALL 8 FLAP ACTUATORS REPLACED IAW COMPANY FLAP FAIL POLICY. (TC NR 20080331006)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080521		NM  	2008	5	21	CA080331007      	1	20080327	G	5753	17039312001	FLAP TRACK      			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					TE FLAPS	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3862 								(CAN) UPON INSP OF THE IB FLAP TRACK RAILS, GOUGES ARE EVIDENT ON THE UPPER INNER SURFACE FACE AND ON THE UPPER SIDE FAC	E THAT ARE OUT OF LIMITS. SEE ALSO SDR 20080318006 FOR DETAILS.   RAIL AFT, RAIL, RAIL MAIN 1, RAIL MAIN 2 OUT PN:  170-	39320-001, 170-39060-01, 170-39310-001, 170-39312-001  DUE TO NO ALLOWABLE REWORK LIMITS AVAILABLE IN THE SRM (STRUCTURA	L REPAIR MANUAL) , ALL C/A  CARRIED OUT IAW MFG INSTRUCTION. REF: IC2007-17005998C, IC2008-17002015A, IC2008-17002163. (	TC NR 20080331007)		2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20080521		EU  	2008	5	21	CA080331008      	1	20080325	G	3600		B-NUT           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CRACKED	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA			7625 								(CAN) FOLLOWING AN ANNUAL INSP AND A SATCOM AVIONICS UPGRADE IN THE INITIAL CLIMB PHASE OF A TEST FLIGHT , CABIN PRESSUR	E WAS INCREASING AT A MAXIMUM RATE. ECS WAS PROMTPLY SHUTDOWN ,CABIN DUMPED, AC LEVELED OFF AND RETURNED TO AIRPORT FOR 	LANDING. THE SENSE LINE FROM THE CONTROLLER TO THE AUXILLARY VOLUME TANK WAS FOUND TO HAVE A CRACKED B-NUT. UPON A SLIGH	T TUG , NUT SEPARATED COMPLETLY AND LINE COULD BE PULLED COMPLETLY FROM FITTING. A NEW LINE WAS INSTALLED , SUBSEQUENT G	ROUND RUNS AND TEST FLIGHT PROVED SATISFACTORY. SOME OF THE WIRING NECESSARY FOR THE PROJECTS LEADING UP TO THIS INCIDEN	T WAS CARRIED OUT IN THIS AREA (UPPER FIREWALL).  IT IS BELIEVED THAT THE LINE MAY HAVE BEEN DISTURBED IE TYWRAPS, PERHA	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080521		EA  	2008	5	21	CA080331009      	2	20080320	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			469  	469  							(CAN) DURING A ROUTINE INSP, THERE WAS EVIDENCE OF A CRACK LOCATED AROUND THE INTAKE HSG. THE VALVE COVER WAS REMOVED AN	D FURTHER VISUAL INSP REVEALED THE INTAKE VALVE WAS HITTING THE SIDE OF THE INTAKE HOUSING. WE FEEL THE CONSTANT HITTING	 OF THE HOUSING CAUSED A STRESS CRACK. CYLINDER WAS REPLACED. (TC NR 20080331009)				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20080521		EA  	2008	5	21	CA080401001      	1	20080327	G	7830	W31G1120	WIRE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  										THRUST REVERSER	BROKEN          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ABOUT 20 MINUTES BEFORE EXPECTED ARRIVAL , RECEIVED THAT THERE WAS REV UNLOCKED MESSAGE ON EICAS IN FLIGHT, THE CR	EW ACCORDING TOOK QUICK CHECKLIST OPERATION, SHUTDOWN THE LT ENGINE MANUALLY, DID SINGLE ENGINE LANDING PROCEDURES.  STA	RTED THE TROUBLESHOOTING. CHECKED THE PDU, ETC. FINALLY, FOUND THE PROBLEM, THE WIRE OF THE W31G/1/1-20 OF THROTTLE LOCK	OUT THROTTLE LOCKOUT WAS BROKEN, THE BROKEN WIRE WAS TOO SHORT,  (ALL THE WIRE SHOULD HAVE THE SAME LENGTH NORMALLY) THE	Y SHOULD BE RIGGED TO MAKE SURE EVERYTHING WOULD BE OK, WE CHANGED THE THROTTLE LOCKOUT MICROSWITCH REF AMM78-37-01, AND	 REF ESPM20-16-10C, DID THE SOLDER SLEEVE WIRE SPLICING OF THROTTLE LOCKOUT MICROSWITCH, TESTING IS NORMAL BETWEEN EVERY	2	L	7	2 	4F			RT	A21EA   					 
	20080521		NE  	2008	5	21	CA080401002      	2	20080313	G	7230	806101	BLADE           			BOEING	727   	72722C      	138400F	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18651	2963 							(CAN) WHILE PERFORMING AC DAILY INSP, NR (3) ENGINE C-1 FAN ASSY WAS FOUND TO HAVE SUBSTANTIAL DAMAGE TO (3) BLADES. THE	 (3) BLADES HAD SIGNIFICANT L/E DEFORMATION WITH ONE EXHIBITING VISUAL CRACKING. THE C-1 FAN WAS REMOVED FROM SERVICE AN	D REPLACED.  THE AC WAS INSPECTED IAW MFG ABNORMAL OCCURRENCE "BIRD STRIKE".  NO FAULTS WERE FOUND.   IT HAD BEEN OBSERV	ED AT THE END OF THE PRECEDING FLIGHT THAT ICE ACCUMULATION FALLING FROM THE EMPENNAGE AFTER ARRIVAL AND SHUTDOWN. IT IS	 SPECULATED THAT INGESTION OF ICE AT SOME STAGE OF FLIGHT MAY HAVE OCCURRED. THERE HAD BEEN NO INDICATIONS OF ENG OR AIR	FRAME ABNORMALITIES DURING THE FLIGHT AND THE PROCEEDING DAILY INSP HAD NOT REVEALED THE DAMAGE. (TC NR 20080401002)	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20080602		EA  	2008	6	2	CA080401004      	2	20080326	G	7200		ENGINE          			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  					LEFT	POWER LOSS      	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				4517 							ON TAKEOFF, THE LEFT ENGINE LAGGED BEHIND NOT PRODUCING MAX.  POWER, TROUBLE SHOOTING FOUND THE TEMPERATURE COMPENSATOR 	UNIT LEAKING P3 AIR.  THE PART WAS REPLACED AND THE PROBLEM WAS FIXED. (TC NR 20080401004)					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
	20080602		NM  	2008	6	2	CA080401005      	1	20080401	G	3222		PIN             			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					NLG	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											DURING INSPECTION, FOUND NUT ON LOWER DRAG BRACE ATTACHEMENT HINGE PIN NOT SAFETIED WITH CUTTER PIN AND PRC ADRIFT SEE A	TTACHEMENT.  NO EVIDENCE OF WORK PREVIOUS ACCOMPLISHED ON THE NOSE GEAR.					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20080602		NM  	2008	6	2	CA080401008      	1	20080313	G	3213	2821A000003	STRUT           			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					LT MLG	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2604 	2604 							DURING THE SERVICING OF THE LEFT MAIN GEAR IT AT BEEN NOTICE THAT THE AIR KEPT COMING OUT FROM THE OIL VENT VALVE.  AS P	ER EMBRAER, TO FIX THE PROBLEM THE MAIN GEAR AS TO BE CHANGE AIR CANADA FLEET AS BEEN ADVISED AND SEEMS TO BE A KNOWN CO	NDITION (TC NR 20080401008).				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20080602		NM  	2008	6	2	CA080401010      	1	20080401	G	3232	65C330325	ARM             			BOEING	737   	737490      	1384715	NM  										MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			34053								WHILE PERFORMING CUSTOMER T/C (AD 99-10-12) INSPECTION OF MLG ACTUATOR BEAM ARM, UT INSPECTION FINDS THAT RT MLG ACTUATO	R BEAM ARM IS CRACKED CYCLES/TSN ARE AIRFRAME.  NO EVIDENCE THAT THIS PART HAS BEEN REPLACED SINCE A/C MANUFACTURE. (TC 	NR 20080401010)				2	L	7	2 	4F			RT	A16WE   					 
	20080602		EA  	2008	6	2	CA080402001      	1	20080331	G	3040		HEATER          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					WINDSHIELD	SMOKE           	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE CREW OBSERVED SMOKE IN THE COCKPIT AND QUICKLY NOTICED THAT THE SMOKE WAS COMING FROM THE LT WIN	DSHIELD ELECTRICAL TERMINALS.  THE WINDSHIELD HEATING SYSTEM WAS TURNED OFF AND THE SMOKE STOPPED.  DECISION WAS MADE TO	 TURN BACK AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  LINE MAINTENANCE DISCOVERED THAT THE LT WINDSHIELD L1 TERM	INAL WIRE NR 3041-48B12C WAS BURNT.  THE RT WINDSHIELD TERMINALS WERE INSPECTED AND THE L2 TERMINAL WIRE NR 3041-40A12NA	 WAS FOUND WITH BURNT MARKS.  BOTH WIRES WERE REPLACED AND THE SYSTEM TESTED SERVICEABLE.  THE AIRCRAFT WAS RELEASED AND	 A VERIFICATION FLIGHT WAS CONDUCTED. (TC NR 20080402001)	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20080602		NE  	2008	6	2	CA080402002      	2	20080305	G	7532		BLEED VALVE     			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					COMPRESSOR	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											THE CREW EXPERIENCED ENGINE VIBRATIONS, FOLLOWED BY AN EEC MANUAL LIGHT.  ENGINE POWER INCREASED AS EXPECTED, BUT THE CR	EW WAS UNABLE TO FURTHER MODULATE POWER BY MOVING THE THRUST LEVER.  THE ENGINE WAS SHUT DOWN AS A RESULT AND THE FLIGHT	 CONTINUED TO PLANNED DESTINATION.  THE COMPRESSOR BLEED VALVE ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVIC	E. THE COMPONENT WILL BE INVESTIGATED AND RESULTS FORWARDED FOR REVIEW. (TC NR 20080402002)			2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20080602		NE  	2008	6	2	CA080402005      	2	20080314	G	7261		TANK            			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	120   	PW120       	 	NE  					ENGINE OIL	LEAKING         	W				E				ENGINE SHUTDOWN         				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	DE	DESCENT        	1			CA											DURING DESCENT, OIL MIST WAS NOTED IN THE CABIN FOLLOWED BY A LOW OIL PRESSURE WARNING INDICATION.  THE ENGINE WAS SHUT 	DOWN BY THE CREW.  TROUBLESHOOTING REVEALED LOW OIL LEVEL IN THE TANK, AND SIGNS OF EXTERNAL OIL LEAKAGE.  THE ENGINE IS	 TO BE REMOVED FOR INVESTIGATION.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.	 (TC NR 20080402005)			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
	20080602		EA  	2008	6	2	CA080402006      	2	20080328	G	8530	72877	TAPPET          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 1 CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1490 							WHEN REPLACING NR 1 CYLINDER THE HYDRAULIC TAPPET BODY WAS FOUND CRACKED IN TWO PLACES. (TC NR 20080402006)						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20080602		EA  	2008	6	2	CA080402007      	1	20080402	G	3150		WARNING LIGHT   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  						ILLUMINATED     	W				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			J			WARNING INDICATION        			DE	DESCENT        	1			CA											AT THE TOP OF DESCENT WHEN PULLING BACK POWER, THE CREW GOT THE "LOW OIL PRES WARNING" ON THE LT ENG, SHORTLY FOLLOWED B	Y THE LOW OIL PRES INDICATION.  ALL OTHER PARAMETERS NORMAL.  CREW THEN ACTIONED EMERGENCY PROCEDURES AND SHUT DOWN LT E	NG AND LANDED. (TC NR 20080402007)				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080602		EA  	2008	6	2	CA080402008      	1	20080314	G	2435		BRUSHES         			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A34      	52043	EA  					STARTER/GEN	WORN            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				379  							STARTER WOULD NOT OPERATE TO START ENGINE. (TC NR 20080402008)						1	H	7	1 	3T	4	T		A806    	E4EA				 
	20080602		NE  	2008	6	2	CA080402010      	2	20080316	G	7320		EEC             			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW124B      	 	NE  					ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											DURING TAKEOFF ROLL, THE ENGINE TORQUE INDICATED 75 PERCENT.  THE TAKEOFF WAS ABORTED AND AIRCRAFT TAXIED BACK TO THE RA	MP.  THE EEC WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.  THE REMOVED UNIT WILL BE RETURNED FOR INVESTIGATION AND UPD	ATES PROVIDED TO TC. (TC NR 20080402010)				2	H	7	2 	4T	4	T	RT	        	E2ONE				 
	20080603		EA  	2008	6	3	CA080402011      	2	20080304	G	7200		ENGINE          			EMB   	312   	EMB312      	       	SO  	PWA   	PT6   	PT6*        	52043	EA  						POWER LOSS      	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											DURING TRAINING MANEUVERS, THE PILOT REPORTED A LOSS OF ENGINE POWER.  PILOT ATTEMPTED TO RECOVER WITHOUT SUCCESS, AND E	JECTED SAFELY.  AIRCRAFT CRASHED IN AN EMPTY FIELD.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF RO	OT CAUSE ONCE ESTABLISHED.				1	L	7	1 	4T	3	T	RT	        	E2NE				 
	20080602		NE  	2008	6	2	CA080402014      	2	20080321	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						POWER LOSS      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											DURING CLIMB, ENGINE POWER WAS LOST ACCOMPANIED BY A LOUD NOISE.  THE ENGINE WAS SECURED AND THE AIRCRAFT RETURNED TO BA	SE.  INITIAL INVESTIGATION REVEALED SEVERE ENGINE DAMAGE INCLUDING FRACTURE OF THE 2ND STAGE POWER TURBINE BLADES.  P&WC	 WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.  (TC NR 20080402014)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20080602		NE  	2008	6	2	CA080402017      	2	20080327	G	7200		ENGINE          			AEROSP	ATR72 	ATR72201    	8680943	EU  	PWA   	PW120 	PW124B      	 	NE  						MAKING METAL    	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											THE OIL PRESSURE INDICATION REDUCED TO ZERO FOLLOWED BY A LOUD NOISE, OIL MIST AND ODOR IN THE CABIN.  THE ENGINE THEN F	LAMED OUT.  INITIAL INSPECTION REVEALED A CONTAMINATED CHIP DETECTOR AND THE PROPELLER DIFFICULT TO TURN.  THE ENGINE IS	 TO BE REMOVED FOR INSPECTION AND UPDATES WILL BE PROVIDED.				2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
	20080602			2008	6	2	CA080402018      	4	20080317	G	6122		GOVERNOR        			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A67B     	52043	NE  					PROPELLOR	MISRIGGED       	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											TAKEOFF WAS ABORTED WHEN THE ENGINE WOULD NOT PRODUCE FULL POWER.  INVESTIGATION REVEALED IMPROPER RIGGING OF THE PROP G	OVERNOR.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
	20080602		NE  	2008	6	2	CA080402019      	2	20080401	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											THE CREW HEARD A LOUD NOISE ACCOMPANIED BY AN AIRCRAFT YAW.  UPON POWER REDUCTION, THE ENGINE SHUT DOWN BY ITSELF.  INIT	IAL INVESTIGATION REVEALS SEVERE INTERNAL ENGINE DAMAGE.  THE ENGINE WILL BE INVESTIGATED AND UPDATES WILL BE PROVIDED. 	(TC NR 20080402019)				2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20080602		EA  	2008	6	2	CA080403002      	1	20080331	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  						MALFUNCTIONED   	W				L				ABORTED APPROACH        				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA			24045								THE POST MAINTENANCE TEST FLIGHT WAS UNSUCCESSFUL. THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE ON APPROACH WHEN THE FL	APS WERE SELECTED FROM 0 TO 8 DEGREES.  THE FLAP ELECTRONIC CONTROL UNIT (FECU) CODES WERE RETRIEVED. THE RT BRAKE AND P	OSITION SENSOR UNIT (BPSU) WAS REPLACED AND RIGGED, THE LT BPSU WAS RE-RIGGED AND THE FECU WAS REPLACED FOR TROUBLESHOOT	ING.  THE AIRCRAFT WAS RELEASED AND COMPLETED A SUCCESSFUL TEST FLIGHT.  RT BPSU, P/N 855D100-9, S/N 372, TSN 24045:44, 	CSN 13150, TSR 20:02, CSR 12. FECU, P/N 601R93050-7, S/N 331, TSN 14405:58, CSN 10815, TSR 7938:28, CSR 6408. (TC NR 200	80403002)	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080602		WP  	2008	6	2	CA080403003      	2	20080331	G	7310	8945682	TUBE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R	K		PARTIAL RPM/PWR LOSS      	FLUID LOSS                		CL	CLIMB          	1			CA											DURING TAKEOFF, THE CREW NOTED THE LT ENGINE WAS A LITTLE LOW ON POWER.  DECIDED TO RETURN TO THE AIRPORT AS THE FUEL FL	OW INDICATION FOR THAT ENGINE WAS ERRATIC.  THE LANDING WAS UNEVENTFUL.  ONCE ON THE GROUND THE AIRCRAFT WAS INSPECTED B	Y MAINTENANCE AND THEY DETERMINED THE LINE FROM THE FUEL FLOW TRANSMITTER TO THE FUEL FLOW DIVIDER HAD SPLIT AT A BEND R	ADIUS IN THE TUBE CAUSING A SOMEWHAT LARGE FUEL LEAK.  THE LEAK WAS ENOUGH TO AFFECT ENGINE PERFORMANCE.  THE LINE WAS F	OUND TO BE INSTALLED CORRECTLY WITH NO EXISTING DAMAGE TO THE LINE OR AREA OF THE SPLIT.  THE AGE OF THE LINE COULD NOT 	BE ACCURATELY DETERMINED BUT IT WAS IN VERY GOOD CONDITION AND THE PART NUMBER WAS CORRECT FOR THE ENGINE INSTALLATION. 	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20080602		SW  	2008	6	2	CA080403005      	1	20080331	G	5610	2621126905	WINDSHIELD      			SWRNGN	SA226 	SA226T      	8780122	SW  	GARRTT	TPE331	TPE33110U   	01514	WP  					COCKPIT	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			W			INADEQUATE Q C            			CR	CRUISE         	1			CA			1986 								IN LEVEL CRUISE AT FLIGHT LEVEL 220 APPROXIMATELY 25 MINUTES AFTER DEPARTURE, THE LEFT HEATED WINDSHIELD SUDDENLY SHATTE	RED.  ATC WAS ADVISED AND DESCENT REQUESTED FOLLOWED BY REQUEST FOR RETURN TO CYWG.  AFTER ESTABLISHING THE RETURN COURS	E AND LEVELING AT 9000 FEET, THE PASSENGERS WERE BRIEFED AND THE AIRCRAFT PROCEEDED BACK AT REDUCED CRUISE SPEED AND COM	PLETED A NORMAL LANDING.  UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLATION, ALL ATTACHING 	HARDWARE WAS CORRECT.		2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
	20080602		EU  	2008	6	2	CA080403007      	1	20080319	G	2121		BEARING         			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					RECIRC FAN	OVERHEATED      	W				B				EMER. DESCENT           				M	B	J	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA			19565								NEAR TOP OF CLIMB, COCKPIT ODOR OF ACRID BURNING SMELL NOTICED.  NO ECAM OR VISUAL CUES.  DURING CRUISE CHECK NOTICED FA	N IN AMBER DISPLAYED ON COND PAGE.  RECYCLED CAB FAN AND SMELL REOCCURRED IMMEDIATELY.  RETURNED TO AIRPORT.  THE SHOP R	EPORT INDICATED THAT THE REAR BEARING SEIZED, THE FRONT BEARING WAS DRY, THE FAN OVERHEATED BUT THE STATOR WAS ELECTRICA	LLY NORMAL.  THE FAN WAS DIRTY AND SMELLED OVERHEATING.			2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
	20080602		NE  	2008	6	2	CA080403008      	2	20080401	G	8550	100243	SHAFT           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE OIL	SHEARED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA				946  							(CAN) JUST BEFORE TURNING BASE LEG FOR LANDING THE RT BMEP GAUGE FELL TO ZERO.  NO OIL WAS OBSERVED LEAKING FROM ENGINE 	ALTHOUGH THE OIL QUANTITY WAS SLOWLY FALLING.  LANDING WAS CARRIED OUT NORMALLY.  ON ROLL OUT QUANTITY WAS READING 8 GAL	LONS, SO THE RT ENGINE WAS SHUT DOWN.  MAINTENANCE DISCOVERED THAT THE SCAVENGE PUMP HAD INGESTED A PIECE OF A CASTLE NU	T WHICH HAD BROKEN OFF ONE OF THE NUTS P/N 542 FROM ONE OF THE REDUCTION PINION GEAR SHAFTS.  THIS HAD CAUSED THE FAILUR	E OF THE GEAR/SHAFT P/N 100243 IN THE ACCESSORY DRIVE CASE.		2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
	20080602		NE  	2008	6	2	CA080403009      	2	20080116	G	8520	128495	MAIN BEARING    			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	MASTER ROD	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1474 							DURING INSPECTION METAL PIECES FOUND IN ENGINE SUMP.  INVESTIGATION DETERMINED THEM TO BE PART OF FLANGE OF MASTER ROD B	EARING.  ENGINE REMOVED FOR OVERHAUL.					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P736	 
	20080602		GL  	2008	6	2	CA080404001      	1	20080303	G	5310	C2TP63ND	SPAR            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											WHEN REPLACING FRONT CENTER SPAR DUE CRACK.  REAR CENTER SPAR DISCOVERED CORRODED BEHIND CENTER MOUNT BRACKET.  SPAR REP	LACED.  THIS CORROSION WAS NOT VISABLE UNTIL ACCESS TO INSIDE OF TAILPLANE WAS GAINED (TC NR 20080404001)					1	H	7	1 	3R	3	R	RC	A806    	5E1				 
	20080602		SW  	2008	6	2	CA080404002      	1	20080326	G	2913		SHAFT           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					HYD PUMP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1155 							DURING A ROUTINE INSPECTION OF THE HYDRAULIC PUMP, THE RETAINING BOLT WHICH HOLDS THE SPLINE DRIVE INTO THE HYDRAULIC PU	MP HAD SHEARED.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20080602		NM  	2008	6	2	CA080404004      	1	20080402	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYDRAULIC SYS	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1339 								DURING CRUISE FL 120, NR 2 ENG HYD PRES CAUTION LIGHT ILLUMINATED.  HYD NR 2 PRESS - 0 PSI - AFTER PERFORMING ABNORMAL C	HECKLIST WITH PTU ON, PRESS 3000 PSI.  UNEVENTFUL LANDING.  MAINTENANCE CREW REPLACED THE NR 2 ENGINE DRIVEN HYDRAULIC P	UMP.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20080602		EA  	2008	6	2	CA080404005      	1	20080331	G	2823	39423091	SHUTOFF VALVE   			DHAV  	DHC3  	DHC3        	2800202	EA  	GARRTT	TPE331	TPE33110R   	0517	WP  					FUEL SYSTEM	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				77   							ENGINE WOULD NOT SHUT DOWN USING NORMAL SHUT DOWN PROCEDURES.  EMERGENCY SHUTOFF PROCEDURES USED.  TROUBLESHOOTING FOUND	 FUEL SHUTOFF VALVE U/S (SOLENOID STICKING).  REPLACED FUEL SHUTOFF VALVE.  ENGINE RUN-UP AND SHUT DOWN NORMAL.  AIRCRAF	T RETURNED TO SERVICE.				1	H	7	1 	3R	4	T		A815    	E4WE				 
	20080602		NM  	2008	6	2	CA080404006      	1	20080331	G	2420	1701320	GENERATOR       			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					APU	FAULTED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA			2802 								ON FIN 309 WHILE T/S A LONG HISTORY FAULT OF APU GEN FAULT.  ARCING WAS FOUND AT THE LUG T3 ATTACH POINT WITH THE APU GE	NERATOR.  APU GENERATOR WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20080602		SO  	2008	6	2	CA080404007      	1	20080329	G	4990	GTCP36150G	APU             			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAYMK6118   	 	NE  						LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			5558 	21   							APU AUTO SHUT DOWN WITH LOW OIL PRESSURE FAULT.  OIL QTY RE-ADJUSTED AND APU STILL SHUT DOWN FOR LOW OIL PRESSURE.  REPL	ACED OIL PRESSURE SWITCH AND APU STILL SHUT DOWN INTERMITTENTLY.  AFTER TROUBLE SHOOTING WITH DIRECT OIL PRESSURE GAUGE 	FOUND OIL PRESSURE DELIVERY WITH INTERMITTENT LOW OIL PRESSURE READING.  SUSPECTING OIL PUMP OR PRESSURE REGULATOR.  LOA	NER APU INSTALLATION IN PROGRESS, MORE INFO WILL BE GIVEN WHEN REPORT OF REPAIR SHOP WILL BE GIVEN.			2	L	7	2 	4F	4	F	RT	A12EA   	A25NE				 
	20080602		CE  	2008	6	2	CA080404009      	1	20080404	G	2510		CABLE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	PILOT SEAT	OUT OF ADJUST   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											FLIGHT CREW DISCREPANCY, PILOTS SEAT DOES NOT SLIDE BACK INTERMITTENTLY.  SEAT REMOVED AND VISUALLY INSPECTED.  REEL ASS	EMBLY CABLE ADJUSTED AND SEAT FUNCTION TESTED WITH NO DEFECTS FOUND.  SEVERAL AIRCRAFT IN OUR FLEET OF CESSNA 100 SERIES	 AIRCRAFT HAVE EXPERIENCED SIMILAR DISCREPANCIES, AND THE PASSENGER SEATED WAS UNABLE TO EXIT THE CABIN.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20080602		NE  	2008	6	2	CA080406001      	2	20080331	G	7321	0301037950	LINE            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											TUBE WAS DISCOVERED CRACKED AND SEPARATED FROM FLARE AT P2 TAP END DURING ROUTINE INSPECTION.  ORIGINALLY, BLACK DEPOSIT	S WERE NOTICED AT B-NUT AND WHEN DISASSEMBLED, FOUND COMPLETE FAILURE OF TUBE FROM FLARE END.  CLOSE TOLERANCE FIT OF TU	BE PROBABLY PROHIBITED ANOMALY FROM BEING NOTICED EARLIER.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
	20081105		NE  	2008	11	5	CA080407001      	2	20080404	G	7200	C632A2116102	HOUSING         			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5291 								(CAN) CRACK INDICATION FOUND ON UPPER RT AREA OF INPUT HOUSING BOSS. THIS WAS FOUND DURING OVERHAUL OF THE MODULE.  PART	 SENT TO MFG FOR EVALUATION.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
	20080602			2008	6	2	CA080407002      	1	20080331	G	3297	472011	WIRE HARNESS    																	NLG WOW	MISINSTALLED    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											AN OPERATOR FOUND THAT DURING INSTALLATION OF MOD SUM 4-125401, FINDING THE NEW HARNESSES PN.47201-1 THREE OUT OF SIX HA	RNESSES PULLED FROM STOCK WERE MISS WIRED.  ON CONNECTOR 3261-P32 PINS A-B AND D-E WERE WIRED REVERSED.  HARNESSES APPRO	PRIATELY REPAIRED IAW MANUFACTURER PROVIDED DATA AND RETURNED TO STOCK.  TO ADDRESS THIS ISSUE, SERVICE LETTER DH8-SL-32	-014A ADVISING OF POSSIBLE MANUFACTURING FAULTS WAS RAISED.																 
	20080602		EA  	2008	6	2	CA080407003      	1	20080406	G	2752	852D1001921	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					FLAP	UNSERVICEABLE   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			CA											ON APPROACH AT 4000 FT SELECTING FLAPS FROM 0 - 8 DEG, FLAP FAIL MSG APPEARED IMMEDIATELY WITH NO MOVEMENT OF FLAPS.  AI	RSPEED 215 AT THE TIME.  A/C WAS AT -57 DEG FOR 1 HR IN CRUISE, GND -4.  FECU INTERGRADED AND FOLLOWING FAULT CODES DISP	LAYED AS FECU WAS LOOKED AT: (1) JAM (2) LEFT BPSU (3) 1 5 1B.  TRIED TO GO FURTHER AFTER THE STEP OF `GO` IN THE FIM AN	D IT WOULD GIVE THE FAULT CODE 1 5 1B  CB 1-F4 AND CB 2-F4 AND SYSTEM RESET WITH NO FURTHER FAULTS.  FERRY FLIGHT PAPERW	ORK COMPLETED.  A/C FERRIED.  TROUBLESHOOTING GOING ON, ACTION PLAN TO INSPECT AND LUBE ALL DRIVES AND CHANGE ALL FLAP A	CTUATORS WITH NEWLY OVERHAULED UNITS SENT.  INFORMATION WILL BE UPDATED WHEN AVAILABLE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20080602		GL  	2008	6	2	CA080407004      	1	20080404	G	3234	1760A000004	LEVER           			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					MLG	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											AFTER TAKEOFF, IT WAS REPORTED THAT THE CREW WERE UNABLE TO RETRACT THE FLAPS FROM THE 10 DEGREE POSITION TO THE 0 DEGRE	E POSITION.  PRELIMINARY REPORT STATES THAT A LOOSE SCREW WAS FOUND INSIDE THE FLAP LEVER GUARD.  THE FORWARD RIGHT SCRE	W LOCATED INSIDE THE GUARD WAS FOUND TO BE PROTRUDING SUFFICIENTLY TO PREVENT THE LEVER FROM MOVING FROM THE 10 DEGREE P	OSITION TO THE 0 DEGREE POSITION.  ALL THREE REMAINING SCREWS WERE FOUND TO BE SECURE.  A VISUAL AND TACTILE INSPECTION 	CAN BE PERFORMED TO ENSURE THAT ALL 4 SCREWS LOCATED INSIDE THE FLAP LEVER GUARD ARE SLIGHTLY COUNTERSUNK AND DO NOT SHO	W ANY SIGNS OF LOOSENESS (REFER TO FIGURE1).  PLEASE REPORT ANY ANOMALIES FOUND DURING THIS INSPECTION.	2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
	20080602		EA  	2008	6	2	CA080407005      	2	20080403	G	7200	PT6A20	ENGINE          			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		STOPPED         	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CA			11786	4634 							AFTER A NORMAL TAKEOFF, THE CREW WENT THROUGH POWER 1, FLAPS UP AND POWER 2 AND AFTER SETTING POWER 2 PRIOR TO CLIMB CHE	CKS, THE CREW HEARD A LOUD POP AND SCRAPPING NOISE FROM THE NUMBER ONE ENGINE.  THE FLIGHT CREW OBSERVED THAT THE NUMBER	 ONE PROPELLER WAS STOPPED AND ALL ENGINE GAUGES WERE AT ZERO.  EMERGENCY CHECKLIST WAS FOLLOWED AND THE AIRCRAFT LANDED	 SAFELY WITH ONE ENGINE RUNNING.  ENGINE TO BE REMOVED FOR EVALUATION BY REPAIR FACILITY.			1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081105		EU  	2008	11	5	CA080407006      	1	20080405	G	2913	A5026780	PUMP            			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	60037	NE  					HYDRAULIC SYS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			2763 	2763 							(CAN) DURING NORMAL FLIGHT DURING A BIRD TOWING OPERATION THE PILOT RECEIVED A BING INDICATING A FAILURE. AIRSPEED 60KTS	, 1000 FT AGL, 170 FT LINE WITH BIRD, 45 MINUTES INTO FIRST FLIGHT OF THE DAY:  " BING " HEARD IN HEADSET, HYD WARNING L	IGHT OBSERVED, NOTICE CHANGE OF FEEL TO THE CYCLIC CONTROL (ACCUMULATORS ACTIVATED) CHECKED THAT BOTH HYD SWITCHES HAD N	OT BEEN INADVERTENTLY ACTIVATED. OBSERVED AIRSPEED 60KTS, SWITCHED HYD CUT OFF TO ON POSITION, CONTINUED TO DECENT TO A 	LAKE, SET UP FLAT APPROACH WITH BIRD.  RADAR ALT INDICATED BIRD WAS 5 FT OFF GROUND LOAD WAS JETTISONED AT 25KTS IAS  PO	SITION FOR A SECOND APPROACH AND LANDED HELICOPTER WITHOUT INCIDENT THE HYDR PUMP WAS REPLACED AFTER AND ACFT WAS TEST F	1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20080602		SW  	2008	6	2	CA080407007      	1	20080405	G	6322	R476204971	GEAR SET        	BELL        	4762060025  	BELL  	47    	47G4        	1181030	SW  	LYC   	O540  	VO540B1B3   	41532	EA  					COOLING FAN	SHEARED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA			77   								APPROX 100 HRS AGO TRANSMISSION WAS O/H AND NEW PMA GEAR SET WAS INSTALLED S/N GR586A FROM HELICOPTER TECH DURING FLIGHT	 PILOT HEARD AND FELT NOISE AND MADE A PRECAUTIONARY LANDING AND FOUND COOLING FAN DRIVE PULLEY AND APPROX 1.25 INCHES O	F THE DRIVE SHAFT WAS MISSING.  WE ARE SENDING IN REMAINING SHAFT SEGMENT WHERE IT SHEARED FOR METALLURGICAL ANALYSIS.				1	G	7	1 	3O	3	O		2H3     	E304				 
	20080602		EA  	2008	6	2	CA080407010      	1	20080402	G	3250		CABLE           			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	STEERING	BROKEN          	W				D				RETURN TO BLOCK         				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											STEERING CABLE BROKE ON TAXI WHILE THE AIRCRAFT WAS PREPARING FOR TAKEOFF.						1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20080602		EU  	2008	6	2	CA080408001      	1	20080408	G	2520	4030082SRS	ATTACH FITTING  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PAX SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8953 								DURING 100 HOUR INSPECTION PASSENGER SEAT RECLINE HYDRAULIC MOUNT ATTACHMENT FOUND CRACKED.  SEAT MANUFACTURER IS ERDA. 	NOT FOUND IN ASSEMBLY MANUFACTURER LIST.  REPAIR INFORMATION REQUESTED THROUGH AIRCRAFT MANUFACTURER, PILATUS.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20080602		EA  	2008	6	2	CA080408002      	1	20080329	G	2750	70745	CONTROL UNIT    			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C5     	30050	NE  					TE FLAP MOTOR	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			8989 	8989 							PRIOR TO DEPARTURE FLIGHT CREW COMPLETED A STAB TRIM RESET.  SHORTLY AFTER FLAP RETRACTION ON TAKEOFF, FLIGHT CREW RECEI	VED AN AP TRIM IS ND ASSOCIATED WITH AN AP PITCH TRIM CAUTION MESSAGE.  SUBSEQUENTLY CREW RECEIVED A ELEVATOR SPLIT CA	UTION MESSAGE.  CREW FOLLOWED QRH, CIRCLED TO BURN OFF FUEL AND LANDED BACK AT DEPARTURE AIRPORT WITHOUT INCIDENT.  MAIN	TENANCE CHECKED ELEVATOR TRIM POSITION FULL NOSE DOWN, NEUTRAL AND FULL NOSE UP OK.  AUTO PILOT ELEVATOR SERVO OPERATION	 CHECKED OK.  ELEVATOR SPLIT MESSAGE TROUBLESHOT PER FIM TASK OK.  PROBLEM ISOLATED AS MDC DISPLAYED AN INTERNAL FAULT O	F THE MOTOR CONTROL UNIT CHANNEL 2 INTERNAL HOLD ON RELAY.  MOTOR CONTROL UNIT REPLACED.  OPERATIONAL TESTS OF THE SSCU,	2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20080602		NM  	2008	6	2	CA080408003      	1	20080404	G	2130		CABIN PRESSURE  			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				G			MULTIPLE FAILURE          			CL	CLIMB          	1			CA											AIRCRAFT C-GTDX DEPARTING FROM YYZ ON APRIL 4TH 2008, AROUND 7000 FT AN EICAS MSG AUTO PRESSURIZATION SYS 1 AND 2, AIRCR	AFT RETURNED BACK TO YYZ AND REQUESTED FIRE TRUCKS ON ARRIVAL DUE TO OVERWEIGHT LANDING.  TROUBLESHOOTING CARRIED OUT, B	OTH PRESSURIZATION CONTROL UNITS AND STBY ALTIMETER REPLACED AS PRECAUTIONARY MEASURE.  FLIGHT TEST CARRIED OUT SUCCESSF	ULLY.  INVESTIGATION IS ON GOING.			2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
	20080602		EA  	2008	6	2	CA080408004      	1	20080330	G	3230	101655	UPLOCK ROLLER   			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RH MLG	SEIZED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			35895	20079							RT MLG FAILED TO EXTEND ON LANDING GEAR SELECTION, CREW PERFORMED GO-AROUND AND USED ALTERNATE GEAR EXTENSION.  ALL LAND	ING GEAR EXTENDED AND NORMAL LANDING CARRIED OUT.  MAINTENANCE INSPECTION FOUND RT MLG UPLOCK ROLLER SEIZED, ROLLER REPL	ACED, GEAR SWINGS COMPLETED AND AIRCRAFT RETURNED TO SERVICE.  TIMES PROVIDED ARE SHOCK STRUT TIMES, ROLLER IS NOT SERIA	LIZED AND NOT TRACKED FOR ACTUAL TIMES.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080602		EU  	2008	6	2	CA080409001      	1	20080325	G	2597	40900011	WIRE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					COFFEEMAKER	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			4341 	483  							IN CRUISE AFT GALLEY RT COFFEEMAKER BURNED.  ALL C/BS WERE PULLED.  HALON FIRE EXTINGUISHER WAS USED AS A PRECAUTIONARY	 MEASURE.  C/B ON COFFEE MAKER FOUND POPPED.  FOUND WIRES TO PRESSURE SWITCH BURNED AND DISCONNECTED.  NO OTHER WIRING D	AMAGE ON THE COFFEE MAKER.  COFFEE MAKER REPLACED AND ROUTED TO SHOP FOR REPAIR.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20080602		EU  	2008	6	2	CA080409003      	1	20080407	G	2133		OUTFLOW VALVE   			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					CABIN PRESSURE	MALFUNCTIONED   	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											AFTER 30 MIN IN CRUISE, CAB PRESSURE REG NR 2 FAULT, FOLLOWED BY CAB PRESSURE REG NR 1 FAULT.  UNABLE TO CONTROL IN MANU	AL.  EMERGENCY DESCENT AND QAR PROCEDURES FOLLOWED.  PAX MASK SYSTEM ACTIVATED IN AUTO.  FLIGHT RETURNED TO STATION AT F	L 10,000 FT.  ACFT WAS REMOVED FROM SERVICE FOR INVESTIGATION.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20080602		EA  	2008	6	2	CA080409004      	1	20080330	G	3040	601R3303313	CONTROLLER      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					WINDSHIELD TEMP	OVERTEMP        	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			14325	14325							ON DESCENT THROUGH 21000 FEET INTO ARRIVAL AIRPORT, CAPTAINS LT WINDSCREEN SHATTERED.  CREW DONNED OXYGEN MASKS AS A PR	ECAUTION.  CREW DECLARED AN EMERGENCY WITH ATC AND MADE ANNOUNCEMENT TO THE PASSENGERS.  FLIGHT LANDED WITHOUT INCIDENT.	  MAINTENANCE REPLACED THE WINDSHIELD ASSEMBLY P/N 601R33033-13, S/N 01057H1890, TIMES AND CYCLES SAME AS THE TEMPERATUR	E CONTROLLER.  MAINTENANCE ALSO REPLACED THE LT WINDSHIELD TEMPERATURE CONTROLLER SUSPECTING THAT IT HAS CAUSED AN OVERH	EAT CONDITION.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081105		SW  	2008	11	5	CA080409005      	1	20080409	G	2450	MS2207375	CIRCUIT BREAKER 			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					OVERHEAD PANEL	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING A PREFLIGHT CHECK DURING FLIGHT TRAINING IT WAS NOTED THAT THE LT BOOST PUMP CIRCUIT BREAKER WAS NOT A	BLE TO BE CYCLED. THE CIRCUIT BREAKER WAS REMOVED AND REPLACED. AFTER GOING THROUGH THE REST OF THE CIRCUIT BREAKER PANE	L IS WAS NOTED THAT IN EXCESS OF 20 BREAKERS WERE DIFFICULT TO OR UNABLE TO BE CYCLED. REQUIRED CIRCUIT BREAKERS WERE RE	PLACED. INSPECTION CRITERIA TO NOW INCLUDE CYCLING BREAKERS AT INTERVALS TO REDUCE THE CHANCE OF A BREAKER NOT POPPING W	HEN REQUIRED AND CAUSING FURTHER PROBLEMS/DAMAGE. (TC NR 20080409005)		1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20080602		EA  	2008	6	2	CA080409006      	2	20080330	G	7230		BLADES          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COMPRESSOR TURB	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			AP	APPROACH       	1			CA											ON APPROACH, THE CREW NOTED ENGINE TEMP AT APPROX 900 DEGREES FOLLOWED BY SOME NOISES.  THE ENGINE WAS SHUTDOWN AND THE 	AIRCRAFT LANDED.  INITIAL INVESTIGATION REVEALED LOSS OF COMPRESSOR TURBINE BLADE MATERIAL AND SHROUD SEGMENT MATERIAL, 	THE ENGINE WAS SENT FOR REPAIR.				1	G	7	2 	4U	4	U		H4SW    	E22EA				 
	20080602		EA  	2008	6	2	CA080409008      	1	20080409	G	5210	33130131	PISTON          			CNDAIR	CL215 	CL2151A10   	1900320	EA  										ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4499 								ANOTHER OPERATOR INFORMED OUR QUALITY ASSURANCE DEPARTMENT OF THEIR FINDING CRACKS IN THE ACTUATOR THREADED PORTION IN 5	 OUT OF 7 ACTUATORS.  INSPECTED ALL 14 OF OUR FLEET ACTUATORS AND FOUND 4 TO BE CRACKED ALSO.					2	H	7	2 	4R			RT	A14EA   					 
	20081105		NE  	2008	11	5	CA080410004      	2	20080401	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			881  								(CAN) DURING A DAILY INSP OIL WAS FOUND LEAKING FROM THE ENGINE DRIVEN FUEL PUMP, PART WAS REMOVED AND REPLACED (TC NR 2	0080410004)					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080602		EA  	2008	6	2	CA080410005      	1	20080408	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					RT FLAP SYS	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			3291 								ON DESCENT, CREW SELECTED AND RECEIVED FLAPS 8 DEGREES, WHEN THEY ATTEMPTED TO PROCEED TO FLAPS 20 CREW RECEIVED A FLAP 	FAIL MESSAGE.  FLIGHT LANDED WITHOUT INCIDENT.  FECU MESSAGE POINTED TO THE RT BPSU AS THE FAULT.  THE RT BPSU WAS REPLA	CED, FLAP SYSTEM RIGGED AND FUNCTION CHECKED SERVICEABLE.  THE A/C RETURNED TO SERVICE WITH NO FURTHER FAULTS.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081105		WP  	2008	11	5	CA080410006      	1	20080409	G	6310		SHAFT           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CLUTCH	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1998 								(CAN) CLUTCH WAS REMOVED FOR GRINDING NOISE ON GROUND RUN. DURING DISASSEMBLY THE OIL IN THE CLUTCH WAS VERY BLACK DUE T	O INTERNAL WEAR OF THE SHAFT, HSG AND SPRAG. THE SPRAG CAGE CROSSBAR WAS CRACKED, PEANUT INNER EARS WERE BROKEN OFF, WEA	R ON THE INNER SURFACE OF THE PEANUTS (POSSIBLE SLIPPAGE) AND EXCESSIVE CAGE WINDOW WEAR.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080602		SO  	2008	6	2	CA080410009      	2	20080312	G	8530	AEC631397SN2B22	CYLINDER HEAD   			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA				105  							PILOT FLYING IN CRUISE FLIGHT, WHEN HE HEARD A POP AND EXPERIENCED LOSS OF ENGINE POWER.  FEATHERED PROPELLER AND LANDED	 AT NEAREST AIRPORT.  ENGINE CYLINDER REPLACED.					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
	20081105		EU  	2008	11	5	CA080411001      	1	20080220	G	6700	D107610E	ACTUATOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TRIM SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACTUATOR FAILED, (WOULD NOT RETRACT) ON PRESTART TEST. FAILED IN THE EXTEN POSITION (CYCLIC FULL FWD) (TC NR 20080	411001)					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
	20080602			2008	6	2	CA080411002      	4	20080409	G	6122	210332	PILOT VALVE     	WOODWARD    																GOVERNOR	DAMAGED         	W				O				OTHER                   				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			CA			97   								THE GOVERNOR WAS MANUFACTURED BY ONTIC, ONTIC HAS THE MANUFACTURING RIGHTS TO THE FORMER WOODWARD GOVERNOR COMPANY PISTO	N ENGINE GOVERNORS.  THE GOVERNOR WAS RECEIVED FROM THE AIRCRAFT MANUFACTURE, DIAMOND AIRCRAFT INDUSTRIES, FOR REPAIR IN	 APRIL 2008.  ACCORDING TO A CUSTOMER CLAIM/RETURN AUTHORIZATION FORM RECEIVED FROM DIAMOND, THE GOVERNOR WAS REMOVED FR	OM AIRCRAFT SERIAL NR 40.438 ON OR ABOUT SEPTEMBER 21, 2005, WITH AIRCRAFT TTSN OF 96.9 HOURS.  WITH ORIGINAL COMPLIANT 	OF ENGINE OVERREVED DURING FLIGHT, COULD NOT CONTROL PROPELLER.  THE NAME PLATE ON THE GOVERNOR GIVES A ASSY DATE OF 08/	04 DURING INSPECTION OF THE GOVERNOR IN OUR SHOP, AFTER REMOVAL OF THE TOP COVER, IT WAS FOUND THAT THE HEAD END HAD SEP														 
	20081105		EU  	2008	11	5	CA080411003      	1	20080220	G	6700	10513142	ROD END         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					BEARING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROD END HAS TEFLON MISSING WITH METAL TO METAL CONTACT (TC NR 20080411003)						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
	20080602		NM  	2008	6	2	CA080411004      	1	20080408	G	2910	6517840330	LINE            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											AFTER TAKEOFF WHEN GEAR SELECTED UP, HYDRAULIC SYSTEM "A" LOW LEVEL LIGHT ILLUMINATED AND HYDRAULIC QUANTITY DROPPED TO 	2.0 GAL.  FLIGHT CREW DECLARED AN EMERGENCY AND RETURNED FOR APPROACH.  PER FLIGHT CREW CHECKLIST GEAR WAS MANUALLY LOWE	RED HOWEVER FLIGHT CREW WAS UNABLE TO MANUALLY LOWER THE LT GEAR.  TWO ATTEMPTS WERE MADE AND THEN THE FLIGHT CREW SELEC	TED ON ONE "A" SYSTEM HYDRAULIC PUMP TO GET THE LT GEAR DOWN AND LOCKED.  THE PUMP WAS THEN TURNED OFF AGAIN.  THE AIRCR	AFT LANDED SUCCESSFULLY WITH NO ADDITIONAL FAULTS.  MAINTENANCE PERSONNEL FOUND A PIN HOLE LEAK ON THE A SYSTEM HYDRAULI	C RETURN LINE RETURNING FROM THE A SYSTEM HEAT EXCHANGER.  A PERMANENT REPAIR WAS CARRIED OUT BY THE INSTALLATION OF A P	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20080602		GL  	2008	6	2	CA080411006      	2	20080409	G	7250	23063354	TURBINE         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA			4509 	1226 							ON THE THIRD MAIN ROTOR STROBING FLIGHT OF THE MORNING AND WHILE ACCELERATING FROM 100KTS TO 120KTS, A LOW HOWLING NOISE	 WAS HEARD WHICH INTENSIFIED RAPIDLY AND WAS FOLLOWED IMMEDIATELY BY AN ENGINE CHIP LIGHT.  A FORCED LANDING WAS MADE TO	 A FIELD.  AN EXTERNAL INSP INCH BY 4 INCH PIECE OF SHEET METAL WAS FOUND BROKEN AWAY FROM THE AFT RIGHT SIDE OF THE EXH	AUST STACK.  AFTER REMOVAL OF THE OUTER COMBUSTION CASE MAJOR VISIBLE DAMAGE WAS FOUND TO THE 1ST AND 2ND STAGE TURBINE 	BLADE TIPS.  TURBINE SECTION IS BEING SENT TO STANDARD AERO LTD FOR INSPECTION WITH ROLLS ROYCE PARTICIPATION.  1ST AND 	2ND TURBINE WHEEL CYCLES ARE 2004, 3RD AND 4TH STAGE CYCLES ARE 4977.  ENGINE DATA COULD NOT BE DOWNLOADED FROM THE ECU,	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20080602		CE  	2008	6	2	CA080411007      	1	20080407	G	3245	0923150	TUBE            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	NLG WHEEL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			62   								NOSE TIRE FOUND LOW ON POST FLIGHT INSPECTION BY 10 PSI.  NOSE WHEEL ASSY REMOVED FOR TEAR DOWN AND INVESTIGATION.  SPAR	E BUILT-UP WHEEL ASSY INSTALLED.  TEAR DOWN SHOWED INNER TUBE HAD PIN HOLE IN OUTER CIRCUMFERENCE AT ONE END OF A FOLD M	ARK.  NO OTHER FAULTS FOUND WITH TIRE OR TUBE.				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	3PNE	 
	20080603		GL  	2008	6	3	CA080414001      	1	20080407	G	5711		SPAR            			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5796 								CRACKS FOUND WHILE COMPLYING WITH SB2/47.  CRACKS JUST VISIBLE WITH FLUORESCENT PENETRANT INSPECTION.  WHEN SPAR REMOVED	 CRACKS WERE VISIBLE TO NAKED EYE ON THE INTERIOR OF SPAR AND ON GUSSET BETWEEN SPAR AND GUSSET.					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
	20080603		WP  	2008	6	3	CA080414003      	1	20080410	G	2435		GEAR            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			58   								UPON POST FLIGHT INSPECTION, STARTER TEETH FOUND WORN, REMOVED AND INSTALLED NEW STARTER.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080603		WP  	2008	6	3	CA080414004      	1	20080410	G	6310		CLUTCH ACTUATOR 			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1552 								UPON INSPECTION, CARRIED OUT METHOD 2 AND THE ACTUATOR KEPT RUNNING .						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080603		EA  	2008	6	3	CA080414005      	2	20080411	G	7230	3012060	DUCT            								PWA   	PT6   	PT6A27      	52043	EA  						DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											METAL SWARF FOUND INSIDE COOLING PASSAGES OF DUCT ASSY.											4	T			E4EA				 
	20080603			2008	6	3	CA080414006      	4	20080407	G	2210	08071	STATIC LINE     			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	AUTO PILOT SYS	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			697  								DURING RE-ACTIVATION OF THE AIRCRAFT, THE MAINTENANCE CREW NOTICED THAT THE STATIC LINE FOR THE AUTO PILOT ALTITUDE HOLD	 P/N 0807-1 WAS DETERIORATED AND CRACKED.  THE LINE WAS REPLACED WITH A SERVICEABLE PART.  ALL OTHER AIRCRAFT IN THE FLE	ET WILL BE INSPECTED FOR SERVICEABILITY.				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
	20080603		NM  	2008	6	3	CA080414008      	1	20080328	G	3242		BRAKE DISC      	BFGOODRICH  		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG BRAKE ASSY	WARPED          	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			39505	6254 							RAMP CREW NOTICED THAT RT INBOARD (NR 3) MAIN WHEEL WAS FLAT WHILE AIRCRAFT WAS PARKED AT GATE.  MAINTENANCE DISCOVERED 	THE NR 3 BRAKE UNIT WITH A WARPED/OVERHEATED BRAKE DISKS WHICH CAUSED THE FUSE PLUGS ON THE NR 3 MAIN WHEEL TO BLOW.  MA	INTENANCE REPLACED THE NR 3 BRAKE UNIT AND THE NR 3 AND 4 MAIN WHEEL ASSEMBLIES.  TAXI AND FUNCTION CHECKS OF THE BRAKIN	G SYSTEM WERE COMPLETED WITH NO FURTHER FAULTS FOUND.  WHEEL SHOP CONFIRMED BRAKE UNIT DID OVERHEAT AND THAT IT WAS NOT 	A FAULT WITH THE UNIT.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080603			2008	6	3	CA080414009      	1	20080414	G	3110	7003652631	DISPLAY         																	COCKPIT	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FAIL AT INSTALLATION, AND CAME BACK OUT WITH THE SAME PROBLEM THAT WE SENT FOR REPAIR. DISPLAY BLANK OUT AFTER POWER UP 	O 5800145883,DATE REPAIR MARCH 14 2008.																		 
	20080603		EU  	2008	6	3	CA080415004      	1	20080408	G	2750	Z4243130000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											FLAP CENTER CABLE WAS FOUND FRAYED DURING REGULARLY SCHEDULED MAINTENANCE.						1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
	20080603		SW  	2008	6	3	CA080415005      	1	20080412	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA			1233 								DURING THE RETURN LEG TO MAIN BASE THE AIRCRAFT EXPERIENCED A RT HEATED WINDSHIELD CRACK IN A SPIDER WEB FASHION. THE AI	RCRAFT DESCENDED THE CABIN DIFF WAS LOWERED AND AIRSPEED REDUCED.  UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH 	THE PREVIOUS INSTALLATION, ALL ATTACHING HARDWARE WAS CORRECT.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20080603		NE  	2008	6	3	CA080415006      	2	20080411	G	7250		BLADE           								TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TURBINE WHEEL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											1ST STAGE TURBINE WHEEL BLADE LEADING EDGE DAMAGE IN ZONE 2 ON A TOTAL OF 8 BLADES.  THE DAMAGE WAS CAUSED BY THE SEMI-C	ONDUCTOR OF THE IGNITER, P/N 9550175400, THAT DISLODGED ITSELF FROM THE HOUSING. THIS WAS FOUND DURING A SCHEDULED 100/1	50 HR ENGINE INSPECTION.  THE AFFECTED MO3 HAS BEEN SEND TO MANUFACTURER FOR FUTURE INVESTIGATION.  SUBSEQUENTLY ALL OTH	ER ENGINE IGNITER WHERE INSPECTED AND REMOVED FROM SERVICE DO TO LOOSENESS OF THE SEMI-CONDUCTOR.  PICTURES WERE TAKEN A	ND SEND TO MANUFACTURER.							3	U			E19EU				 
	20080521		WP  	2008	5	21	CA080415007      	1	20080411	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			79   								(CAN) AFTER FIRST GROUND RUN, STARTER CRACKED, REPLACED STARTER (TC NR 20080415007)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080521		EU  	2008	5	21	CA080416001      	1	20080414	G	5302	V40GT3911AA	SPRING          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL BOOM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMING OUT OF A MAJOR INSP, WHERE THE EJECTION SPRINGS ON ALL THE COWLS ( P/N 105-62648, 105-62664, 105-62643, 105	-62663 AND 105-30851) WERE REPLACED. SEVERAL EJECTION SPRINGS P/N V40GT39-1-1AA WERE BREAKING INTO (2) PIECES. THIS PROB	LEM HAPPENED STATICALLY ON THE GROUND. THESE EJECTION SPRINGS WERE ORDERED NEW FROM MFG, BATCH NR S0000243616 COMING FRO	M DIFFERENT LOT NR. BREAKAGE HAPPENS IN THE MFG LOGO STAMPED ON THE EJECTION SPRING.  NEW EJECTION SPRINGS SAME PN, SAME	 BATCH NR USED TO REPLACE BROKEN ONES ON THIS AC. (TC NR 20080416001)		1	G	7	2 	3U	3	U		H3EU    	E4CE				 
	20080521		NE  	2008	5	21	CA080416002      	2	20080416	G	7414		COIL            		BL6006163   	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAG WAS RECEIVED FOR 500 HOUR INSP.  WHEN VENT PLUG WAS REMOVED DIRTY BROWN OIL WAS FOUND IN THE MAGNETO. UPON DIS	ASSEMBLY THE OIL SEAL WAS FOUND TO BE LEAKING. THE COIL WAS LOOSE IN THE HOUSING UNDER THE COIL CLAMPS. THE COIL HAD DAR	K BROWN MATERIAL AROUND THE MOUNTING AREA OF THE COIL POLES FROM WEARING AGAINST THE HOUSING. BOTH THE COIL AND HOUSING 	WERE UNSERVICEABLE DUE TO THE AMOUNT OF WEAR. THE MAGNETO HAD A NEW STYLE OF HOUSING WITH THE LETTERS (TCM) RAISED IN TH	E CASTING AND A NEW CONTINENTAL ALPHA SYS DATAPLATE. THIS MAG WAS REBUILT  IN JANUARY OF 2007. THE MAG WAS RETURNED TO M	FG FOR WARRANTY PURPOSES. (TC NR 20080416002)	1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080521			2008	5	21	CA080416003      	4	20080416	G	2562	ELT10	ELT             			BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320A2B     	41508	EA  						INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN TESTING UNIT FOR ITS 12 MONTH CERTIFICATION IAW CAR 571 APPENDIX G, UNIT DID NOT HAVE ANY TRANSMIT POWER. ELT	 TRANSMITTER BOARD REPLACED AND UNIT TESTED SERVICEABLE. (TC NR 20080416003)					1	H	7	1 	3O	3	O		A759    	E274				 
	20080521		WP  	2008	5	21	CA080417003      	1	20080413	G	7920		PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE OIL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			978  								(CAN) DURING INSPECTION THERE WAS EVIDENCE OF OIL COMING OUT OF THE DRAIN LINE. THERE HAS BEEN MANY PUMPS LEAKING FORM T	HE SEALS AND THIS ALLOWS ENGINE OIL TO BYPASS AND FLOW OUT OF THE DRAIN. PUMP WAS REPLACED AND AIRCRAFT RETURN TO SERVIC	E. DATE CODE ON THE PUMP IS 4105. (TCNR 20080417003)				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20080521		EU  	2008	5	21	CA080417010      	1	20080221	G	5610		SEAL            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					CHIN BUBBLE	DEPARTED        	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) CHIN BUBBLE WINDOW AND SEAL DEPARTED THE AIRCRAFT IN CRUISE FLIGHT. AIRCRAFT WAS LANDED AND CHECKED FOR DAMAGE, NO	T FOUND. REVIEW INDCATED THAT THE WINDOW WAS REMOVED FOR MAINT BEFORE THE OCCURANCE.   WILL FOLLOW UP FOR SPECIFIC PN (T	C NR 20080417010)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
	20080521			2008	5	21	CA080418001      	1	20080416	G	3310	REE75R	RHEOSTAT        	VIKING      	72510090005 						PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	RESISTANCE COILS	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CONCERNED WITH THE USE OF RHEOSTAT (PN REE75R) FOR REPLACEMENT OF RHEOSTAT SWITCH 20465-1. THE SB 7-33-21 CALLS TH	E NEW RHEOSTAT, A RHEOSTAT SWITCH BUT IT DOES NOT HAVE AN "OFF" POSITION LIKE THE ORIGINAL RHEOSTAT SWITCH HAD. AS SUCH,	 WHEN IT IS TURNED TO THE SIMULATED OFF POSITION, IT IS STILL IN CIRCUIT (EVIDENCED BY THE FACT THAT THE UTILITY LIGHT H	AS A SLIGHT GLOW) AND DISSIPATING MAXIMUM WATTAGE.  THE HEAT IS TRANSFERRED THROUGH THE RHEOSTAT SHAFT CAUSING KNOB PN M	S91528-1C1-B TO BECOME DEFORMED AND HOT TO THE TOUCH.  ALSO, THE PANEL MATERIAL ADJACENT TO THE RHEOSTAT SHOWS EVIDENCE 	OF HEAT DAMAGE (CRACKING/DISCOLORATION).  HAVE CONDUCTED BENCH TESTS ON THIS RHEOSTAT TO SIMULATE THE AC CIRCUIT AND HAV						4	T			E4EA	6	C	P1NE	 
	20080521		NM  	2008	5	21	CA080418002      	1	20080417	G	2612		FIRE DETECTOR   			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 1 NACELLE	FALSE INDICATION	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, AT APPROX 1,000 FEET AGL, THERE WAS A FIRE WARNING ON THE NR 1 ENGINE. THRUST LEVER RETARDED, LIGHT	 REMAINED ON. EMERGENCY DRILL COMPLETED AND LIGHT EXTINGUISHED AFTER FIRE BOTTLE DISCHARGED.  AC RETURNED AND LANDED WIT	HOUT FURTHER INCIDENT.  THERE WAS NO EVIDENCE OF A FIRE.  MAINT FOUND THE FAULT IN THE NR 1 FIRE DETECTION B SYS. (TC NR	 20080418002)			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20080521			2008	5	21	CA080418003      	1	20080318	G	3245	302120402	TUBE            																	MLG TIRE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MULTIPLE FAILURES OF INNER TUBES ON VARIETY OF COMPANY C-208 MAIN WHEELS. TUBES FAIL IN DIFFERENT WAYS FROM PIN HO	LES TO 18 INCH SPLITS. THERE HAVE BEEN NO FOREIGN OBJECTS FOUND IN THE AFFECTED TIRES AND ASSY PRACTICES HAVE BEEN OBSER	VED TO ENSURE CORRECT PROCEDURES ARE BEING FOLLOWED. TUBES ARE PURCHASED FROM A VARIETY OF SUPPLIERS AND ORIGINATE IN DI	FFERENT COUNTRIES. (TC NR 20080418003)																 
	20080521			2008	5	21	CA080418004      	4	20080417	G	6113	VT2E16231	PLATE           			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP SPINNER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			35   								(CAN) RECEIVED A CALL REGARDING DAMAGE THAT OCCURRED TO THE PROP BACKING PLATED ON A TURBO BEAVER WE COMPLETED REG, C-FO	EU. THIS DAMAGE IS THE RESULT OF OUR INSTALLATION OF OUR PROP POSITION TRANSMITTER MOD STCSA 98-46, VT2E 1623.  IDENTIFI	ED THE PROBLEM TO BE THE INCOMPATIBILITY BETWEEN THE PROP SPINNER BACKING AND OUR POSITION INDICATOR. THE BACKING PLATE 	IN QUESTION HAS A DIFFERENT PROFILE FROM THE ONES THAT WE HAVE SEEN BEFORE. COMPARED THIS PROBLEM BACKING PLATE TO OUR A	/C AND THERE IS A BIG DIFFERENCE, OURS ALLOWS ALMOST .5 CLEARANCE AND THERE IS NO INTERFERENCE WITH THE CAM ROD THROUGH 	THE TOTAL MOTION.   MFG NEEDS TO IDENTIFY THIS COMPATIBILITY ISSUE IN THE STC AND FOR THE INTERIM SEND OUT A SL TO THE O	1	H	7	1 	3T	4	T		A806    	E4EA	6	C	P15EA	 
	20080521		SO  	2008	5	21	CA080421001      	1	20080408	G	3210	424052	COTTER PIN      	PIPER       	7872331     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	TORQUE LINK	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COTTER PIN MISSING ON LT MLG TORQUE LINK DURING WALK AROUND.  BOLT REMOVED AND FOUND DRY OF LUBRICATION, WHICH COU	LD HAVE CAUSE NUT TO TURN AND SHEARING OF COTTER PIN.  NEW BOLT INSTALLED AND LUBRICATED ON BOTH MAIN GEAR TORK LINKS. (	TC NR 20080421001)				1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
	20080521		NE  	2008	5	21	CA080422002      	2	20080417	G	7250	3053094CL	BLADE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	DEFORMED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			820  								(CAN) THE PILOTS NOTICE THAT THE ENGINE WAS RUNNING 50 DEGREES HOTTER THAN NORMAL. A HOT SECTION (HSI) WAS COMPLETED AND	 IT WAS FOUND THAT THE OLD SEGMENT 3053094CL WAS INSTALLED 820 HOURS BEFORE WITH A NEW WHEEL AND BLADES. THE SEGMENTS HA	D DEFORMED AND THE CT BLADES HAD RUBBED AGAINST THE SEGMENTS CAUSING EXCESSIVE CLEARANCES. THIS WORK HAD BEEN DONE BY MF	G.  THE HOT SECTION WAS SENT BACK FOR WARRANTY CONSIDERATION . (TC NR 20080422002)			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
	20080522			2008	5	22	CA080422003      	4	20080420	G	8300		COUPLER         			LKHEED	188   	188A        	5262602	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	ENG/GEARBOX	UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING START SEQUENCE OF NR 4 ENGINE, IT WAS OBSERVED THAT RPM AND ACCELERATION CLIMBED TOO FAST, BEFORE LIGHT OFF	, ENGINE START ABORTED AND FOUND ENGINE DECOUPLED FROM GEARBOX. SUSPECT TORQUE SHAFT COUPLER (TC NR 20080422003)					2	L	7	4 	4T	4	T	RT	4A22    	E282	6	C	P898	 
	20080522		NE  	2008	5	22	CA080423003      	2	20080421	G	7320	1520KDC0501	EEC             			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE AIRCREW REPORTED THE FOLLOWING, AC WAS CRUISING AT FL450 AND CREW REALIZED THAT THE LT ENGINE SPOOLED DOWN TO 	IDLE WITHOUT PILOT INPUT. CREW ATTEMPTED TO MOVE THE THROTTLE IN EPR AND N1 MODE AND THERE WAS NO REACTION FROM THE LT E	NGINE.  EICAS MESSAGE (L FADEC FAULT) (CYAN) POSTED.  CREW REQUESTED LOWER FLIGHT LEVEL AND LEVELED OFF AT FL370. APU WA	S STARTED. THEY DESCENDED FURTHER TO FL290 AND SHUTDOWN THE LT ENGINE TO ATTEMPT A START AND RUN ON THE OPPOSITE ENGINE 	ELECTRONIC CONTROLLER (EEC) CHANNEL TO REGAIN LT ENGINE CONTROL.  ENGINE WAS RESTARTED AND ALL LT ENGINE CONTROLS RETURN	ED TO NORMAL OPERATING CONDITIONS.  CREW DIVERTED, AS A PRECAUTIONARY MEASURE, IN ORDER TO HAVE THE AC EVALUATED AND REP	2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
	20080521		NM  	2008	5	21	CA080423004      	1	20080416	G	5610	5893543130	WINDSCREEN      			BOEING	727   	727260      	138408K	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) AFTER COCKPIT SETUP SMOKE AND FLAME WAS OBSERVED BY THE FLIGHT CREW FROM THE TOP LT CORNER OF THE R1 WINDOW.  WHEN	 THE R1 WINDOW HEAT WAS SELECTED OFF THE FLAME AND SMOKE CEASED. THE R1 WINDSCREEN WINDOW HEAT SYS WAS DEFERRED BY MAINT	. UPON ARRIVAL AT THE DESTINATION THE R1 WINDOW WAS REPLACED AND THE R1 WINDOW HEAT CONTROLLER WAS ALSO REPLACED AS A PR	ECAUTION.  THE AC WAS RETURNED TO SERVICE. (TC NR 20080423004)			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
	20080521		NE  	2008	5	21	CA080423011      	2	20080330	G	7200		ENGINE          			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) THE CREW REPORTED VIBRATIONS SHORTLY AFTER TAKEOFF AND WAS ATTEMPTING TO RETURN TO POINT OF DEPARTURE. THE AC CRAS	HED. ALL ON BOARD WERE FATALLY INJURED.  BOTH ENGINES SHOWED INDICATIONS CHARACTERISTIC OF THE ENGINES PRODUCING LOW POW	ER OR WINDMILLING UNDER AIR LOADS AT THE TIME OF IMPACT. THERE WERE NO INDICATIONS OF ANY PRE-IMPACT ANOMALIES TO ANY OF	 THE COMPONENTS OBSERVED.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 2	0080423011)		1	L	7	2 	4F	4	F		A22CE   	E25EA				 
	20080521		NE  	2008	5	21	CA080423012      	2	20080417	G	7261		OIL SYSTEM      			AMD   	FALC50	FALCON2000  	2730170	NM  	PWC   	PW306 	PW306C      	52169	NE  					ENGINE	LEAKING         	W				A				UNSCHED LANDING         				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, THE CREW NOTED OIL SMELL FOLLOWED BY VISIBLE VAPOR IN THE CABIN AIR AND OIL PRESSURE GAUGE FLUCTUAT	IONS. THE FLIGHT WAS DIVERTED TO AN ALTERNATE LANDING SITE. THE ENGINE WAS SHUTDOWN FOLLOWING LANDING. OIL WAS OBSERVED 	INSIDE THE BYPASS DUCT AND FAN STATOR.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS	HED. (TC NR 20080423012)			2	L	7	2 	4F	4	F	RT	A50NM   	E35NE				 
	20080521		EA  	2008	5	21	CA080423013      	2	20080328	G	7321		FUEL CONTROL    			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A28      	 	EA  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				X			ENGINE FLAMEOUT           			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, UPON RETARDING THE POWER LEVER TO IDLE, THE ENGINE ACCELERATED TO 90 PERCENT NG WITH AN ASSOCIATE	D TEMPERATURE OF 800 DEGREES. THE PILOT ELECTED TO SHUTDOWN THE ENGINE AND FEATHER THE PROP. THE FUEL CONTROL WAS SUBSEQ	UENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20080423013)				1	L	7	2 	3T	4	T		3A20    	E4EA				 
	20080521		CE  	2008	5	21	CA080423014      	1	20080417	G	7500		LINE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) OPERATOR REPORTS (2) EVENTS OF POWER LOSS FOLLOWED BY ENGINE SHUT DOWN. ONE EVENT APRIL 17, 2008, THE OTHER APRIL 	18, 2008. BOTH CAUSED BY FRACTURE OF THE PY LINE.  AIRCRAFT RETURNED TO SERVICE FOLLOWING 2ND REPLACEMENT OF THE PY LINE	. (TC# 20080423014)				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20080522		NM  	2008	5	22	CA080424001      	1	20080418	G	2910	AE2463510E0124	FLEX LINE       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	F		FLUID LOSS                	FLT CONT AFFECTED         		CR	CRUISE         	1			CA											(CAN) AFTER TAKEOFF WITH GEAR RETRACTON NR 2 HYD SYS QUANTIY DROPPED TO 2 QUARTS, THE CREW ELECTED TO RETURN TO THE AIRF	IELD. DURING LANDING THE NR 2 HYD ISOLATION LIGHT CAME ON AND THE AC LOST THE OB SPOILERS, AND STEERING. THE AC WAS TOWE	D TO THE HANGAR AND THE LEAK WAS TRACED TO THE NOSE GEAR PRESSURE LINE NEAR THE SWAGE. TT ON THIS PART IS UNDETERMINED. 	(TC NR 20080424001)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080522		SO  	2008	5	22	CA080424003      	2	20080423	G	7414	10160844	BRUSHES         	BENDIX      	BL3492205   	CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	MAGNETO	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			363  								(CAN) LT ENGINE REPORTED DIFFICULT TO START. MAGNETO REMOVED AND BENCH TESTED, FOUND TO HAVE LOW AND INCONSISTENT OUTPUT	. MAGNETO DISASSEMBLED FOR INSP AND FOUND CARBON BRUSH ASSY NOT INSTALLED IN DISTRIBUTOR GEAR. NO EVIDENCE OF BRUSH OR S	PRING REMNANTS FOUND INSIDE OF MAGNETO. MAGNETO RE-ASSEMBLED WITH NEW BRUSH, BENCH TESTED IAW BENDIX OVERHAUL MANUAL X42	000-1. MAGNETO RE-INSTALLED ON ENGINE, ENGINE STARTS NORMAL. (TC NR 20080424003)			1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
	20080522		NE  	2008	5	22	CA080424005      	2	20080423	G	7420	90591507	IGNITION LEAD   			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					LT ENGINE	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1971 								(CAN) DURING ROUTINE INSP OF THE ENGINE, THE LT ENG OB IGNITER LEAD WAS FOUND DEFECTIVE. UPON REMOVAL OF IGNITER FROM LE	AD, FOUND THE LEAD`S CENTER ELECTRICAL POST LOOSE AT IGNITER END.  APPROX ONE INCH OF THE CENTER POST OF LEAD FEEL OUT W	ITH CERAMIC INSULATOR AND NOTED BURNING MARKS AROUND WHERE THE CENTER CORE HAD BROKEN AWAY.  LEAD REPLACED WITH NEW UNIT	. (TC NR 20080424005)			2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
	20080522		NM  	2008	5	22	CA080425002      	1	20080421	G	2740	32EN614	WARNING SWITCH  			BOEING	727   	72722C      	138400F	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					LOWER STABILIZER	CLOSED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) WHILE ATTEMPTING TAKEOFF, TAKEOFF WARNING INTERMITTENT, HORN SOUNDED UPON POWER LEVER ADVANCEMENT. TAKEOFF WAS ABO	RTED AND AC RETURNED TO BLOCKS. TROUBLESHOOTING REVEALED THE LOWER HORIZONTAL STABILIZER TAKEOFF WARNING SWITCH WAS NOT 	CONTACTING ACTUATING CAM. THE SWITCH WAS FOUND TO BE HOLDING CLOSED DUE TO BINDING OF THE ROTARY SHAFT. FURTHER EXAMINAT	ION REVEALED SHAFT HAD BEEN BENT. IT IS SPECULATED THAT ICE MAY HAVE BUILD UP ON THE SWITCH ACTUATION (STABILIZER) CAM. 	THE AC HAD JUST BEEN DE-ICED DUE TO SNOW ACCUMULATION PRIOR TO TAKEOFF ATTEMPT. THE SWITCH WAS REPLACED AND THE AC RETUR	NED TO SERVICE. (TC NR 20080425002)	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20080522		NM  	2008	5	22	CA080425006      	1	20080425	G	5311	654653969	FRAME           			BOEING	737   	737490      	1384715	NM  										BS 616	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VISUAL INSPECTION FOUND THAT INNER FRAME CHORD AT BS 616, RT, WL 200 AT STUB BEAM TO BE CRACKED. (TC NR 2008042500	6)					2	L	7	2 	4F			RT	A16WE   					 
	20080522		NM  	2008	5	22	CA080426001      	1	20080423	G	8120	310440001	TURBOCHARGER    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1 ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA			44847	18251							(CAN) AFTER TAKEOFF, CREW HAD LOW OIL PRESSURE INDICATION ON THE NR1 ENGINE, CREW DID PRECAUTIONARY ENGINE SHUTDOWN AND 	ADVISED THEY WERE RETURNING. FLIGHT LANDED WITHOUT INCIDENT. MAINT INSPECTED THE ENGINE AND FOUND OIL COMING OUT OF LP O	UTLET AND COVERING TOP OF THE ENGINE, ALSO FOUND SEAL DAMAGE . THE ENGINE WAS CLEANED, GROUND RUNS WERE C/O AT MAX POWER	 FOR 30 MIN TO SEE IF ANY SMOKE SMELL TO SHOW CONTAMINATED DUCTING AND TO SEE IF OIL IS STILL COMING OUT. LEAK FROM COMP	RESSOR FOUND TO BE BEYOND LIMITS, ENGINE CHANGE TO BE C/O. TEARDOWN REPORT TO FOLLOW WHEN AVAILABLE. (TC NR 20080426001)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080522		NM  	2008	5	22	CA080428001      	1	20080424	G	2761		CASE            	SMITHSIND   		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ACTUATOR	RUPTURED        	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			49425								(CAN) WHEN TAXING INTO POSITION FOR TAKEOFF, THE CREW RECEIVED A NR1 HYD ISO VALVE AND A ROLL SPLR IB HYD CAUTION LIGHTS	. THE AC RETURNED TO GATE AND A HYD LEAK WAS OBSERVED AT THE RT WING. FURTHER INVESTIGATION REVEALED THAT THE RT IB SPOI	LER ACTUATOR CASING HAD RUPTURED AND CAUSED THE LEAK. THE ACTUATOR WAS REPLACED, ADJUSTED, LEAK CHECKED AND TESTED SERVI	CEABLE. THE AC WAS RELEASED AND RETURNED INTO SERVICE.  TSR: 1657:43 CSR: 1678 (TC NR 20080428001)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20080522		EA  	2008	5	22	CA080428002      	2	20080425	G	8530	05K21104	CYLINDER HEAD   			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	MCAULY	2D34C	2D34C53     	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA				440  							(CAN) ON TAKEOFF PILOT FELT SLIGHT VIBRATION THROUGH RUDDER PEDALS. AFTER GETTING TO HIS CRUISE LEVEL THE VIBRATION GOT 	WORSE. HE RETURNED TO THE AIRPORT, AC WAS BROUGHT INTO MAINT SHOP AND COWLING WAS REMOVED. COMPRESSION TEST WAS COMPLETE	D AND IT WAS FOUND THAT NR3 CYL NO COMPRESSION. CYL WAS REMOVED FROM ENGINE. FOUND THAT THERE WAS A HOLE BURNED UNDER TH	E EXHAUST VALVE SEAT AND THERE WAS A PART OF THE EXHAUST VALVE MISSING. RECORDS INDICATE THAT AT ENGINE OVERHAUL THE EXH	AUST VALVES AND SEATS WERE REPLACED. AME WONDERS IF WHEN THEY CHANGED THE SEAT THAT THEY MAY HAVE CRACKED THE CYL ALLOWI	NG THE EXHAUST GASES TO BURN THROUGH THE CYL UNDER THE SEAT. (TC NR 20080428002)	1	L	7	1 	3O	3	O		2A3     	E286	5	C	P7EA	 
	20080522		NM  	2008	5	22	CA080428005      	1	20080421	G	3246	29685	BEARING         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	WHEEL ASSY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA				238  							(CAN) DURING TAXI FOR DEPARTURE, THE AC FOLLOWING THE SUBJECT S/N 4168 AC, REPORTED (SMOKE AND FIRE) FROM THE RT GEAR. T	HE F/A CONFIRMED. THE AC STOPPED AND PASSENGERS WERE EVACUATED ON THE TAXIWAY. INSP BY MAINT DETERMINED THE CAUSE TO BE 	A WHEEL BEARING FAILURE. THE WHEEL WAS REMOVED AND THE AC WAS TOWED TO THE HANGER.  MAINT REPLACED THE MAIN WHEEL ASSY A	ND THE AC RETURNED TO SERVICE. (TC NR 20080428005)			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE	 
	20081105		EU  	2008	11	5	CA080507004      	1	20080430	G	6420		FORK            			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					TAIL ROTOR	BINDING         	W				C	R			ABORTED TAKEOFF         	AUTOROTATION            			F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			65   								(CAN) ACFT WAS UNDERGOING A TEST FLIGHT FOR RADAR ALTIMETER TROUBLESHOOTING. 5 MINUTES INTO CRUISE FLIGHT, A SUDDEN VIBR	ATION WAS INDUCED INTO AIRFRAME AND ALL FLIGHT CONTROLS. PILOT IMMEDIATELY RETURNED TO BASE FOR AN UNSCHEDULED LANDING W	ITHOUT INCIDENT. UPON INSP OF ACFT, IT WAS FOUND THAT 1 TAIL ROTOR MOUNTING FORK WAS BINDING WHILE ATTEMPTING TO FEATHER	 BLADE. IT WAS ALSO NOTED THIS BLADE HAD NO AVAILABLE MOVEMENT IN THE FLAPPING AXIS. REMOVAL OF TAIL ROTOR INNER SLEEVE 	ASSY. REVEALED 1 OUTER BUSHING WAS PROTRUDING BEYOND THE INNER SLEEVE BY 1.80MM. INSPECTION OF THE MOUNTING FORK ALSO IN	DICATED ABRASION MARKS ON THE INSIIDE WHERE THE DISLODGED BUSHING HAD COME INTO CONTACT. SUSPECT ACFT VIBRATION A RESULT	1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
	20081105		EU  	2008	11	5	CA080508007      	1	20080506	G	5610	350A25904320	WINDSHIELD      			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1943 	1943 							(CAN) DURING INSP, A CRACK WAS FOUND IN THE UPPER LT CORNER OF THE PILOTS WINSHIELD. WINDSHIED HAS BEEN REPLACED. THIS I	S THE 4TH WINDOW REPLACED ON THIS ACFT IN 1943 HRS. IAW CONVERSATIONS WITH THE MFR THE THICKNESS OF THE WINDOWS WILL BE 	INCREASED IN THE FUTURE.				1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
	20081105		WP  	2008	11	5	CA080508020      	1	20080428	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			392  								(CAN) ON START ACFT STARTER GEN DID NOT ENGAGE.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081105		NM  	2008	11	5	CA080510002      	1	20080102	G	6220		BEARING         	ROBSIN      		ROBSIN	R22   	R22BETAII   	7640110	NM  										M/R HEAD	WORN            	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			2169 								(CAN) PILOT REPORTED A LATERAL VIBRATION HAD BEEN PROGRESSIVELY GETTING WORSE OVER THE PAST WEEK. UPON VISUAL INSP OF TH	E MAIN ROTOR HEAD THERE WAS A BLACK PASTE (SMOKING) AROUND ONE OF THE TEETER HINGE BEARINGS. AFTER REMOVING MAIN ROTOR H	EAR IT WAS FOUND THAT THE THRUST WASHER HAD BEEN CHAFING THE OTBD FACE OF THE BEARING.  THE MAIN ROTOR HEAD WAS REMOVED 	AND REPLACED WITH A SERVICABLE HEAD. (TC NR 20080510002)			1	G	7	1 	3O				H10WE   					 
	20081105		EU  	2008	11	5	CA080513007      	1	20080506	G	6320	332A3210073P	TRANSMISSION    			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA				2581 							(CAN) TRANSMISSION CHIP LIGHT ILLUMINATION. FERROUS METAL CHIPS, WHISKERS AND FLAKES FOUND IN FILTER AND SUMP AND ON CHI	P DETECTOR.					2	G	7	2 	4U	4	U		H4EU    	E12NE				 
	20081105		WP  	2008	11	5	CA080513008      	1	20080506	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			1064 								(CAN) DURING INSPECTION FOUND THE LT FWD SERVO LEAKING. (TC NR 20080513008)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081105		WP  	2008	11	5	CA080514007      	1	20080508	G	6510		SHAFT           			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					COOLING FAN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			473  								(CAN) ON POST FLIGHT THE COOLING FAN WAS FOUND SPUN ON THE LOWER BEARING AND SHAFT ASSY. (ALIGNMENT MARK MISALIGNED) (TC	 NR 20080514007)					1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081105		SW  	2008	11	5	CA080515002      	1	20080515	G	6710		CYCLIC CONTROL  			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						OBSTRUCTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER INSTALLATION OF THE VERTICAL REFERENCE SEAT KIT LISTED ABOVE, IT WAS DISCOVERED DURING FLIGHT CONTROL CLEARA	NCE CHECKS THAT THE SEAT IN VARIOUS PLACEMENTS OF IT`S RANGE OF TRAVEL INTERFERED WITH THE FULL MOVEMENT OF THE CYCLIC F	LIGHT CONTROL. INCLUDED WITH THIS REPORT IS A DOCUMENT WITH SOME PRELIMIARY APPROXIMATE VALUES AND PICTURES OF THE CLEAR	ANCE AND INTERFERANCE THAT EXISTS.  INSTALLATION OF THE SEAT KIT AS IAW AAL-292-035-001, UNDER STC APPROVAL NR SH 06-31			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081105		SW  	2008	11	5	CA080516003      	1	20080513	G	6520	212040004103	GEARBOX         			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA			24   								(CAN) 90 DEGREES, GEARBOX STARTED LEAKING AFTER 7.8 HOURS OF FLIGHT. UPON LANDING (TOTAL FLIGHT TIME OF 24.1 HOURS ON TH	E HOURMETER),THE OIL LEVEL WAS CHECKED IN THE 90 DEGREE AND FOUND TO BE EMPTY, WITH OIL SPLASHED ALL OVER THE GEARBOX. T	HE GEARBOX WAS FILLED WITH OIL TO THE NORMAL LEVEL AND THE ACFT WAS HOVERED FOR HALF AN HOUR AND CHECKED FOR LEAK, WHICH	 WAS CONFIRMED. THE OIL WAS LEAKING FROM THE PITCH CHANGE MECHANISM. THE OIL FILLER CAP WAS CHECKED FOR BLOCKAGE BUT WAS	 FOUND OK.		1	G	7	2 	4U	4	U		H4SW    	E22EA				 
	20081105		EU  	2008	11	5	CA080516013      	1	20080515	G	6220	350A37116200	STOP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					MAIN ROTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7162 								(CAN) SUPPORT WAS FOUND BROKEN DURING THE AFTER LAST FLIGHT INSPECTION BY THE PILOT. NO SIGN OF FLIGHT CONTROL PROBLEM, 	VIBRATION OR NOISE WAS NOTICED. WORST CASE SCENARIO, IF THE DROOP RING GOT STUCK BETWEEN ONE BLADE AND THE MAST, IT COUL	D BE FATAL SINCE ONLY (2) OUT OF (3) WAS KEEPING THE RING CENTERED. (TC NR 20080516013)				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081105		SW  	2008	11	5	CA080521002      	1	20080513	G	6410		BEARING         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					T/R BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1421 	1421 							(CAN) DURING THE 100 HR INSP A SMALL CRACK WAS FOUND ON THE INBD FEATHERING BEARING ON ONE OF THE TAIL ROTOR BLADES. CRA	CK WAS NOTICED AS A BLACK LINE AT THE TOP OF THE BEARING.  THIS IS A CRACK THAT WAS QUITE COMMON 10-15 YEARS AGO AND SEE	MS TO HAVE RESURFACED.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081105		SW  	2008	11	5	CA080521007      	1	20080516	G	6310	206040270	CLUTCH          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FREEWHEEL UNIT	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1421 								(CAN) NOISE FROM FREEWHEEL ON SPOOLDOWN, NO INDICATIONS ON CHIP PLUG. REMOVED FREEWHEEL ASSY AND FOUND CLUTCH NOT FULLY 	RELEASING. REPLACED FREEWHEEL ASSY.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081105		SW  	2008	11	5	CA080523002      	1	20080522	G	6220	AN17420	BOLT            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317BLYC   	41616	NE  					STAB BAR DAMPER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING ADI, AME DISCOVERED THAT A STAB BAR DAMPER TUBE ASSY P/N: 204-010-925-009 AND A DAMPER LEVER P/N:	 212-010-301-001 WERE MISSING. IT APPEARS THAT THE TUBE ASSY UPPER BOLT P/N: AN174-20 BROKE OFF FIRST AND WAS THE CONTRI	BUTING FACTOR OF THE DAMAGE.  THE REMAINS OF SUBJECT BOLT (NUT WASHER AND SHANK WILL BE SENT FOR INVESTIGATION/ANALYSIS 	FOR POSSIBLE METAL FATIGUE AND/OR CORROSION. (REMAINS OF SUBJECT BOLT WERE STILL IN STAB BAR FRAME, INBOARD SIDE)  STAB 	BAR DAMPER P/N: 204-010-937-009 WILL BE REPLACED AS A PRECAUTIONARY MEASURE AND SENT FOR INSVESTIGATION AS WELL FOR A PO	SSIBLE INTERNAL FAILURE/SEIZURE WHICH MIGHT HAVE CONTRIBUTED TO SUBJECT BOLT FAILURE.  STAB BAR DAMPER TUBE RIGGING FOR 	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081105			2008	11	5	CA080523005      	4	20080516	G	2311	TK760HG	TRANSCEIVER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					UHF SYSTEM	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RADIO WOULD NOT TRANSMIT, REMOVED AND INSTALLED SERVICABLE RADIO.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
	20081105		WP  	2008	11	5	CA080523006      	1	20080518	G	2432	RG2415	BATTERY         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MASTER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			73   								(CAN) DURING DI FOUND THE BATTERY LEAKING, REPLACED WITH A NEW ONE.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081105		GL  	2008	11	5	CA080527002      	2	20080521	G	7230	23057142	STATOR          	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					6TH STAGE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3486 							(CAN) COMPRESSOR ASSY WAS REMOVED FOR O/H, AT WHICH TIME IT WAS NOTED THE 6TH STAGE STATOR BAND WAS MISSING ONE BLADE, W	ITH IMPACT DAMAGE NOTED ON OTHER BLADES ALSO IN THE 6TH BAND. NO DAMAGE NOTED FWD OF 6 TH STAGE. BURNER CAN REMOVED AND 	TURBINE INSPECTED FOR FOD, BUT NONE WAS FOUND. IT DID NOT APPEAR THAT THE STATOR WENT THROUGH THE ENGINE, HOWEVER, AT TH	IS TIME, WE WERE UNABLE TO LOCATE THE DEPARTED BLADE. THE CRACK APPEARS RECENT, AND IT IS BELIEVED THE BLADE CRACKED IN 	THE LAST 100 HOURS OF OPERATION (TC NR 20080527002)		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081105		SW  	2008	11	5	CA080528003      	1	20080523	G	5302	206032400027S	RING            	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON TAIL BOOM RING DURING ROUTINE INSPECTION.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081105		SW  	2008	11	5	CA080528004      	1	20080523	G	5300	206031337003	FITTING         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  						CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DETECTED ON FITTING DURING ROUTINE INSPECTION.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081105		SW  	2008	11	5	CA080528007      	1	20080525	G	5100	427065125111	SHROUD          			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					FUSELAGE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3800 								(CAN) OPERATOR REPORTED A MAIN ROTOR TRANSMISSION OIL LINE FAILURE. INSP REVEALED CHAFING DAMAGE TO THE OIL-LINE SHROUD 	ASSY FROM THE FIREWALL CLOSEOUT METAL EDGE.					1	G	7	1 	3U	3	U		R00001RC	E42NE				 
	20081105			2008	11	5	CA080528010      	4	20080417	G	8300	23068295	GEARSHAFT       	ALLSN       		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE GEARBOX WAS RECEIVED FOR OVERHAUL.  A CRACK WAS FOUND DURING THE MPI PROCESS AT THE REPAIR FACILITY. THERE ARE	 (2) THROUGH CRACKS IN THE REAR SEAL JOURNAL AREA OF THE POWER TAKEOFF GEARSHAFT.  THE POWER TAKEOFF (PTO) GEAR IS SN CG	119988. (TC NR 20080528010)				1	G	7	2 	3U	3	U		H1NE    	E1GL				 
	20081105		WP  	2008	11	5	CA080528014      	1	20080522	G	2822	D8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			609  								(CAN) AUX FUEL PUMP UNSERVICEABLE, CHANGED OUT FUEL PUMP WITH A SERVICABLE ONE. (TC NR 20080528014)						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081105		NE  	2008	11	5	CA080530001      	1	20080529	G	6730	S156520421041	SERVO           			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					MAIN ROTOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4694 	1156 							(CAN) DURING A POST-FLIGHT INSP, MECHANIC FOUND MOVEMENT BETWEEN THE FORK AND PISTON. THE PRIMARY SERVO WAS REPLACED.  A	FTER DISASSEMBLY AT REPAIR STATION, IT WAS DISCOVERED THAT THE MOVEMENT WAS CAUSED BY THE BREAKDOWN OF A LAMINATED REPAI	R SHIM INSTALLED BETWEEN THE FORK AND PISTON ROD, CAUSING THE LOSS OF TORQUE BETWEEN THE SERVO FORK AND PISTON ROD.  SUB	MITTING THIS SDR IAW OUR REPAIR STATION CANADIAN SUPPLEMENT.  AN ASB 64B29-8 WAS RELEASED BY THE MFG, ON MAY 24, 2008 (T	C NR 20080530001)		2	G	7	2 	4U	4	U		H4EA    	E15EA				 
	20081106		EU  	2008	11	6	CA080530003      	1	20080528	G	6730	SC5083	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					FLT CONTROLS	WORN            	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			HO	HOVERING       	1			CA			2895 	2895 							(CAN) STIFF FLIGHT CONTROLS IN ALL RANGE OF TRAVEL, IN HOVER, CRUISE, LANDING.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081229		NE  	2008	12	29	CA080601001      	2	20080521	G	7200	70BM035420	MODULE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	NOISY           	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			2955 	2955 							(CAN) SQEALING NOISE COMING FROM ENGINE.  SHUTDOWN AFTER FLIGHT, SUSPECT TURBINE BLADE RUB.  MODULE 2 AND MODULE 3 REMOV	ED AND SENT TO MFG.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081106			2008	11	6	CA080602005      	1	20080516	G	7810	3031988	EXHAUST DUCT    								PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			13577	1220 							(CAN) DAMAGED EXHAUST DUCT, PRIMARY FAILURE WAS TO THE INNER CONE OF THE EXHAUST DUCT, APPEARED TO CRACK AT NR 3 BEARING	 END AND EVENTUALLY DAMAGED THE T/E OF THE PT ROTOR BLADES. (TC NR 20080602005)										4	T			E4EA				 
	20081229		GL  	2008	12	29	CA080603005      	2	20080602	G	7314		PUMP            			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20R2    	 	GL  					FUEL	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REINFORCED PAPER WIPERS LEFT IN THE FUEL TANK AFTER WORK CARRIED OUT.  DURING A 300 HOUR INSP, THERE WAS SIGNIFICA	NT FUZZ LIKE DEBRIS FOUND IN THE ENGINE DRIVEN FUEL PUMP FILTER THAT WAS A BLUISH COLOR.   WHEN PICKING UP THE HELICOPTE	R AT THE SERVICE CTR WHERE THE ACFT WAS DISASSEMBLED, INSPECTED, PAINTED AND REASSEMBLED, USED ONE OF THEIR SHOP TOWELS 	DURING THE ACCEPTANCE INSP.  CALLED THE SERVICE CTR TO CONFIRM THAT THEY WERE USING THIS TYPE OF WIPER. THAT WAS VERIFIE	D AS CORRECT. THE FUEL CELL WAS OPENED UP AND A LARGE INTACT WIPER WAS FOUND OVER THE START FUEL PUMP. A SECOND .5 PIECE	 WAS RECOVERED FROM THE FUEL CELL INTERCONNECT AREA. AN SMS REPORT WAS PREPARED AND OUR INTERNAL SAFETY TEAM IS NOW DOIN	1	G	7	1 	3U	3	U		H3WE    	E4CE				 
	20081106			2008	11	6	CA080603006      	1	20080528	G	5744	00100018273	HINGE BRACKET   																	RT WING	WORN            	W				I				CABIN DEPRESSURIZATION  				O			OTHER                     			IN	INSP/MAINT     	1			CA			1191 								(CAN) REAR SPAR, RT LOWER WING AILERON, HINGE BRACKET INNER OUTER SHELL BECOMING LOOSE IN BEARING (REPLACED WITH NEW) (T	C NR 20080603006)																		 
	20081106		CE  	2008	11	6	CA080604005      	1	20080530	G	2910	4529101067001	LINE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					HYDRAULIC SYS	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			2614 								(CAN) DURING CRUISE, THE ACFT EXPERIENCED A HYDRAULIC FAILURE. THE CREW DECLARED AN EMERGENCY, LANDING WITHOUT FLAPS. IN	VESTIGATION REVEALED A KINK IN A HYDRAULIC SUPPLY LINE IN THE PYLON AREA OF THE LT ENGINE. A CRACK HAD FORMED IN THE KIN	KED AREA AND THE FLUID WAS RELEASED FROM THE PRESSURIZED LINE.				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
	20081106		SW  	2008	11	6	CA080604011      	1	20080528	G	5340		ATTACH FITTING  			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					LIFT LINK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CONDUCTING A 25 HR INSP, A CRACK WAS NOTED ON THE LIFT LINK BEAM LUG. THE PART WAS REMOVED AND TT OF THE BEA	M IS UNKNOWN AT THIS TIME. CRACK WAS FOUND ON THE AFT EAR OF LUG RT SIDE.					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081106		NE  	2008	11	6	CA080604013      	2	20080603	G	7200		ENGINE          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  						FLAMED OUT      	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ACFT TOOKOFF AND ENGINE FLAMED OUT AT 41000 FT, ENGINE RESTARTED AT 25 000 FT AND LANDED SAFELY. ENG MFG WAS CALLE	D AND OPERATOR INSTRUCTED TO DO POWER ASSURANCE.  AT THE TIME ARCRAFT WAS AT IMC SOME 17NM OFF TRACK DIVERTING AROUND SO	ME MODERATE INTENSITY RADAR RETURNS.  RADAR PICTURE GAVE NO CAUSE FOR CONCERN WITH THE PATH WHICH WAS CHOSEN AND INDICAT	ED THAT ACFT WAS WELL CLEAR OF THE CELLS. LIGHT TURBULENCE BEING EXPERIENCED IN CLOUD WAS NOT NOTEWORTHY AND COMMONPLACE	 FOR FLIGHTS IN THE REGION. HOWEVER UNEXPECTED UNPAINTED ACTIVITY WAS ENCOUNTERED AND IN CLOSE PROXIMITY TO A LIGHTENING	 FLASH FOLLOWED BY THE SOUND OF ICE PARTICLES IMPACTING THE ACFT, BUT THE TURBULENCE WAS STILL LIGHT. VERY SHORTLY AFTER	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081106		EA  	2008	11	6	CA080604016      	1	20080602	G	5280		ROD             			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					MLG DOOR	OUT OF RIG      	W				A				UNSCHED LANDING         				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CL	CLIMB          	1			CA											(CAN) UPON GEAR RETRACTION DURING TAKEOFF A RHYTHMIC THUMPING SOUND WAS HEARD COMING FROM THE NOSE AREA. A RETURN TO FIE	LD WAS REQUESTED AND AN EMERGENCY DECLARED. NO EICAS MESSAGE WAS POSTED AND NOISE STOPPED WHEN GEAR SELECTED DOWN.  LAND	ING DONE WITHOUT ANY ISSUE. ACFT WAS PUT IN QUARANTINE FOR TEST ON GROUND AND FINDING OF THE ROOT CAUSE. AFTER TROUBLESH	OOTING NOISE SUSPECTED TO BE COMING THE NOSE LANDING GEAR DOOR FUNCTIONAL TEST PROCEDURE FTP S604-323001 R  RECHECKED FO	R  -DOOR MECHANISM RIGGING PARA 5.1.2 -GEAR MANUAL RELEASE PARA5.6.4 -LANDING GEAR FUNCTIONAL CHECK PARA 5.8  MINOR ADJU	STMENT DONE TO R/H NOSE DOOR ACTUATING ROD SYS WAS CHECKED AND FOUND OK AND ACFT WAS RELEASED FOR FLIGHT TEST.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081106		SW  	2008	11	6	CA080606002      	1	20080603	G	6410	212010750113	BLADE           			BELL  	205   	205B        	       	SW  	LYC   	T53   	T5313B      	41549	NE  					TAIL ROTOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			573  								(CAN) PILOT REPORTED PEDAL VIBRATIONS THROUGHOUT THE DAYS FLYING.  AD-2008-10-03 CLEAN AND INSPECT T/R BLADES WAS SCHEDU	LED FOR THE 25 HRS AME INSP PORTION OF THE AD AFTER THE DAYS FLYING.  AME INSPECTED T/R BLADES AND DETERMINED ONE BLADE 	TO BE UNSERVICEABLE DUE TO POSSIBLE CRACK. THE SUSPECT DEFECT IS LOCATED AT A 45 DEGREE ANGLE ON/THRU THE MAIN SPAR APRO	X .333 OF BLADE LENGTH OUT FROM THE ROOT. THE DEFECT IS APROX 2 INCHES IN LENGTH. T/R BLADE REPLACED WITH SERVICEABLE UN	IT AND SENT FOR FURTHER INSP. THERE HAVE BEEN NO DAMAGE OR ABNORMAL INCIDENTS NOTED TO HAVE AFFECTED THE BLADE, AND THER	E ARE NO INDICATIONS OF ANY IMPACT OR OTHER DAMAGE IN THE SUSPECT AREA.  WILL SEND ADDITIONAL INFO AFTER INSPECT THE BLA	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081106		SW  	2008	11	6	CA080606004      	1	20080604	G	2740	C200G3R	SWITCH          			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	STAB TRIM	INTERMITTENT    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) LT SAS FAILED AND ALL STAB TRIM FUNCTIONS FAILED. MASTER DISCONNECT SWITCH REPLACED AND TEST FLIGHT CARRIED OUT SE	RVICIBLE.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081106		SW  	2008	11	6	CA080606005      	1	20080516	G	3246	LM29749	BEARING         			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LH NOSE WHEEL	LACK OF LUBE    	W				D				RETURN TO BLOCK         				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI FOR DEPARTURE THE PILOT NOTICED A VIBRATION FROM THE NOSE GEAR. HE RETURNED AND MAINT FOUND LT NOSE WHEEL 	INNER BEARING SEAL WAS STICKING OUT FROM ITS SEAT. WHEEL BEARING WAS ALSO FOUND TO BE ROUGH TO THE (FEEL) AND WERE DRY. 	 NOSE WHEEL ASSY REPLACED AND CHECKS CARRIED OUT SERVICIBLE.				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081229		NE  	2008	12	29	CA080606008      	2	20080530	G	7321	350A57147620	CONTROL LEVER   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					FCU	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GOVERNOR LEVER P/N 350A57-1476-20 WAS FOUND ON FCU WHERE LEVER P/N 350A57-1472-20 SHOULD HAVE BEEN. UPON CONFIRMAT	ION WITH MFG THIS WAS CONFIMED. AS THIS ACFT CAME TO US, ON B2 S/N 1685 WE ASSUMED THAT THE INSTALLATION WAS CORRECT. TH	E RIGGIN WAS WAY OUT AND WE COULD NOT REACH THE REQUIRED RPM. LEVER WAS REPLACED, RIGING WAS CARRIED OUT AND THE ACFT WA	S RETURNED TO SERVICE.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081106		EU  	2008	11	6	CA080608003      	1	20080603	G	2752		NUT             	TALLEY      	1251T100    	BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FLAP ACTUATOR	STRIPPED        	W				C				ABORTED TAKEOFF         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING A TRAINING FLIGHT, ON OVERSHOOT FROM A ABORTED LANDING, FLAPS RETRACTED UN-COMMANDED. PILOT REDUCED POWER A	ND WAS ABLE TO LAND STRAIGHT AHEAD ON REMAINING RUNWAY. INSPECTION FOUND THE FLAP ACTUATOR STRIPED.  ACTUATOR WAS REMOVE	D AND SENT FOR OVERHAUL.  OVERHAUL FACILITY REPORT THAT THE STRIPPED BRASS NUT WAS MADE OF A SOFTER THAN STANDARD MATERI	AL.  THERE WAS IN EVIDENCE IN THE AVAILABLE LOGS OF THE TIME IN SERVICE SINCE NEW OR OVERHAULED. OVERHAULED ACTUATOR WAS	 RE-INSTALLED IN ACFT.		1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
	20081106		SW  	2008	11	6	CA080609004      	1	20080603	G	2742	DL5040M6	ACTUATOR        			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	PITCH TRIM	UNRESPONSIVE    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA				6486 							(CAN) SHORTLY AFTER DEPARTING, AND ACCELERATING THROUGH 200KTS, THE PITCH TRIM STOPPED RESPONDING. TRIM SONALERT WAS SOU	NDING WHENEVER THE TRIM SWITCH WAS USED, HOWEVER THE TRIM GAUGE WAS NOT MOVING AND THE ACFT CERTAINLY WAS NOT TRIMMING. 	THIS WAS ATTEMPTED ON THE CAPTAIN AND F/O`S SIDE, AS WELL AS THE STANDBY TRIM SWITCH ON THE PEDESTAL. THE CREW REDUCED P	OWER TO MAKE CONTROLLING THE A/C EASIER AND USED THEIR KNEES TO KEEP THE ACFT LEVEL AND CONTINUED. AS THE ACFT SLOWED FO	R ARRIVAL, THROUGH ABOUT 180 KTS, THE TRIM BEGAN RESPONDING AGAIN. THE ACFT LANDED NORMALLY AND MAINT WAS INFORMED.  MAI	NT REPLACED THE PITCH TRIM ACTUATOR AND THE PROBLEM HAS NOT REOCCURRED. THE ACTUATOR WILL BE SENT FOR REPAIR/OVERHAUL AN	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081105		SW  	2008	11	5	CA080609005      	1	20080605	G	7500	27621009	TUBE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					BLEED AIR	LEAKING         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				21639							(CAN) THE CREW OF THE ACFT REPORTED LOW POWER FROM THE NR 1 ENGINE. DURING THE COURSE OF TROUBLESHOOTING MX SUSPECTED A 	BLEED AIR LEAK CAUSED BY A CRACK IN THE BELLOWS FOR THE BLEED AIR LINE. THIS FLEXIBLE JOINT IS COVERED IN A WIRE HEAT SH	IELD AND UPON CUTTING AWAY THE SHIELD TO INSPECT THE BELLOWS IT WAS DISCOVERED THAT THE LEAK WAS ORIGINATING FROM THE SE	AM WHERE THE BELLOWS ARE FITTED TO THE RIDGED TUBING. THIS PART WAS MANUFACTURED IN 1980 AND IS BELIEVED TO BE ORIGINAL 	EQUIPMENT. ANY DEFECT IN THIS AREA WOULD BE IMPOSSIBLE TO DETECT ON A VISUAL INSPECTION.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20081106		SW  	2008	11	6	CA080609006      	1	20080531	G	2120	2784142007	DUCT            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	BLEED AIR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSP IT WAS DISCOVERED VISUALLY THAT A BLEED AIR LINE TO THE HEAT EXCHANGER OF THE AIR CYCLE MACH	INE HAD CRACKED 2 INCHES, ABOUT ONE THIRD THE CIRCUMFERENCE OF THE TUBE.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081106		EA  	2008	11	6	CA080609007      	1	20080606	G	2751	601R590141	DETECTOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FALSE ACTIVATION	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			9197 	9197 							(CAN) ON APPROACH CREW RECEIVED `FLAPS DEGRADED` MESSAGE ON EICAS, WHEN FLAPS SELECTED TO 45DEG, FLAPS CONTINUED TO SELE	CTED 45DEG POSITION. AFTER LANDING WHEN SELECTING FLAPS UP, CREW RECEIVED `FLAP FAIL MESSAGE AND FLAPS REMAINED AT 43DE	G. MAINT OBTAINED FAULT CODES INDICATING SKEW DETECTION ISSUE. FLAPS RESET AND ACFT FERRIED TO MAINT BASE. MAINT INSP FO	UND NO OBVIOUS FAULTS AND FLAP OPERATION NORMAL. SKEW DETECTOR BOX REMOVED AND REPLACED WITH DUMMY BOX. ACFT RETURNED TO	 SERVICE UNDER MEL FOR FLAP SKEW DETECTION UNSERVICEABLE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081106		EU  	2008	11	6	CA080609009      	1	20080604	G	5753	13760B462	ATTACH FITTING  			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	FLAP SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT A 7 DAY SERVICE CHECK, TECH FOUND 3 FLAP TO SLAT ATTACHEMENT CLEATS, P/N`S 137201B88, 137202B62	 AND 137203B57 WERE FOUND TO BE CRACKED. THE FLAP SECTION WAS REMOVED AND A SERVICEABLE UNIT INSTALLED.  FUNCTION CHECKS	 CARRIED OUT WITH NO FAULTS FOUND AND THE ACFT RELEASED TO SERVICE. THIS IS A KNOWN FAULT WITH THE BAE 3112 ACFT.				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
	20081106		SW  	2008	11	6	CA080610001      	1	20080609	G	6230	206010467105	LEVER           			BELL  	206   	206B        	1181511	SW  										SWASHPLATE	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) MFG HAS BEEN MADE AWARE THAT A QUANTITY OF 94 LEVER ASEMBLIES HAVE BEEN MIS-IDENTIFIED AS -107 INSTEAD OF -105 AS 	REQUIRED BY ENGINEERING DRAWING NOTE. -105 IS A TIME LIFED COMPONENT AND GOVERNED BY MM CHAPTER 4 , -107 IS NOT.					1	G	7	1 	3U				H2SW    					 
	20081106			2008	11	6	CA080610003      	1	20080609	G	5751	25W181001501	SKIN            																	LT AILERON	DELAMINATED     	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			4411 								(CAN) WHILE ON DECENT THROUGH 32,000 FT ENROUTE A MUFFLED BANG WAS HEARD BY THE CREW OF THE ACFT. AFTER A REVIEW OF THE 	ACFT INDICATIONS AND HANDLING AND GENERAL CONDITION, IT WAS UNCERTAIN WHERE THE NOISE HAD COME FROM. IT HAD BEEN THOUGHT	 THAT IT MAY HAVE BEEN A CABIN SLIDING DOOR. NO PROBLEMS WERE ENCOUNTERED ON THE APPROACH OR LANDING. MAINT DURING A POS	T FLIGHT WALK AROUND FOUND THE LT AILERON UPPER SURFACE DELAMINATING FROM THE HONEYCOMB STRUCTURE FROM ABOUT HALFWAY OUT	 THE AILERON TO THE INBD EDGE. REPLACEMENT AILERON ON ORDER AND THE DAMAGED ONE WILL BE SENT FOR FURTHER INVESTIGATION.															 
	20081106		EA  	2008	11	6	CA080611001      	1	20080524	G	2997	M2750012MW3U00	WIRE            			CNDAIR	CL600 	CL600*      	1900302	EA  										HYD SYSTEM	DAMAGED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE RUNNING ACFT HYDRAULIC SYS IN HANGAR FOR CONTROL SYS FUNCTIONAL CHECKS, AN AUDIBLE BANG WAS HEARD FROM THE B	ACK OF THE CABIN, ALONG WITH A FLASH. (INTERIOR IS REMOVED). CIRCUIT BREAKER FOR HYDRAULIC SYS NR1 (B161) POPPED SHORTLY	 AFTER THIS OCCURRENCE. UPON INVESTIGATION FOUND DAMAGE WIRE HARNESS BELOW FLOORBOARD AT FS520 BETWEEN BL19 AND BL27. WI	RES AFFECTED ARE:  HYDR SYS NR1 TRIPLE TWISTED ALL ARE ARCED AND SEVERED: DB93A12WHT, DB94A12BIU, DB95A12ORN, HYDRAULIC 	SYS NR2 TRIPLE TWISTED INSULATION IS DAMAGED AND MELTED: DB81A12WHT, DB82A12BIU, DB83A12ORN - HYDRAULIC SYSTEM NR3 TRIPL	E TWISTED SOOT ON THE WIRE INSULATION  WIRES CABLE P/N M27500-12MW3U00 IS KAPTON WIRE.	2	L	7	2 	4F			RT	A21EA   					 
	20081106		SW  	2008	11	6	CA080611002      	1	20080318	G	6220	C807382	BEARING RACE    			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					PUSH-PULL	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5059 								(CAN) THE PUSH-PULL CONTROL ASSY CENTER RACE FRACTURED AS A RESULT OF FATIQUE. THE FRACTURE OCCURED NEAR WHERE THE ASSY 	WAS LOCATED IN AN INSTALLATION-INDUCED BEND RADIUS.					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
	20081106		SW  	2008	11	6	CA080611003      	1	20080606	G	2820	412061634105	VENT LINE       			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2307 								(CAN) FOUND RT FUEL VENT LINE P/N 412-061-634-105 HAS RUB MARK AT WL 41. LENGTH 0.700X0.100. LOCATION: RT DOOR POST PANE	L. CUT MADE WITH SHARP EDGE OF BOTTOM FOOT DOOR.					1	G	7	2 	4U				H4SW    					 
	20081106		GL  	2008	11	6	CA080611005      	1	20080609	G	5551	BSFS159160	ATTACH BRACKET  			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN1     	52008	NE  					HORIZONTAL STAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			692  								(CAN) DURING ANNUAL INSP WITH AN AOG AIR SUPPORT WING ANGLE INSTALLED MODIFICATION, MOVEMENT WAS FOUND IN THE HORIZONTAL	 STABILIZER FWD ATTACH POINTS. THE HORIZONTAL STABILIZER FWD ATTACH BRACKETS WERE REMOVED AND INSPECTED AND IT APPEARS T	HAT THE FUSELAGE FITTING WAS WEARING INTO THE HORIZONTAL STABILIZER ATTACH FITTING (PN BSFS-159/160).				1	H	7	1 	3R	3	R	RC	A806    	5E1				 
	20081230		NE  	2008	12	30	CA080611006      	2	20080525	G	7200	0292005220	ENGINE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  						MAKING METAL    	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			8428 								(CAN) WHILE DOING AIRBORNE SURVEY WORK (BIRD TOWING), ENGINE CHIP LIGHT ILLUMINATED. HELICOPTER DESCENDED TO VALLEY BOTT	OM AND MADE A PRECAUTIONARY LANDING.  UPON LANDING, THE ENGINE MOMENTARILY DECELLERATED AND THEN RE-ACCELERATED. ENGINE 	WAS SHUTDOWN AND RAPIDLY DECELERATED ACOMPANIED BY A GRINDING/RUBBING NOISE. POST FLIGHT INSPECTION REVEALED A LARGE AMO	UNT OF METAL CHIPS ON THE ENGINE CHIP PLUGS.  ENGINE REMOVED AND SENT TO MFG FOR FURTHER INVESTIGATION.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081106		WP  	2008	11	6	CA080611007      	2	20080610	G	7200	31080981	BEARING         			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33110    	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				13   							(CAN) THE REAR TURBINE WAS FOUND WITH HEAVY SPALLING, GALLING, HEAVY SCORING AND MISSING MATERIAL OFF THE OUTER RACEWAY 	AND ON THE ROLLING ELEMENTS. THE BEARING HAD ONLY 12.5 HOURS SINCE NEW/CAM. THE ENGINE WAS MAKING A STRANGE GRINDING SOU	ND THAT WAS NOTICED BY LINE MAINT.  ANOTHER REAR TURBINE BEARING FAILED ON ENGINE P44436C INSTALLED ON AC. THE BEARING O	NLY HAD 16.4 HOURS ON IT. INVESTIGATION CARRIED OUT AND BOTH BEARING WERE RECIEVED ON THE SAME PO. THE PO CAME IN WITH 4	 BEARING, ANOTHER ONE DISCOVERED ROUGH TO SPIN IN INVENTORY. REMOVED REMAINING 4TH BEARING FROM OUR SYS. MFG CONTACTED I	N REGARDS OT THE SITUATION POINTING TOWARDS BAD BATCH. MFG IS RESEARCHING THE PROBLEM.  ALL CONTACTED TO ASSIST IN PROBL	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081106		SW  	2008	11	6	CA080611009      	1	20080605	G	3246	31418A	BEARING SEAL    			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG WHEEL	DISPLACED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PREFLIGHT WALK AROUND OF THE ACFT THE INNER BEARING SEAL OF THE RT NOSE WHEEL ASSY WAS NOTED TO BE DISPLA	CED SO THAT ONE SIDE OF THE SEAL WAS RIDING UP ON THE HUB AND THE OPPOSITE SIDE WAS IN TOWARD THE AXLE TO THE EXTENT THA	T THE BEARING ROLLERS WERE VISIBLE. NOSE WHEEL ASSY REPLACED AND ACFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081106		SW  	2008	11	6	CA080611010      	1	20080610	G	3246	LM299710	BEARING RACE    			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NOSE WHEEL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE INNER SEAL WAS NOTED TO BE PROTRUDING MORE THAN NORMAL. WHEEL ASSY WAS REMOVED AND THE INNER RACE WAS FOUND TO	 NOT BE SEATED ALL THE WAY. SERVICEABLE WHEEL ASSY WAS INSTALLED ON THE ACFT AND ACFT RETURNED TO SERVICE.					2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE	 
	20081106		EA  	2008	11	6	CA080612001      	1	20080611	G	5753	600143023	VANE            	BOMBDR      		CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348E5A1   	30062	NE  					TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A DAILY INSPECTION, THE LT INBD FLAP VANE WAS FOUND CRACKED ON THE UPPER SURFACE. THE CRACK IS APPROXIMATEL	Y 2 INCHES LONG. FLAP TO BE REMOVED AND SENT OUT FOR FLAP VANE REPLACEMENT. LOANER FLAP TO BE INSTALLED.					2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081113		NE  	2008	11	13	CA080612002      	2	20080605	G	7200		ENGINE          								PWC   	PW615 	PW615FA     	52282	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) DURING LANDING TOUCHDOWN AND BRAKING, BOTH ENGINES REPORTEDLY INCREASED UNCOMMANDED TO FULL POWER. CREW ABORTED LA	NDING AND PERFORMED A GO-AROUND. DURING BASE LEG, TO CONTAIN AIRSPEED CREW SHUT DOWN RT ENGINE AND AT THIS TIME THE LT E	NGINE POWER REDUCED TO FLIGHT IDLE, UNCOMMANDED WITH NO THROTTLE RESPONSE. CREW PERFORMED A LANDING WITH NO INJURES. THE	 ACFT SUSTAINED 2 BLOWN TIRES. ON SITE INVESTIGATION, DATA DOWNLOADS AND ANALYSIS INDICATES AN ISSUE WITH THE THROTTLE Q	UADRANT. THE CAS MSGS AND EVENTS REPORTED BY THE FLIGHT CREW WERE DUPLICATED DURING SIMULATION TESTING. THE NTSB HAS RET	AINED THE QUADRANT FOR FURTHER INVESTIGATION.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE 						4	F			E00073EN				 
	20081106		EA  	2008	11	6	CA080612003      	1	20080612	G	2820	C6PF1034105	LINE            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FUEL SYSTEM	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) A NEW FUEL TUBE ASSY WAS TO BE INSTALLED BETWEEN FUEL CELL NR 4 AND NR 6. THE INSTALLER FOUND THE TUBE ASSEMBLY TO	 BE .7500 INCHES TOO SHORT FOR THE LOCATION.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
	20081106		EA  	2008	11	6	CA080612004      	1	20080612	G	2820	C6PF103479	LINE            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FUEL SYS	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) A NEW FUEL TUBE ASSY WAS TO BE INSTALLED BETWEEN FUEL CELL NR 5 AND NR 8 AS PART OF THE MOTIVE FLOW SYS. THE INSTA	LLER FOUND THE TUBE ASSY TO BE ONE INCH TOO LONG FOR THE LOCATION.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
	20081106		NE  	2008	11	6	CA080612005      	2	20080612	G	7414		BEARING         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			453  								MAG RECEIVED FOR 500 HOUR INSP. BEFORE DISASSEMBLY 0.003 INCH OF END PLAY WAS NOTICED AT THE ROTOR. THIS WAS A FACTORY N	EW MAG. MFG REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THE MAG BEARINGS WERE INSPECTED FOR DAMAGE AND NONE WAS FOU	ND. THE BEARINGS WERE PROPERLY SHIMMED DURING THE 500 HOUR INSP AND THE MAG WAS RETURNED TO SERVICE.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081106		NE  	2008	11	6	CA080612006      	2	20080612	G	7414		BEARING         	BENDIX      		ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			501  								(CAN) MAG WAS RECEIVED FOR A 500 HOUR INSP BEFORE DISASSEMBLY 0.004 INCH OF END PLAY WAS NOTICED AT THE ROTOR. THIS WAS 	A FACTORY NEW MAGNETO. REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THE MAG BEARINGS WERE INSPECTED FOR DAMAGE AND N	ONE WAS FOUND. THE BEARINGS WERE PROPERLY SHIMMED DURING THE 500 HOUR INSPECTION AND THE MAG WAS RETURNED TO SERVICE.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081106			2008	11	6	CA080612007      	2	20080612	G	7414		BEARING         																	MAGNETO	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) MAG WAS SOLD TO A CUSTOMER AS AN EXCHANGE UNIT. WHEN INSTALLING THE CUSTOMERS MAGNETO DRIVE 0.004 INCH OF END PLAY	 WAS NOTICED AT THE ROTOR. MFG REQUIRES 0.0005 TO 0.0015 INCH END PLAY AT ASSY. THIS WAS A FACTORY REBUILT MAGNETO. THE 	MAG WAS REPAIRED BY PROPERLY SHIMMING THE BEARINGS AND RETURNED TO SERVICE.																	 
	20081113		CE  	2008	11	13	CA080613004      	1	20080605	G	3250	AN310A	BOLT            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					COCKPIT	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LEFT RUDDER PEDAL SYSTEM INSPECTED TO VERIFY CLEARANCE BETWEEN THE BOLT AND NUT HOLDING THE BRAKE BELLCRANK LOCATE	D BESIDE THE RIGHT RUDDER PEDAL ARM BAR ON THE PILOT SIDE AND THE NOSE GEAR STEERING ARM TUBE ATTACHMENT. BOLT WASHER AN	D NUT REPOSITIONED TO ALLOW CLEARANCE. MINOR INTERFERENCE NOTED PRIOR TO REPOSITIONING. INSPECTION CARRIED OUT AFTER FIN	DINGS AS DESCRIBED IN SDR 20080613002 (TC# 20080613004)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081106		CE  	2008	11	6	CA080613005      	1	20080604	G	2720	AN310A	BOLT            	CESSNA      		CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	RUDDER PEDAL	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) LT RUDDER PEDAL SYS INSPECTED TO VERIFY CLEARANCE BETWEEN THE BOLT AND NUT HOLDING THE BRAKE BELLCRANK LOCATED BES	IDE THE RT RUDDER PEDAL ARM BAR ON THE PILOT SIDE AND THE NOSE GEAR STEERING ARM TUBE ATTACHMENT. BOLT WASHER AND NUT RE	POSITIONED TO ALLOW CLEARANCE. MINOR INTERFERENCE NOTED PRIOR TO REPOSITIONING. INSP CARRIED OUT AFTER FINDINGS AS DESCR	IBED IN SDR 20080613002.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081106		SW  	2008	11	6	CA080613007      	1	20080605	G	3000	2719156003	TRANSDUCER      			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  					DE ICE SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6918 								(CAN) PILOT REPORTED DEICE PRESSURE GAUGE UNSERVICEABLE. DURING TROUBLESHOOTING MAINT FOUND THE DEICE PRESSURE TRANSDUCE	R CONTAMINATED WITH WATER.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE				 
	20081106		WP  	2008	11	6	CA080613009      	1	20080603	G	2435	BC3151004	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			824  								(CAN) STARTER INTERMITTENT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081106		CE  	2008	11	6	CA080613010      	1	20080611	G	6120	A3495	LOCK PLATE      			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			99   	99   							(CAN) DURING A ROUTINE PROP INSP, IT WAS FOUND THAT THE PITCH LOCK PLATE ALLOWS THE LATCH PIN TO SLIP OFF THE EDGE AND C	OULD JAM THE PIN. THIS COULD PREVENT IN FIGHT ENGINE START.					1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
	20081106		SW  	2008	11	6	CA080614001      	1	20080612	G	2910		LINE            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317BLYC   	41616	NE  					HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	F		FLUID LOSS                	FLT CONT AFFECTED         		HO	HOVERING       	1			CA											(CAN) THE PILOT WAS FLYING THE HELICOPTER WHEN THE COLLECTIVE BECAME STIFF TO MOVE. THE PILOT RELEASED THE LOAD AND NR 2	 HYDR SYS HAD FAILED. THE PILOT LANDED THE ACFT. IT WAS FOUND THAT NR 2 HYD SYS HAD LOST ALL IT`S FLUID DUE TO A HYDRAUL	IC LINE HAD CHAFED THROUGH CREATING A HOLE. MORE DETAILS ARE COMING.				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081106		NE  	2008	11	6	CA080616001      	2	20080611	G	7250		TURBINE         								PWA   	PW120 	PW123       	 	NE  					ENGINE	OUT OF BALANCE  	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			18667	10033							(CAN) EI PW100 2008-059 - VIBRATIONS DURING START, IT HAS BEEN DETERMINED THAT THE POWER TURBINE WAS OUT OF BALANCE THUS	 CAUSING THIS EVENT. (PRE SB21737)										4	T			E20NE				 
	20081105		EU  	2008	11	5	CA080616002      	1	20080611	G	2820	5282412189	LINE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					FUEL SYS	CORRODED        	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) MX FOUND FUEL LEAKING FROM CENTER BELLY PANEL AND DURING INVESTIGATION FOUND A CORRODED FUEL LINE.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
	20081106		CE  	2008	11	6	CA080616003      	1	20080611	G	2612	24418922	FIRE LOOP       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	NACELLE	LOOSE           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			13987	13987							(CAN) ENGINE FIRE WARNING INDICATION CAME ON IN FLIGHT. THE ENGINE WAS REPLACED THE PREVIOUS DAY AND THE FIRE WIRE MAY H	AVE BEEN DISTURBED AT THAT TIME. THE PILOT LANDED AND THE FIRE WIRE WAS REPLACED AND CHECKED SERVICEABLE.					1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20081106		EA  	2008	11	6	CA080616004      	1	20080615	G	2750	860D10018	FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					FLAP SYSTEM	UNSERVICEABLE   	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FLAP FAIL CAUTION MESSAGE ON FLAP RETRACTION. FLAPS WERE SELECTED FROM 8, 0 AND THE FLAP FAIL HAPPENED WITH FLAPS 	NOW INDICATING 0 ON EACH SIDE. A/C LANDED OVERWEIGHT DUE TO RETURNING WITH FLAP FAIL  FDR DATA RETRIEVED AND CALCULATED 	LANDING VERTICAL SPEED TO BE AT MOST 300 FT/SEC. THIS IS WELL BELOW THE MAX ALLOWABLE OF 360 FT/SEC. NO HEAVY LANDING CH	ECK REQUIRED. FECU SHOWS THAT FECU HAS FAILED. TECH OPS ACTION PLAN FOR THE INPUT TORQUE OF THE FLAP DRIVE SYS COMPLETED	. NO FAULTS FOUND. WIRING FROM FECU TO FLAP HANDLE, LT AND RT BPSU`S RANG OUT AND ALL CHECKED OK. FECU REPLACED. GROUND 	TESTED SERVICEABLE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081106		EU  	2008	11	6	CA080616005      	1	20080611	G	2731	Z4244170000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ELEVATOR TAB	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3800 								(CAN) AFT ELEVATOR TRIM CABLE WAS DISCOVERED FRAYED DURING REGULARLY SCHEDULED MAINT. IT WAS SURMISED THAT FURTHER OPERA	TION OF THE TRIM SYS WOULD HAVE LED TO SYS FAILURE BEFORE THE NEXT SCHEDULED INSPECTION.					1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
	20081106		CE  	2008	11	6	CA080617001      	1	20080610	G	5720		SUPPORT         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SPEED BRAKES	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE OTBD HOLE IN THE SPEED BRAKE TRUNNION SUPPORT IS ABOUT .5 HOLE MISALIGNED WITH THE HOLE IN THE RIB WHERE THE U	PPER OTBD AILERON CABLE PASSES THROUGH ON BOTH THE LT AND RT WING. THE AILERON CABLES WERE WORN AND HAD WORN INTO THE AF	T SIDE OF THE HOLE IN THE TRUNNION SUPPORTS. REPAIR S-550-0699/04RD WAS ISSUED TO BLEND THE TRUNNION SUPPORT AND THE AIL	ERON CABLES WERE REPLACED.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081106		CE  	2008	11	6	CA080617002      	1	20080418	G	5343	05430161	FITTING         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			7960 								(CAN) AS THE ACFT WAS TAKING OFF, THE NOSE GEAR COLLAPSED. THE ACFT WAS INSPECTED AND THE NOSE GEAR LOWER FITTING WAS FO	UND BROKEN. IT IS UNDETERMINED AT THIS TIME IF THIS WAS A RESULT OF AN UNREPORTED HARD LANDING. RETAINED THE BROKEN PART	 TO CARRY OUT METALLURGY TESTS.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081106		NE  	2008	11	6	CA080617003      	2	20080607	G	8530		EXHAUST VALVE   			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	R2800CA3    	52026	NE  	HAMSTD	43E	43E60       	NE  	NR 9 CYLINDER	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA				970  							(CAN) DURING CRUISE, THE FLIGHT CREW HEARD THE NR1 ENGINE BACKFIRE. THE ENGINE WAS SHUTDOWN AND THE PROPELLER FEATHERED.	 DURING INVESTIGATION, THE MAINT CREW DISCOVERED THE EXHAUST VALVE IN CYL NR 9 HAD DROPPED INTO THE CYL. SOME PIECES OF 	THE VALVE WENT OUT THE EXHAUST PIPE. THE CYL WAS REPLACED, ENG GROUND RUN  AND THE MAIN OIL SCREEN WAS INSPECTED. THE AC	FT WAS RETURNED TO SERVICE.			2	H	7	2 	4R	4	R	RT	A14EA   	5E8	6	C	P871	 
	20081106		EU  	2008	11	6	CA080617004      	1	20080616	G	3040		SHAFT           			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					WINDSHIELD WIPER	SHEARED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ACFT ARRIVED AT GATE WITH CAPTAINS WINDSHIELD WIPER ASSEMBLY MISSING. FURTHER INVESTIGATION FOUND THAT CONVERTER 	SPLINED SHAFT HAD SHEARED OFF CAUSING THE WIPER ASSY TO DEPART ACFT WHILE TAXIING IN FROM LANDING TO APRON. WIPER ASSY W	AS FOUND IN TAXIWAY. CONVERTER ASSY REPLACED.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20081106		NM  	2008	11	6	CA080618001      	1	20080615	G	3233	AS11510K0330	HOSE            			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					MLG ACTUATOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) LT TRUCK TILT ACTUATOR RETURN LINE FOUND LEAKING.						2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
	20081230		SW  	2008	12	30	CA080618002      	1	20080616	G	2510	AAL292030001	SEAT FRAME      			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COCKPIT SEAT	INTERFERENCE    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING THE INSTALLATION OF VERTICAL REFERENCE SEAT KIT, IAW STC SH06-31, IT WAS DISCOVERED THAT THE CYCLIC FLIGHT 	CONTROL STICK IS INTERFERED WITH DUE TO THE SEAT NOW BEING POSITIONED FURTHER FWD AND ELEVATED BECAUSE OF THE KIT INSTAL	LATION. AN ELEVATION OF THE INSTALLATION IS ATTACHED TO PROVIDE DETAILS OF THIS ISSUE. THE CYCLIC CONTROL STICK CONTACTS	 THE SEAT FRAME WHEN THE SEAT IS TILTED. THE CYCLIC CONTROL STICK IS NOT ABLE TO CONTACT THE CONTROL STOP WHEN THE SEAT 	IS IN THE TILTED POSITION.		1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081106		NE  	2008	11	6	CA080618003      	2	20080602	G	7261		SEAL            								PWA   	PT6   	PT6A60      	52043	NE  					NR 1 BEARING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING ENG COMPRESSOR RECOVERY WASH, ENGINE OIL LOSS FROM NR 1 BEARING SEAL. MULTIPLE ENGINE SPOOLS ARE REQUIRED T	O COMPLETE AN ENG COMPRESSOR RECOVERY WASH IAW ENG MFG. MAINT FOUND IN CARRYING OUT MULTIPLE ENGINE SPOOLS, INTERNAL ENG	 SCAVANGE PUMPS LOCATED IN THE AGB WERE NOT EFFICIENT ENOUGH THROUGH THE SPOOLING PROCESS AT LOW ENG SPEEDS TO SUCSESSFU	LLY SCAVANGE ENOUGH ENGINE OIL OUT OF THE AGB TO AVOID AN OVER FILL CONDITION OF THE AGB. SCAVANGE PUMPS ARE DESIGNED TO	 TAKE THE USED ENGINE OIL FROM THE AGB AND RGB AND PUMP THE OIL BACK INTO THE MAIN ENGINE OIL RESERVOIR. MAINT FOUND DUR	ING ENGINE SPOOLING ALONE, THE PUMPS COULD NOT KEEP THE OIL AT A SAFE LEVEL IN THE AGB IN ORDER TO AVOID THE OIL TO SEEP						4	T			E4EA				 
	20081106		NM  	2008	11	6	CA080618004      	1	20080613	G	5210	BACS12ER06K6	SCREW           			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					PAX DOOR ARM	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17134	17134							(CAN) L1 MAIN CABIN ENTRANCE DOOR WAS FOUND TO HAVE RESTRICTED OPERATION FOR OPENING AND CLOSING UPON ARRIVAL AT THE GAT	E. GUIDE ARM LWR RADIUS LINK ATTACHING SCREW AND KEY WASHER WERE FOUND MISSING. PARTS REPLACED. SINCE THIS HAS OCCURRED 	RECENTLY ON ANOTHER ACFT IS PROCEEDING WITH A PRECAUTIONARY FLEET CAMPAIGN TO INSPECT THE L1 AND L2 DOOR HINGE ARM LINKS	 AND HARDWARE FOR CONDITION AND SECURITY. THIS WILL BE CARRIED OUT ON WJIS ENTIRE FLEET OF 737 NGS AND SHOULD BE COMPLE	TED WITHIN 90 DAYS OF THE CAMPAIGN DETAILS BEING FINALIZED.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
	20081106		NE  	2008	11	6	CA080618005      	2	20080616	G	7200	6018T30P14	BLADE           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					ENGINE FAN	BENT            	W				O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			CA											(CAN) FLIGHT INGESTED A BIRD INTO THE NR1 ENGINE ON APPROACH. MTC INSPECTED AND FOUND A BENT FAN BLADE. ACFT TAKEN OUT O	F SERVICE FOR A FAN BLADE REPLACEMENT. THIS WAS REPORTED BY THE CREW PICKING UP THE ACFT FOR THE NEXT FLIGHT, AFTER THEI	R WALK AROUND. BENT FAN BLADE FOUND ON THE NR 1 ENGINE AFTER EVIDENCE OF BIRD INGESTION REPORTED BY THE PILOT.  ADVISES 	THAT THE BIRD WENT THROUGH THE CORE. CONTAMINATION FOUND THROUGHOUT THE COMPRESSOR. COMPRESSOR WASH REQUIRED. BLADE REPL	ACEMENT IN PROGRESS.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081105		EA  	2008	11	5	CA080618006      	2	20080508	G	8530	LW16740	VALVE           	LYC         							LYC   	O540  	TIO540A2C   	41532	EA  					VALVE STEM	ELONGATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2700 								(CAN) VALVE STREACHED TO 6 THOU AND MANUFACTURES LIMITATION IS 2 THOU. CONCERN IS VALVE IS SODIUM FILLED AND WILL DISINT	IGRATE IF THE STREACH IS BEYOND MANUFACTURES RECOMMENDATIONS. THE MAIN CONCERN IS THIS ENGINE IS ON CONDITION AND THE CY	LINDERS ALL HAVE 2700 HOURS ON THEM AND IF ONE IS STREACHED THE QUESTION NOW IS ARE ALL THE VALVES STREACHED. THE POINT 	BEING IF YOU ARE WORKING ON AN AIRCRAFT THAT IS GOING ON CONDITION IT IS CLEAR THE VALVES NEED TO BE CHECKED BEFORE THE 	ENGINE GOES ON CONDITION.							3	O			E14EA				 
	20081105		EA  	2008	11	5	CA080618007      	2	20080602	G	8530	LW16703	CYLINDER        								LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA				225  							(CAN) THE LOWER SPARK PLUG HOLE ON CYLINDER NR 4 HAD A CRACK, THE ACFT HAD BEEN INSPECTED ON MAY 24/08 AND THERE WAS NO 	APPARENT CRACKS OR ISSUES WITH THE CYLINDER, ON JUNE 2 IT WAS RUNNING ROUGH AND BROUGHT TO MX, THERE WAS FOULING OF THE 	PLUGS AND WHEN THE PLUG WAS REMOVED THE FINE CRACK WAS NOTED. THE OTHER CYLINDERS WERE INSPECTED AND FOUND TO BE CLEAR O	F ANY CRACKS. THIS ENGINE HAD BEEN OVERHAULED 225 HOURS PREVIOUSLY AND THE CYLINDERS WERE OVERHAULED AS WELL. THE RECORD	S SHOWED THAT THE CYLINDERS WERE OVERHAULED AS PER MANUFACTURERS SPECIFICATIONS. WE WILL CONTINUE TO MONITOR THE OTHER C	YLINDERS AND WILL REPORT ANY FUTURE ISSUES REGARDING THESE CYLINDERS.						3	O			E223				 
	20081105		EA  	2008	11	5	CA080618008      	2	20080604	G	7314	A10014044	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					FUEL SYSTEM	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHEN POWER WAS APPLIED THE PUMP WOULD OPERATE UNLESS IT WAS TAPPED WITH A HAMMER. PUMP WAS REPLACED AND NO FURTHER	 ISSUES WERE NOTED. WILL SUPPLY HOURS ON THE PUMP IN THE NEXT FEW DAYS.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20081106		SO  	2008	11	6	CA080618009      	1	20080604	G	8120		BOLT            	KELLY       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				15   							(CAN) DURING INSP IT WAS DISCOVERED THAT BOTH BOLTS SECURING THE TURBO TO THE UPPER TURBO SUPPORT HAD COME OUT. THE TURB	O WAS LEAKING EXHAUST GASES FROM THE SEAM BETWEEN THE TURBINE HOUSING AND THE BEARING HOUSING. WILL SUPPLY HOURS OF THE 	TURBO THE NEXT FEW DAYS.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081106		EA  	2008	11	6	CA080618010      	1	20080602	G	5610	NP13932212	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5     	30050	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT COCKPIT SIDE WINDOW SHATTERED WHILE SITTING AT THE GATE. REMOVED AND REPLACED THE RT COCKPIT SIDE WINDOW.						2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081106		NM  	2008	11	6	CA080619001      	1	20080618	G	3220		BUSHING         			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					NLG	MIGRATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, FOUND EVIDENCE OF BUSHING MIGRATED ON NLG RETRACK ACTUATOR , MAIN FITTING ASSY AND UPPER SHOCK 	STRUT ATTACHMENTS (PRC BROKEN).					2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081106			2008	11	6	CA080619002      	4	20080617	G	2565	101651303	SLIDE           																		LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SLIDE UNIT`S HAVE BEEN DEVELOPING PROBLEMS WITH THE ADHESIVE HOLDING MANY OF THE SEAMS TOGETHER AS THEY AGE BEYOND	 THE 20 YEAR THRESHOLD. THERE HAVE BEEN SEVERAL INSTANCES WHERE SLIDE TUBES FROM UNITS MFG CIRCA 1984 HAVE RUPTURED UPON	 INFLATION TEST. MOST RECENTLY, A SLIDE MFG CIRCA 1986 (PN 101651-303, SN B51-325) SHOWED, UPON INFLATION TESTING, THAT 	MANY OF THE SEAMS HAVE BECOME COMPLETED DISBONDED IN AREAS SUCH AS THE CANOPY AS WELL AS IN BETWEEN THE MAIN UPPER AND L	WR INFLATION TUBES. IT APPEARS THAT THE SLIDE UNITS, AS THEY AGE BEYOND 20 YEARS FROM DATE OF MFG, HAVE EXPONENTIALLY IN	CREASING FAILURE RATES AS SHOWN WHEN BROUGHT INTO THE SHOP ENVIRONMENT FOR CHECK/OVERHAUL. ONE CAN ONLY ASSUME THAT FAIL														 
	20081105		CE  	2008	11	5	CA080619003      	1	20080618	G	5343	AN35A	BOLT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TRUNNION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CARRIED OUT VISUAL INSPECTION AS PER CAMPAIGN FOUND 4 BOLTS INSTALLED AND WASHERS AND NUTS. REMOVED HARDWARE INSTA	LLED NEW PARTS AS PER IPC 53-11-01 ITEM 109 AND 110. REPLACED ARM ASSY P/N 5565619-6 WITH NEW DUE DAMAGED AND NEW BOLT P	/N NAS464P5LA28 DUE WORN.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081106			2008	11	6	CA080619004      	4	20080418	G	6122	F624L	GOVERNOR        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA				6    							(CAN) AFTER INSTALLATION OF THE OVERHAULED GOVERNOR, THE TEST FLIGHT WAS CARRIED OUT AND THE ENGINE WAS OVER SPED. THE G	OVERNOR WAS SENT BACK TO THE REPAIR FACILITY, THE FACILITY REPORTS NOTHING ABNORMAL.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081106			2008	11	6	CA080619005      	4	20080619	G	8300	310625801	BEVEL GEAR      								PWA   	120   	PW120A      	 	NE  					ASSY GEARBOX	MISMANUFACTURED 	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) BEVEL GEAR P/N 3106258-01, S/N A0002WAB WAS FOUND TO BE NON-CONFORMING DUE TO MISSING POST PLATE BAKING OPERATION 	AFTER THE PART WAS SILVER PLATED. THIS PART WAS INTALLED IN ENGINE S/N 120673 WHICH WAS ALREADY SHIPPED TO THE CUSTOMER.	 THE CUSTOMER WAS INFORMED BY A LETTER TO RETURNED THE ENGINE WITHIN 60 HRS FLYING TIME IN ORDER TO REPLACED THE PART.									4	T			E20NE				 
	20081106		SO  	2008	11	6	CA080619006      	1	20080323	G	8120	4091709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA				1    							(CAN) AN OVERHAULED ENGINE COMPLETE WITH NEW TURBOCHARGER WAS INSTALLED. AFTER THE FIRST HOUR OF THE FLIGHT THE TURBOCHA	RGER COMPLETELY FAILED. MAINT INSTALLED A NEW TURBOCHARGER AND ACFT RETURNED TO SERVICE.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081106		CE  	2008	11	6	CA080619007      	1	20080617	G	5753	50160018	FLAP TRACK      			BEECH 	100   	A100A       	       	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A WALKAROUND THE PILOTS NOTICED EXCESSIVE PLAY ON THE RT OTBD FLAP AT THE INBD HINGE. THE FLAP WAS REMOVED 	FOR FURTHER INVESTIGATION AND THE INBD FLAP TRACK WAS FOUND TO BE CRACKED AT THE AFT END OF THE TRACK, THE CRACK WEAKEN 	THE TRACK ALLOWING IT TO SLIGHTLY BEND WITH THE FLIGHT LOADS. NO SECONDARY DAMAGE WAS FOUND. THE FLAP TRACK WAS REPLACED	. AND THE ACFT RETURNED TO SERVICE.			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
	20081106		EU  	2008	11	6	CA080619008      	1	20080506	G	2822	P94B12203C	PUMP            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL BOOST	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				221  							(CAN) BOOST PUMP FAILED IN FLIGHT, MOTOR STILL TURNING BUT NOT CREATING PRESSURE. SUSPECT SHEARED SHAFT OR DRIVE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
	20081106		WP  	2008	11	6	CA080620002      	1	20080615	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			139  								(CAN) STARTER WOULD NOT TURN OVER THE ENGINE, TROUBLESHOOTING REVEALED THE STARTER WOULD NOT ROTATE THE STARTER GEAR.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081106		GL  	2008	11	6	CA080620004      	1	20080618	G	5541		SPAR            	DHAV        		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FRONT SPAR WAS FOUND CRACKED AFTER THE RUDDER WAS REMOVED FOR REPLACEMENT OF UPPER HINGE BEARING. FRETTING WAS NOT	ICED AT BEARING BLOCK TO SPAR MOUNTING SURFACE/BEARING BLOCK WAS REMOVED AND CRACKS FROM THE (2) ATTACH HOLES WERE FOUND	. 3 CRACKS FROM ONE HOLE EXTENDED BEYOND THE BEND OF THE FRONT SPAR. RUDDER REMOVED FROM SERVICE FOR REPAIR.				1	H	7	1 	3R	3	R	RC	A806    	5E1				 
	20081106		GL  	2008	11	6	CA080621001      	2	20080611	G	7240	6870992	COMBUST CHAMBER 								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) ENGINE REPORTED HIGH OPERATING TEMP. ATTEMPTED POWER CHECK BUT NOTED 790 DEGREE TOT IN HOVER. ABORTED POWER CHECK 	UPON FURTHER VISUAL INSP FOUND RT ARM PIT CRACKED APPROX 5 INCH CRACK.										3	U			E4CE				 
	20081106		EA  	2008	11	6	CA080622001      	1	20080618	G	3230	750005000	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) CREW TRIED (4) TIMES TO GET THE MLG DOWN. THEY USED THE EMERGENCY FREE FALL, AND THE MAINS CAME DOWN. (THE NOSE WA	S ALL READY DOWN. NO EMERGENCY WAS DECLARED.) CONTACTED REPAIR STATION TO PIN THE LANDING GEAR, AND MAKE READY FOR THE F	ERRY FLIGHT. A/C TO FERRY FOR REPAIRS.  REMOVED AND REPLACED THE MAIN LANDING SELECTOR VALVE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081106		NM  	2008	11	6	CA080623001      	1	20080424	G	3250	69355174	ROD END         			BOEING	737   	737*        	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					STEERING TILLER	WORN            	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			18425								(CAN) MINOR BUT PERSISTENT VIBRATION COULD BE FELT IN THE STEERING TILLER DURING TAXI, PARTICULARLY AT HIGHER SPEEDS.						2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
	20081106		CE  	2008	11	6	CA080623002      	1	20080619	G	3230	AA5C	MOTOR           			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	MLG	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			954  	954  							(CAN) PILOT SELECTED GEAR DOWN THE DOOR MOTOR CIRCUIT BREAKER POPPED. MANUAL GEAR EXTENSION COMPLETED AND ACFT LANDED WI	THOUT INCIDENT. MECHANIC DISPATCHED AND FOUND THE GEAR DOOR ACTUATOR/MOTOR UNSERVICEABLE. ACFT FERRIED TO MAINTENANCE BA	SE, DOOR ACTUATOR/MOTOR REPLACED AND GEAR SWING COMPLETED. ACFT RETURNED TO SERVICE.				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
	20081106		EA  	2008	11	6	CA080623003      	2	20080514	G	8520	LW15628	SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CRANKCASE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				98   							(CAN) DURING 2 ROUTINE INSP OF THE ENGINE, IT WAS DISCOVERED THAT THE CRANKSEAL WAS LEAKING. A NEW SEAL WAS INSTALLED AT	 APPROXIMATLEY 50 HRS. THE NEXT SCHEDULED INSP CARRIED OUT AT 98 HRS REVEALED THE SEAL LEAKING AGAIN. THE ENGINE WAS STI	LL UNDER WARRENTY AND IT WAS DECIDED TO REMOVE THE ENGINE FROM SERVICE AND INSTALL A NEW ONE. THE ENGINE OVERHAUL FACILI	TY WAS REQUESTED TO PROVIDE A TEARDOWN REPORT AS A FOLLOW UP.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081106		EA  	2008	11	6	CA080623004      	1	20080620	G	5200	215260522	SHAFT           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	DOOR	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			4896 	4896 							(CAN) DURING AERIAL FIGHT FIGHTING OPERATIONS, THE PILOTS HEARD A LOUD BANG AFTER DROPPING THEIR LOAD OF WATER. THE "RT 	JACK READY" LIGHT WOULD NOT COME ON AS IT NORMALLY WOULD AFTER THE BOMB DOOR CYCLES AND LOCKS "CLOSED". THE PILOTS RETUR	NED TO BASE IAW COMPANY SOPS. MAINT FOUND THAT THE BOMB DOOR CLOSING JACK MOUNTING SPIGOT WAS SHEARED AND THAT THE ACTUA	TOR WAS HANGING FROM ITS HYDRAULIC LINES. NO OTHER DAMAGE WAS FOUND, THE SPIGOT WAS REPLACED, THE SYS FUNCTION-TESTED AI	RWORTHY,AND THE ACFT RETURNED TO SERVICE.		2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
	20081114		EA  	2008	11	14	CA080623005      	1	20080620	G	5240	601R387271	UPLOCK          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					SERVICE DOOR	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) PILOT REPORTED THAT THE SERVICE DOOR MESSAGE WAS DISPLAYED. MAINT WAS CALLED TO INVESTIGATE THE PROBLEM AND THEY W	ERE TOLD BY THE CREW THAT THE ENGINEER COULD NOT OPEN THE DOOR AND THEY START REMOVING THE DOOR LINER. ONCE REMOVED, THE	Y FOUND THAT THE SERVICE DOOR UP-LOCK MECHANISM HAD BROKEN COMPLETELY. BY LOOKING AT THE MATERIAL INSIDE THE CRACK IT WA	S NOTICED THERE WERE SIGNS OF DIRT ACCUMULATION IN DIFFERENT AREAS MEANING THAT A CRACK DEVELOPED FOR QUITE SOME TIME.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081106		EA  	2008	11	6	CA080623006      	1	20080620	G	3070	304310	HEAT TAPE       			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					WATER LINE	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE 96 MONTH INSPECTION ON ACFT BURNED HEAT TAPE PART NR 3043-10 AND 3043-15 WAS DISCOVERED. THIS TAPE WAS 	INSTALLED UNDER A DRAWING NR 34-260W011 ON THE AFT WATER SYSTEM LINES (AFT CABIN). THE SURROUNDING INSULATION AND AFFECT	ED PIPING WAS DEEPLY BURNED. THE BREAKER NEVER POPPED DURING THIS INCIDENT.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081106		EU  	2008	11	6	CA080623007      	1	20080623	G	3030		HEATER          	PILATS      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITOT TUBE	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			7257 								(CAN) ACFT RETURNED WHEN PITOT STATIC HEAT FAIL LIGHT CAME ON. FOUND RT PITOT TUBE NOT HEATING, REPLACED TUBE TESTED SYS	TEM AND PERFORMED LEAK TEST ACFT RETURNED TO SERVICE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081106		EU  	2008	11	6	CA080623008      	1	20080618	G	5311	5331412041	FRAME           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17784								(CAN) CORROSION WAS FOUND ON THE TOP SURFACE OF FUSELAGE FRAMES 21 AND 24 BETWEEN ALL 4 SEAT RAILS.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081106		EU  	2008	11	6	CA080623009      	1	20080621	G	5311	5331412041	FRAME           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14225								(CAN) CORROSION FOUND ON TOP SURFACE OF FUSELAGE FRAMES 21 AND 24 BETWEEN ALL 4 SEAT RAILS.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081106		SW  	2008	11	6	CA080623010      	1	20080622	G	3260		BULB            			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					MLG INDICATOR	INOPERATIVE     	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) DISPATCHED FROM CYLB TO CYMM AT 11:10. ON DOWNWIND RT FOR 07 CYMM SELECTED GEAR DOWN BUT DID NOT GET A GEAR DOWN L	IGHT FOR THE LT MAIN. GEAR APPEARED TO BE IN THE NORMAL DOWN POSITION, GEAR UNSAFE LIGHT WAS NOT ILLUMINATED, AND THE HY	DRAULIC PRESSURE WAS NORMAL. MX WAS PHONED TO DISCUSS THE ISSUE, AND CONCLUDED THAT IT WAS PROBABLY A DEFECTIVE LIGHT. C	YMM RADIO WAS CONTACTED TO HAVE EMERGENCY VEHICLES ALERTED. ACFT CIRCLED WEST OF CYMM UNTIL EMERGENCY VEHICLES ARRIVED A	ND THEN PROCEEDED TO LAND WITH NO FURTHER PROBLEMS. AFTER LANDING IT WAS DETERMINED THAT THE LT GEAR LIGHT BULB WAS BURN	ED OUT.  LT MAIN GEAR LIGHT BULB REPLACED.	1	H	7	2 	3T	4	T		2A4     	E2WE				 
	20081106			2008	11	6	CA080623011      	4	20080623	G	2562		G SWITCH        	DORNEMARGLN 																ELT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN PERFORMING THE ANNUAL TESTS REQUIRED BY CAR 571 APPENDIX G FOUND G SWITCH WOULD NOT ACTIVATE. ELT REPLACED WI	TH SERVICEABLE UNIT.																		 
	20081106			2008	11	6	CA080623012      	4	20080620	G	6122	4U1827	GOVERNOR        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	PROPELLER	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA				33   							(CAN) ON APPROACH TO TALBOT LAKE FOR A SCOOP (WATER PICK UP) THE RT ENGINE BEGAN TO SPEED UP UNCOMMANDED TO 3000 RPM AND	 AN OVERSHOOT WAS INITIATED. THE RPM LEVER WAS RETARDED IN AN ATTEMPT TO CONTROL THE RPM WITH NO RESPONSE. THE PROP OVER	SPEED PROCEDURE WAS FOLLOWED AND THE ENGINE RESPONDED TO THROTTLE REDUCTION BUT WOULD NOT FEATHER. THE ENGINE AND PROP R	EMAINED STABLE AND LANDING WAS UNEVENTFUL. THE PROP GOVERNOR WAS CHANGED AND THE ACFT WAS RETURNED TO SERVICE. DUE TO TH	E TSO AND TYPE OF FAILURE THIS GOVERNOR WILL BE SENT OUT FOR A TEAR DOWN REPORT. A FOLLOW UP REPORT WILL BE GENERATED UP	ON RECEIPT OF THE TEAR DOWN REPORT.	2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
	20081106		EA  	2008	11	6	CA080624001      	2	20080624	G	7230		COMPRESSOR      								PWA   	PT6   	PT6A21      	52043	EA  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) EIR PT6A 2008-040 OVER TEMPERATURE EVENT OCCURRED AS A RESULT OF COMPRESSOR FAILURE DUE TO LOSS OF STACK RIGIDITY,	 WHICH RESULTED FROM A LOSS OF STRETCH ON THE COMPRESSOR TIE RODS (P/N 3019371). COMPRESSOR SELF-DESTRUCTED. TIE RODS WE	RE INSTALLED "NEW" AT PRIOR OVERHAUL (TSO 465 HOURS).  TIE RODS WERE FOUND TO BE WITHIN ALLOWABLE HARDNESS RANGE.  ENGIN	E WAS PREVIOUSLY A PT6A-11 MODEL BUT CONVERTED TO A PT6A-21 VIA TCCA APPROVAL IN SEPT/04.								4	T			E4EA				 
	20081106		WP  	2008	11	6	CA080624002      	1	20080610	G	5345	D2010104	ARM             	DART        		ROBSIN	R44   	R44         	7640120	WP  										MIRROR	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DART HAS RECEIVED REPORTS FROM CUSTOMERS THAT UNDER CERTAIN CIRCUMSTANCES ON D044-715-011 AND D022-716-011 CARGO M	IRROR INSTALLATIONS AT CHG001 THE D2010-104 ARM MAY CRACK DURING FLIGHT CAUSING THE D2011-101 MIRROR TO SEPARATE FROM TH	E ASSEMBLY. DART SERVICE BULLETIN SB08-2 IS BEING ISSUED TO ALL CUSTOMERS WHO HAVE PURCHASED THESE ASSEMBLIES FROM DART.				1	G	7	1 	3O				H11NM   					 
	20081106		NM  	2008	11	6	CA080624003      	1	20080624	G	7933		INDICATOR       			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					OIL TEMP	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) ON TAKE-OFF/CLIMB OUT, THE NR 3 ENGINE EGT WAS 60 DEGREES HIGHER THAN ENGINES 1 AND 2. THROUGH 1000 FEET AGL THE N	R 3 OIL TEMP WENT INTO THE RED BAND. A REDUCTION IN POWER FOR QUITE THRUST BROUGHT THE OIL TEMP BACK TO THE YELLOW BAND.	 A RESUMPTION IN POWER RESULTED IN THE OIL TEMO RETURNING TO THE RED BAND. THE ENGINE WAS SHUT DOWN AND THE ACFT RETURNE	D FOR LANDING.  MX REPLACED THE OIL TEMP INDICATOR AND BULB WHICH RECTIFIED THE PROBLEM.			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081106		EU  	2008	11	6	CA080624004      	1	20080618	G	3397		WIRE            			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  					NAV LIGHT	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			125  								(CAN) THE GREEN NAV LIGHT POWER WIRE CHAFED INSIDE THE HORIZONTAL STABILIZER AND THE RESULTING SHORT CIRCUIT POPPED THE 	6 AMP CIRCUIT BREAKER BUT NOT BEFORE DAMAGING THE POS LIGHT SWITCH AND THE LIGHT & ANCILLARY CONTROL UNIT (LACU).					1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
	20081114		CE  	2008	11	14	CA080625001      	1	20080606	G	2910	6317003136	LINE            			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					HYDRAULIC SYS	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			2115 	2115 							(CAN) ACFT DEPARTED AND EXPERIENCED COMPLETE HYDR FLUID LOSS. ACFT GEAR ALTERNATE EXTENDED AND RETURNED TO AIRPORT. TROU	BLESHOOTING REVEALED RUPTURED HYDR PRESSURE LINE INBD OF SERVICE QUICK CONNECT. LINE REPLACED WITH NEW, AND SYS BLED. AC	FT RUN FOR 10 MIN AND ALL 3 SYS FILTERS REMOVED AND CHECKED FOR DEBRIS. NONE NOTED. FILTERS REPLACED WITH NEW IAW AMM 29	-10-00. AND SYS BLED. ALL SYS INCLUDING GEAR CYCLED 40 TIMES. ACFT RUN AND SYS CHECKED SERVICEABLE. RUPTURE APPEARED TO 	BE A MFG FLAW THAT WAS NOT NOTICEABLE DUE TO THE HYDR LINE IDENT LABEL BEING PLACED OVER THE FLAW.		1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
	20081114		SO  	2008	11	14	CA080625002      	1	20080429	G	2997		CONNECTOR       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	HYD POWERPACK	LOOSE           	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) HYDR FLUID NOTED LEAKING FROM MANUAL HYDR HAND PUMP UPON POST-TAKEOFF GEAR RETRACTION. ATTEMPT TO RE-EXTEND GEAR W	ITH STANDARD SYS OR MANUAL HAND PUMP FAILED. CO2 EMERGENCY DEPLOYED, GEAR EXTENSION UNSUCCESSFUL. S-PIN ON BACK OF PRIOR	ITY VALVE REMOVED BY OTHER CREW MEMBER ONBOARD (WITH GUIDANCE FROM AME ON GROUND VIA RADIO). PIN FOUND DIFFICULT TO REMO	VE, TOOLS AND CONSIDREABLE FORCE REQUIRED. GEAR IMMEDIATELY EXTENDED WITH NORMAL INDICATIONS ONCE PIN WAS REMOVED, SUCCE	SSFUL LANDING EXECUTED.		1	L	7	2 	3O	3	O		1A10    	E14EA	5	C	P9EA	 
	20081114		EU  	2008	11	14	CA080625003      	1	20080620	G	7500	7275031504	PIPE            			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F26 	NE  	HP BLEEDAIR	CRACKED         	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ON TAKE OFF ROLL WITH THE CTOT ENGAGED, THE NR1 ENGINE TEMP INCREASED TO 900 DEGREES AT A TORQUE OF 60 PERCENT. TH	E CREW REDUCED ENGINE POWER AND AT THIS TIME THEY DID HAVE A STEADY DECREASE IN ENGINE TEMP. THE ACFT RETURNED TO THE RA	MP AND MAINT WAS DISPATCHED TO INVESTIGATE THE PROBLEM. UPON OPENING THE ENGINE COWLS MAINT DISCOVERED THAT THE HP BLEED	 PIPE HAD CRACKED ALL THE WAY AROUND THE LOWER CLAMP CREATING A BLEED AIR LEAK. PIPE WAS REPLACED AND THE ACFT RELEASED 	BACK INTO SERVICE.		2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
	20081114		SW  	2008	11	14	CA080625004      	1	20080618	G	2910		LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	29073	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, CREW NOTED A DROP IN HYDR PRESSURE FOLLOWED BY THE ILLUMINATION OF THE HYDR WARNING LIGHTS. THE HYDR 	PRESSURE WENT TO ZERO AND CREW CREW CONSULTED TO APPROPRIATE CHECKED LIST AND COMPLETED A MANUAL EXTENSION OF THE LANDIN	G GEAR USING THE ALTERNATE EXTENSION PROCEDURES. THE ACFT LANDED WITHOUT INCIDENT. AN INSP BY MAINT DETERMINED THAT HYDR	 FLUID HAD BEEN LOST DUE TO A LEAK IN A HYDR TUBING IN THE LT GEAR WELL. LINE HAD A CRACK AT THE FLARE AND RESULTED IN T	HE LEAK. LINE WAS REPLACED WITH NEW, FUNCTION, OPERATION, AND LEAK CHECKS COMPLETED AND THE ACFT RETURNED TO SERVICE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081114		SW  	2008	11	14	CA080625005      	1	20080612	G	6210	206015001119	BLADE           			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					MAIN ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			753  								(CAN) DELAMINATION AT ROOT OF BLADE ON UPPER SURFACE OF THE GIP PLATE FINGER. VISUAL SEPARATION NOTED ON DAILY INSP.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081118		SO  	2008	11	18	CA080625006      	1	20080622	G	2823		SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	FUEL SELECTOR	IMPROPER PART   	W				D				RETURN TO BLOCK         				W	S		INADEQUATE Q C            	AFFECT SYSTEMS            		TX	TAXI/GRND HDL  	1			CA											(CAN) ON GROUND RUN UP, DURING NORMAL PROCEDURE, PILOT MOVED FUEL SELECTOR TO LT FROM RT AND TRY TO COME BACK TO RT. BUT	 HANDLE WAS SEIZED ON FUEL SELECTOR PANEL ATTACHING SCREWS. FOUND FUEL SELECTOR COVER SCREWS MAKING CONTACT WITH HANDLE 	AND PREVENTING MOVEMENT FROM LT TO RT POSITION. COVER REMOVED AND AREA INSPECTED AND NO DAMAGE FOUND. COVER INSTALLED WI	TH APPROPRIATE SCREWS AND FUNCTIONAL CHECK C/O. INSTALLATION C/O IAW MM. FUEL SELECTOR PANEL WAS REMOVED AND REINSTALLED	 FOR THE ELT SWITCH WIRING INSTALLATION.  GOOD FUNCTIONAL CHECK OF THE FUEL SELECTOR HAS NOT BEEN COMPLETED AFTER PANEL 	INSTALLATION. IT IS A GOOD THING PILOT DID A GOOD WALK AROUND AND FUEL SELECTOR CHECK.  SUGGEST TO MAKE A INDEPENDENT IN	1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
	20081118		CE  	2008	11	18	CA080625007      	1	20080624	G	5312	1014302851	BULKHEAD        			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9057 								(CAN) MAINT WAS CARRYING OUT THE FIRST 1000 CYCLE REPETITIVE INSP AFTER  INITIAL 10000 CYCLE STRUCTURAL INSP. FOUND A 4 	INCH CRACK IN THE FS 280.275 BULKHEAD WEB, ON THE LT SIDE AT THE STRINGER NR 4 CUTOUT.  THE BULKHEAD WAS CRACKED ALL THE	 WAY THROUGH. THICKNESS IS .040 INCH AT THIS AREA. THE CRACK ORIGINATED IN A POORLY DONE STRINGER CUTOUT.   THIS IS THE 	HIGH TIME IN OUR FLIGHT. IT ACCRUES APPROX 1.4 CYCLES/HOUR IN AIR AMBULANCE WORK.			2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
	20081118		EA  	2008	11	18	CA080625008      	1	20080612	G	2742	6009230167	ACTUATOR        			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF348E5A1   	30062	NE  					HORIZ STAB	MALFUNCTIONED   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			869  	869  							(CAN) DURING A FLIGHT, PILOT REPORTED A PITCH TRIM CHANNEL NR1 INOP LIGHT ON. TROUBLESHOOT THE TRIM SYS AND FOUND NR1 TR	IM ACTUATOR BRAKE COIL OPEN. HORIZ STAB TRIM ACTUATOR (P/N 600-92301-67/21207-008 S/N Y2003)  WAS REPLACED WITH A REPAIR	ED UNIT WITH TSN 868.8 HRS, CSN 613 CYCLES.  UNIT WAS FUNCTIONAL TESTED IAW AMM 27-40-00 TRIM SYS TEST AND PASSED TEST, 	RETURNED ACFT TO SERVICE.  DURING OUR NEXT FLIGHT ON 17 JUNE 08, FOR ABOUT 20 MINUTES THE ACTUATOR WORKED FINE. BUT AFTE	R THAT THE PILOT REPORTED CHANNEL NR1 AND NR2 INOP LIGHT ON. AFTER ATTEMPTING TO RESET THE TRIM SYS BY THE AFM RECOMMEND	ATION AND FAILED TO RESET, THE PILOT RETURNED TO BASED WITH THE  ACTUATOR TRIM FROZEN TO THE LAST SET FLIGHT POSITION. T	2	L	7	2 	4F	4	F	RT	A21AE   	E00063EN				 
	20081230		NE  	2008	12	30	CA080626001      	2	20080619	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			600  								(CAN) OIL LEAK NOTICED PRIOR TO ANNUAL INSP.  OIL WAS LEAKING OUT THE VENT LINE FROM THE FUEL PUMP.  REMOVED PUMP,  REMO	VED FUEL VENT FITTING, FOUND VENT CHAMBER FULL OF ENGINE OIL.  REPLACED WITH NEW PUMP.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		EA  	2008	11	18	CA080626002      	2	20080624	G	8520	982C9HE2	MAIN BEARING    								WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	NR 1 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA				460  							(CAN) ACFT WAS IN CRUISE FLIGHT WHEN PILOT NOTICED OIL TEMP ON NR1 ENGINE INCREASING. A PRECAUTIONARY SHUTDOWN WAS INITI	ATED ENGINE FEATHERED ACFT RETURNED AND LANDED WITH NO EVENT.  INVESTIGATION FOUND THE MAIN OIL SCREENS CONTAMINATED (SU	SPECT MAIN BRG FAILURE) ENGINE IS BEING REMOVED AND REPLACEMENT ENGINE INSTALLED ACFT WILL BE RETURNED TO SERVICE.									4	R			E259	6	C	P8879	 
	20081118		WP  	2008	11	18	CA080627001      	1	20080623	G	2435	14924HTH	HOUSING         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER-GEN	CRACKED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			24   								(CAN) STARTER WAS GRINDING ON STARTUP, UPON FURTHER INVESTIGATION AND REMOVAL OF THE STARTER IT WAS FOUND TO HAVE A CRAC	KED HSG.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		NE  	2008	11	18	CA080627002      	2	20080624	G	7200	LTS100750B	ENGINE          			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 2	FLAMED OUT      	W				O				OTHER                   				X			ENGINE FLAMEOUT           			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING NR2 ENGINE START UP PROCEDURE NR2 ENGINE FLAMED OUT. NR2 ENGINE WAS SET TO IDLE AND UPON TURNING ON NR2 GEN	ERATOR, ENGINE SPOOLED DOWN. THERE WERE NO SURGES WITH THE INSTRUMENTS. ACFT WAS SHUTDOWN AND INSPECTED. DURING INSP NO 	FAULTS WERE DETECTED. A FUEL SAMPLE WAS TAKEN AND SHOWED THAT IT WAS CLEAR AND FREE OF WATER. ALL FUEL SUPPLY LINES TO T	HE NR2 ENGINE WERE INSPECTED AND FOUND NO FAULTS. ALL AIR LINES WERE REMOVED AND VISUALLY INSPECTED AND CAPPED LEAK CHEC	KED AROUND THE FLARES AND NO FAULTS WERE DETECTED. AIR LINES WERE REINSTALLED AND NR2 ENGINE ASSY WAS LEAK CHECKED IAW M	M NO FAULTS DETECTED. THE NR2 ENG WAS GROUND RUNNED AND LEAK CHECKED NO FAULTS WERE FOUND. ACFT WAS RETURNED TO SERVICE 	1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
	20081118			2008	11	18	CA080627003      	1	20080625	G	2910	MS21926J4	FITTING         			GULSTM					GARRTT	TFE731	TFE73140    	29001	NE  					NLG	LOOSE           	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA			1175 								(CAN) ON DESCENT THE LT AND RT HYDR PUMP LIGHTS FLICKERED ON AND OFF. LOW HYD RESERVOIR ALSO ILLUMINATED. ALL SYS FUNCTI	ONED NORMAL AND AFTER  ACFT WAS STABILIZED ON APPROACH NO FURTHER LIGHTS WERE SEEN DURING OR AFTER LANDING. UPON A POST 	FLIGHT WALK AROUND HYDR FLUID WAS NOTED DOWN THE BELLY OF THE ACFT FROM NOSEWHEEL WELL BACK. RESERVOIR WAS FOUND LOW AND	 1.5 LITRES OF FLUID WAS ADDED. GROUND RUNS WERE CONDUCTED AND NO LEAK WAS SEEN. MAINT WAS DISPATCHED TO THE SCENE, AFTE	R JACKING IT WAS FOUND THAT B-NUT ON THE 90 DEGREE FITTING FOR THE DOWNLOCK ACTUATOR HAD BACKED OFF AND THE FITTING WAS 	FOUND LOOSE WITH THE O-RING AND BACK UP RING DISTORTED. A NEW BACK UP RING AND O-RING WERE INSTALLED , GEAR WAS SWUNG AN						4	F			E1NM				 
	20081118		EA  	2008	11	18	CA080628002      	1	20080622	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			2651 								(CAN)"THE FOS WINDSHIELD SHATTERED IN FLIGHT. THE OUTTER PANE IS BROKE".  REMOVED AND REPLACED THE WINDSHIELD.  WINDSHI	ELD, (RT) NP-139321-12 03017H4489  TSO: 2651.2/CSO: 2069.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081119		NE  	2008	11	19	CA080630001      	2	20080522	G	7200		ENGINE          			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					NR 2	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) - ON DESCENT, A "BUZZING" SOUND WAS HEARD IN THE FLIGHT DECK FOR APPROX 5-10 SEC. THIS WAS FOLLOWED BY 1 OR 2 "POP	S" AND THEN A LOUD "BANG" AT WHICH TIME THE NR 2 ENGINE LOST THRUST.  NR 2 ENG TEMP CLIMBED BUT THERE WAS NO ENG OVERHEA	T OR FIRE WARNING. ATC ADVISED OF EMERGENCY, AFTER LANDING, THE ACFT WAS BROUGHT TO A FULL STOP IN THE MIDDLE OF THE RUN	WAY AND THE ENGINE WAS SHUT DOWN.  C.F.R. APPROACHED THE ACFT AND NOTICED "SMOKE" AND A "GLOW" FROM THE NR 2 ENGINE. THE	RMAL IMAGING OF THE ACFT WAS ALSO PERFORMED. THEY APPLIED FOAM TO THE NR 2 ENGINE AT THIS TIME.  CREW OPTED FOR A RAPID 	DEPLANEMENT THROUGH THE FORWARD L1 EXIT.  NO VISIBLE DAMAGE TO THE ENGINE. IT WAS NOTED UPON FURTHER INVESTIGATION THAT 	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
	20081118		CE  	2008	11	18	CA080630002      	1	20080623	G	2701	07118505	CONTROL COLUMN  			CESSNA	185   	A185F       	2072821	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	D3A34	D3A34C401   	GL  		CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1692 								(CAN) WHILE CARRYING OUT AN ANNUAL INSP AND SEB 01-3 R1 HEAVY CORROSION WAS FOUND INTERNALLY IN CONTROL YOKE.  A/C HISTO	RY SHOWED FRESH WATER SUBMERSION IN 1982.					1	H	7	1 	3O	3	O		3A24    	1E4	5	C	P47GL	 
	20081118		SO  	2008	11	18	CA080630003      	1	20080425	G	8011	149NLR	STARTER         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			61   								(CAN) AFTER SITTING FOR 4 MONTHS, THE PILOT TRIED TO START THE ENGINE AND AFTER ONE REVOLUTION THE STARTER QUIT. THE STA	RTER WAS REMOVED AND REPLACED. THE ARMATURE END OF THE STARTER HSG WAS BROKEN OUT AND TWISTED, INDICATING THAT SOMETHING	 WAS BINDING IN THE ARMATURE AREA. STARTER SENT TO MFG FOR TEAR DOWN AND FOLLOW UP.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081118		WP  	2008	11	18	CA080630004      	1	20080627	G	8010	A1294BBT	SWITCH          			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	COCKPIT	SHORTED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 1 ENG STARTED TO ROTATE WHEN START ARM SWITCH SELECTED TO START POSITION, WHILE NR 1 START BUTTON NOT ENGAGED A	ND ATTEMPTING TO START NR2 ENG.  NR 1 ENGINE START SWITCH FOUND SHORTING INTERMITTENTLY INTERNALLY WHEN START BUTTON IS 	ROCKED SIDE TO SIDE.				2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
	20081107		EA  	2008	11	7	CA080630005      	1	20080629	G	3230	555406	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					NLG	UNSERVICEABLE   	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			22326	8866 							(CAN) GEAR DISAGREE MSG ON GEAR DOWN SELECTION, MAINS INDICATING GREEN AND THE NOSE INDICATING WHITE. CREW CYCLED GEAR W	ITH SAME RESULT. THEY THEN DID AN ALTERNATE EXTENSION AND GOT THE 3 GREEN INDICATION AND LANDED WITH NO PROBLEM. (LANDIN	G GEAR RETRACTION SYSTEM) MX T/S REVEALED THE NLG DOOR SELECTOR VALVE TO BE AT FAULT. THE SELECTOR VALVE WAS REPLACED AN	D GEAR SWINGS WERE C/O AND THE ACFT WAS CHECKED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081110		EA  	2008	11	10	CA080701003      	1	20080630	G	5751		SKIN            	BOMBDR      		DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					AILERON	DAMAGED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DEPARTING AND DURING CLIMB OUT THE ACFT WAS STRUCK BY LIGHTNING CAUSING DAMAGE TO LT AILERON TIP. DECISION WAS MAD	E TO RETURN THE ACFT TO AIRPORT FOR INSPECTION. INSPECTION COMPLETED PER AMM 05-50-31 AND DAMAGE WAS FOUND AT THE LT AIL	ERON TIP AND ALL STATIC DISCHARGES. AILERON TIP REPLACED, AILERON BALANCE CHECKED AS PER AMM 57-60-71, ALL STATIC WICKS 	REPLACED AND CHECKED SERVICEABLE. ACFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20081110		CE  	2008	11	10	CA080701004      	1	20080627	G	5210	5043003211	HOOK            	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					PAX DOOR	OUT OF ADJUST   	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ACFT DEPRESSURIZED AT 20000 FEET. ACFT DESCENDED TO 10000 FEET AND LANDED WITHOUT INCIDENT MX FOUND THE UPPER FORW	ARD DOOR HOOK WAS NOT LATCHING PROPERLY THAT CAUSED THE DOOR SEAL TO BLOW OUT CAUSING THE DECOMPRESSION. DOOR HOOK ADJUS	TED AND THE DOOR SEAL WAS SECURED.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
	20081110		EA  	2008	11	10	CA080702001      	1	20080629	G	5610	NP1393226	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE FIRST OFFICERS SIDE WINDOW INNER PANE IS CRACKED. FERRIED THE PLANE.  SLC REPLACED THE FIRST OFFICERS SIDE WIN	DOW. OPS CHECKS GOOD.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081110			2008	11	10	CA080702003      	4	20080701	G	2297	4986	FUSE            	STEC        	012980201   	PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					A/P COMPUTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			500  	500  							(CAN) MANUAL ELECTRIC & AUTO TRIM UNSERVICEABLE - REPLACED FUSE F2 IN ACCORDANCE WITH S-TEC SERVICE BULLETIN SB08-004.						1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
	20081110		NE  	2008	11	10	CA080702004      	2	20080602	G	7250		TURBINE BLADES  			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) DURING T/O A LOUD NOISE WAS HEARD FROM THE ENGINE AND THE T/O WAS REJECTED. THE ACFT WAS STOPPED ON THE RUNWAY AND	 BOTH ENGINES WERE SHUT DOWN. INSPECTION REVEALED TURBINE BLADE DAMAGE, THE ENGINE WILL BE REMOVED AND FORWARDED TO P&WC	 FOR INVESTIGATION AND REPAIR. THE ENGINE IS A P&WC RENTAL.   P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF R	OOT CAUSE ONCE ESTABLISHED.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
	20081118		NE  	2008	11	18	CA080702005      	2	20080626	G	7250		TURBINE         			BELL  	205   	205B        	       	SW  	LYC   	T53   	T5313B      	41549	NE  					ENGINE	DAMAGED         	W				R				AUTOROTATION            				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			CA											(CAN) PILOT CONDUCTED TAKE-OFF SCHEDULED TO CONDUCT LONGLINE OPERATIONS. APPROX 2 MINS AFTER TAKE-OFF THE PILOT HEARD A 	LOUD BANG FOLLOWED BY TORQUE YAWING. THE PILOT ENTERED AN AUTOROTATION AND LANDED THE ACFT ON A LOGGING ROAD. THE ACFT S	USTAINED MINOR DAMAGE DUE TO HARD LANDING. SUBSEQUENT INVESTIGATION REVEALED APPROX 3 INCHES EXIT HOLE IN THE COMBUSTOR 	ASSY FROM TURBINE BLADE/DISC FAILURE. INSPECTION OF THE LT ACFT COWLING REVEALED APPROX 2 FT OF ENGINE INTERNAL PART SCA	TTER DAMAGE. INSPECTION OF THE TAILPIPE AREA REVEALED EXTENSIVE DAMAGE TO ALL WHEEL AND DISC ASSEMBLIES.  ACFT INSPECTED	 AS UN-AIRWORTHY.	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081118		NE  	2008	11	18	CA080702006      	2	20080612	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				Z	J		SIGNIFICANT FAILURE REPORT	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE PILOT REPORTED WHILE AT 3000FT AGL, 2-3 MINUTES AFTER TAKEOFF, HE HEARD A LOUD BANG AND OBSERVED THE PROP TORQ	UE HAD DROPPED TO ZERO. THE PILOT LANDED THE ACFT SAFELY. THE ENGINE WILL BE FORWARDED FOR INVESTIGATION. MFG WILL HAVE 	A REPRESENTATIVE ON SITE AND REPORT FINDINGS AS AVAILABLE.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081118		CE  	2008	11	18	CA080702007      	1	20080624	G	2720	0510105207	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5099 								(CAN) BOTH RUDDER CABLES WERE FOUND WORN AT STA 142 WHERE THEY TRAVEL OVER PULLEYS WITH MINIMAL CONTACT ANGLE.  BECAUSE 	THERE IS LITTLE PRESSURE AGAINST THE PULLEYS AT THIS POINT, THEY VIBRATE AND CHAFE AGAINST THE PULLEYS, CAUSING WEAR OF 	THE STRANDS. AFTER REMOVAL OF THE CABLES, THE STRANDS BROKE EASILY WHEN THE CABLE WAS BENT SHARPLY.  THESE ARE GALVANIZE	D STEEL CABLES.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081118		NE  	2008	11	18	CA080702008      	2	20080308	G	7200		BEARING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						DISTRESSED      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) WHILE AT CRUISE AT FL70, THE ENGINE TORQUE DROPPED BELOW 600FT-LB WITH ASSOCIATED COCKPIT WARNING LIGHT. THE FLIGH	T WAS DIVERTED FROM ITS INTENDED DESTINATION AND AN UNEVENTFUL LANDING WAS MADE. THE ENGINE WAS FWD WHERE DISASSEMBLY SH	OWED A DISTRESSED NR 1 BEARING. THE BEARING WAS FWDED TO MFG FOR INVESTIGATION. THE EXTENT OF DAMAGE TO THE BEARING PREV	ENTED ASSESSMENT OF THE ROOT CAUSE FOR ITS DISTRESS.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081118		EA  	2008	11	18	CA080702009      	2	20080422	G	7314		DRIVE SHAFT     			EMB   	110   	EMB110*     	       	SO  	PWA   	PT6   	PT6A34      	52043	EA  					FUEL PUMP	DISTRESSED      	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CA											(CAN) ACCORDING TO REPORTS, CREW DECLARED AN EMERGENCY DUE TO ENGINE DISTRESS. DURING SUBSEQUENT LANDING, A/C EXITED THE	 RUNWAY BEFORE HITTING A DITCH. THE LANDING GEAR COLLAPSED AND THE NOSE OF THE A/C WAS SEVERELY DAMAGED. THE RUNWAY EXCU	RSION WAS CAUSED BY A LOSS OF DIRECTIONAL CONTROL DURING LANDING.   DISASSEMBLY (BY THE OPERATOR) OF THE ENGINE ON WHICH	 THE LOSS OF POWER OCCURRED, SHOWED FUEL PUMP DRIVE SHAFT SPLINE DISTRESS (DE-COUPLE). A LARGE AMOUNT OF CORROSION WAS P	RESENT AROUND THE AREA.		1	L	7	2 	4T	4	T	RT	A21SO   	E4EA				 
	20081118			2008	11	18	CA080702010      	4	20080630	G	3197	EC130B4	WIRE            			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  					WARNING SYSTEM	MISREPAIRED     	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			1998 	1998 							(CAN) THIS SNAG APPEARED AS AN INTERMITTENT WARNING (GONG) IN THE PILOTS HEADSET. THIS GONG ALERTS THE PILOT TO ANY OF T	HE RED WARNING LIGHTS ILLUMINATING ON THE CAUTION LIGHT WARNING PANEL. THE GONG WAS PRESENT BUT VERY LOW AND MAY NOT HAV	E BEEN HEARD BY THE PILOT IN CASE OF A RED WARNING INDICATION. WIRE SPLICE TO THE ASU CARD NR1 WAS FOUND TO HAVE AN INTE	RMITTENT CONNECTION. WIRE WAS REPAIRED AND GONG WARNING WAS RETURNED TO THE PROPER LEVEL.			1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
	20081118		EU  	2008	11	18	CA080702011      	1	20080627	G	2121	EVAC2423H	COOLING FAN     			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	NR 2	FAILED          	W				O				OTHER                   				J	B		WARNING INDICATION        	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING FOR DEPARTURE (FAB 820) THE CREW OBSERVED A NR2 PACK VALVE FAULT. THE FAULT RECURRED AFTER RESET ACC	OMPANIED BY AN AFT SMOKE INDICATION. THE F/A CONFIRMED THE PRESENCE OF SMOKE/HAZE IN THE AFT LAV. WHILE CONDUCTING THE C	HECK LIST THE SMOKE INDICATION EXTINGUISHED BUT THE ASSOCIATED ODOR REMAINED EVIDENT.  MAINT REPLACED THE NR2 GROUND COO	LING FAN AND THE ACFT WAS RETURNED TO SERVICE. THE SMELL AND HAZE WAS ATTRIBUTED TO THE DUCT OVERHEAT CONDITION RESULTAN	T FROM THE FAN FAILURE.		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20081118		EU  	2008	11	18	CA080702012      	1	20080702	G	6720	ASSB3510127	TUBE            		10543079    	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSP OF THE TAIL ROTOR CONTROL TUBE IAW CAMPAIGN NOTICE 351-67-10-017, A 7X7MM AREA WAS FOUND TO HAVE BEEN CHAFED 	TO A DEPTH OF .003 INCHES 15MM FWD OF THE PROTECTIVE SLEEVE INSTALLED ON THE CONTROL ROD IN THE 10 O`CLOCK POSITION LOOK	ING FWD FROM THE AFT OF THE ACFT. CHAFED AREA TO BE CLEANED UP AND ALODINE APPLIED, AND ON REINSTALLATION OF THE PROTECT	IVE BOOT ENSURE NO CONTACT WITH THE CONTROL ROD IS PRESENT.			1	G	7	2 	3U	3	U		H3EU    	E4CE				 
	20081118			2008	11	18	CA080702013      	4	20080630	G	6122		VALVE           			CVAC  					ALLSN 	501D  	501D13H     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	PITCH LOCK VALVE	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) NR 2 PROPELLER WOULD NOT GO INTO BETA OR REVERSE ON LANDING. PROPELLER GOVERNOR AND PITCH LOCK VALVE REPLACED AND 	PROP FUNCTION CHECKED SERVICEABLE ON GROUND RUN.										4	T			E282	6	C	P898	 
	20081118		EA  	2008	11	18	CA080703001      	2	20080702	G	7414	M3975	COIL            	SLICK       	4370        	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	MAGNETO	WORN            	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			1286 								(CAN) SB 3-08 DEALS WITH THE PROBLEM OF COIL HIGH-VOLTAGE OUTPUT TABS BEING BENT SLIGHTLY DURING MAGNETO MFG. THE DISTRI	BUTOR ROTOR HAS A SPRING-LOADED CARBON BRUSH THAT RIDES ON THIS TAB, AND IF THE TAB IS NOT PERPENDICULAR TO THE ROTOR SH	AFT, L THE BRUSH IS THRUST SIDEWAYS IN THE ROTOR SHAFT BORE, WEARING THE SIDES OF THE BRUSH AND CUTTING A HALF-MOON DEPR	ESSION IN THE COIL TAB.  THIS TAB WAS SLIGHTLY OFF-LEVEL AND WAS WORN AS DESCRIBED. THE BRUSH WAS ALSO SOMEWHAT WORN ON 	ITS SIDES.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081105		CE  	2008	11	5	CA080703002      	1	20080703	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			12861								(CAN) A HALF-INCH CRACK WAS NOTED RADIATING FROM THE FLANGE BEND RELIEF CUTOUT NEAR THE BOTTOM OF THE LT SIDE OF THE BUL	KHEAD AT STATION 108 (IMMEDIATELY INSIDE THE BAGGAGE DOOR), JUST ABOVE FLOOR LEVEL.  THIS AREA IS NORMALLY COVERED BY PL	ASTIC INTERIOR PANELS. IT WAS DISCOVERED DURING A 200-HOUR INSPECTION, WHICH REQUIRES REMOVAL OF INTERIOR PANELS AND UPH	OLSTERY.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081105		EU  	2008	11	5	CA080703004      	1	20080702	G	2720		CLEVIS PIN      			STBROS	SC7   	SC72        	8100510	EU  										RUDDER CONTROL	DETACHED        	W				A				UNSCHED LANDING         				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		CL	CLIMB          	1			CA											(CAN) ACFT DEPARTED, APPROXIMATELY 30 MILES EN ROUTE,  PLAY WAS NOTICED IN THE RT RUDDER PEDAL, THERE WAS NO RESISTANCE 	WHEN DEPRESSED AND WAS INOPERABLE, LT RUDDER WAS STILL FUNCTIONAL.  DECISION WAS MADE TO CONTINUE, ACFT LANDED WITHOUT I	NCIDENT. AFTER FURTHER INSPECTION OF RUDDER CONTROL SYSTEM, A CLEVIS PIN HAD BECOME DETACHED FROM RUDDER CONTROL TORQUE 	TUBE ABOVE REAR CARGO DOOR. IT APPEARS THE SAFTY CLIP THAT COVERS THE PIN AT BOTH ENDS IS MISSING.			1	H	7	2 	3T				A15EU   					 
	20081105		EA  	2008	11	5	CA080704002      	1	20080702	G	5753		ROD             			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					TE FLAPS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA		CFTFX	173  	173  							(CAN) DURING AN INSPECTION ON ACFT, IT WAS DISCOVERED THAT THE LT INBD CHORD-WISE FLAP ROD WAS RUBBING AGAINST THE SPAN-	WISE ROD. ONCE THEY WERE REMOVED FROM THE ACFT, IT WAS NOTED THAT THE SPAN-WISE ROD HAD A GROOVE WORN IN IT FROM THE OTH	ER ROD. A NEW SPAN-WISE ROD WAS INSTALLED. DURING INSTALLATION IT WAS NOTED THAT THE BELL CRANK SUPPORT STRUCTURE WAS PO	SSIBLY NOT SITUATED CORRECTLY LEADING TO A LACK OF CLEARANCE BETWEEN THE 2 RODS. THESE ARE RE-LIFED WINGS PURCHASED FROM	 R.W. MARTIN AND INSTALLED BY ROCKY MOUNTAIN ACFT. THE EXACT CAUSE HAS NOT BEEN DETERMINED YET AND AN UPDATE WILL BE PRO	VIDED WHEN THIS IS DETERMINED.	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
	20081105			2008	11	5	CA080704003      	4	20080703	G	2397	3042865102	ELECTRICAL BOX  			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					ROW 8 DEF	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) LIVE TV SCREENS ON SEATS DEF IN ROW 8 NOT DISPLAYING ANY PICTURE (BUT POWER STILL DELIVERED) AND BURNING ELECTRIC/	METAL STRONG ODOR OCCURRING IN VICINITY OF ROW 8. LIVETV SYSTEM TURNED OFF WITH FLIGHT ATTENDANT CONTROL PANEL AND ODOR 	DISSIPATED WITHIN 10-15 MINUTES. THE IFE SYSTEM WAS DEACTIVATED. MX PLACED THE IFE SYSTEM UNDER MEL. SEB AT ROW 8 RT WAS	 REPLACED, WIRES AND CONNECTORS INSPECTED AND SYSTEM TESTED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
	20081105			2008	11	5	CA080704004      	1	20080704	G	3246		BEARING         																	MLG WHEEL	LACK OF LUBE    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) EXCESSIVE WHEEL BEARING NOISE WAS NOTED FROM LANDING GEAR DURING TAXIING. INVESTIGATION REVEALED THAT WHEEL BEARIN	G GREASE HAD WASHED OUT OF THE BEARING AND ONTO THE WHEEL HALF.  WATER HAD PERMEATED THE GREASE AND CAUSED EXCESSIVE COR	ROSION TO THE BEARING AND CUP. U/S PARTS WERE REPLACED. THIS IS THE SECOND OCCURRENCE OF THIS PROBLEM. WE DID NOT REPORT	 THE FIRST 1 AS WE THOUGHT IT WAS AN ISOLATED CASE. HOWEVER, IT APPEARS IT IS NOT.																 
	20081105		NM  	2008	11	5	CA080707002      	1	20080705	G	2751		INDICATOR       			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					FLAP SYSTEM	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF WHEN RETRACTING FLAPS THE INBD FLAPS STUCK AT APPROXIMATELY 5 DEGREES WITH AN ASYMMETRY. THE ACFT D	ECLARED AN EMERGENCY WITH A FLAP PROBLEM AND RETURNED TO CYYC. THE ACFT LANDED WITHOUT FURTHER INCIDENT. TROUBLESHOOTING	 WAS CARRIED OUT AND THE LT INBD FLAP POSITION TRANSMITTER DRUM CABLE WAS FOUND TANGLED AND HAD NO TENSION. THE DRUM ASS	EMBLY WAS FOUND TO BE AT FAULT, AND THE TRANSMITTER ASSEMBLY SPRING TENSION HAD FAILED. THE FLAP POSITION TRANSMITTER AS	SEMBLY WAS REPLACED AND THE FLAP ADJUSTMENT/TEST PROCEDURES WERE CARRIED OUT WITH NO FURTHER FAULTS. THE ACFT WAS RETURN	ED TO SERVICE.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081105		GL  	2008	11	5	CA080707003      	2	20080706	G	7321	23065104	BEARING         	HONEYWELL   		BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FCU DRIVESHAFT	FAILED          	W				B				EMER. DESCENT           				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA				1141 							(CAN) PILOT NOTED N1 INCREASE DURING CRUISE.  REDUCED THROTTLE AND N1 DECREASED ACCORDINGLY.  SOME THROTTLE CONTROL WAS 	POSSIBLE BUT THE ENGINE CONTINUED TO ACCELERATE.  THROTTLE WAS REDUCED UNTIL IDLE STOP WAS REACHED AT WHICH TIME IT CONT	INUED TO CLIMB.  AT APPROX 15 FT AGL THE ENGINE WAS SHUT DOWN AND A SUCCESSFUL AUTO ROTATION WAS CARRIED OUT.  NO DAMAGE	 TO THE ACFT.  MX REMOVED FCU IN THE FIELD.  UPON REMOVAL IT WAS NOTED FCU DRIVESHAFT BEARING FAILED.  ALLOWS AXIAL AND 	RADIAL PLAY APPROX 1/2" BOTH WAYS.  BALL BEARINGS COMPLETELY DISLODGED.  LUBE FOUND INTACTED (NO WASHOUT) AND NO CORROSI	ON NOTED.  REPLACEMENT FCU INSTALLED AND ACFT WAS RUN UP.  ACFT DEPARTED BACK TO BASE WITH NO FURTHER ISSUES.	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081105		CE  	2008	11	5	CA080707004      	1	20080526	G	5610	99144111	WINDSHIELD      			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			1114 	1114 							(CAN) ON DESCENT FOR LANDING THE PILOT NOTED A LT WINDSHIELD INOP ICAS MSG AND SHORTLY AFTER THE PILOTS WINDSHIELD OUTER	 PANE SHATTERED. THE ACFT LANDED WITHOUT FURTHER PROBLEMS AND THE ACFT WAS FLOWN TO A SERVICE CENTER WHERE THE WINDSHIEL	D WAS REPLACED.				2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
	20081113		CE  	2008	11	13	CA080707005      	1	20080407	G	3220	12436351	TORQUE LINK     			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRING INP ON UPPER TORQUE LINK IAW CONTINUED AIRWORTHINESS PROGRAM 32-50-02 THE TORQUE LINK WAS FOUND CRAC	KED. A NEW LINK WAS INSTALLED WITH NEW BOLTS.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
	20081113		SW  	2008	11	13	CA080707006      	1	20080616	G	6510	407040416103	SHAFT           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6360 	6360 							(CAN) WHILE REMOVING THE TAIL ROTOR FROM THE ACFT, THE ENGINEER PERFORMING THE WORK NOTED THAT SEPARATING THE HUB FROM T	HE OUTPUT DRIVE SHAFT WAS SUBSTATIALLY MORE DIFFICULT THAN NORMAL. ONCE THE TAIL ROTOR WAS REMOVED IT WAS NOTED THAT THE	 INCORRECT TYPE OF LUBRICANT HAD BEEN APPLIED DURING THE LAST INSTALLATION OF THE TAIL ROTOR. THE TR GEARBOX WAS SENT TO	 A REPAIR FACILITY FOR A SCHEDULED INSP AND THE TR OUTPUT SHAFT WAS SUBSIQUENTLY SCRAPPED DUE TO CORROSION OF THE TR AND	 TAIL ROTOR OUTPUT SHAFT DRIVE SPLINES.		1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20081113		CE  	2008	11	13	CA080707007      	1	20080422	G	2730		BEARING         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	CONTROL TUBE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16227								(CAN) WHILE INSP IT WAS NOTICE THAT THE LT CONTROL TUBE WAS ROUGH AS IT WAS PULLED OUT AND PUSHED IN. AFTER TAKING IT OF	F, IT WAS NOTICED THAT THE BEARINGS HAD WORN THE TUBE TO ITS LIMITS. THE CONTROL TUBE AND THE BEARINGS WERE CHANGED.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
	20081113			2008	11	13	CA080707008      	4	20080407	G	6113	TCB43940008	SPINNER         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT PROP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING AN INSP, PROP SPINNER WAS FOUND CRACKED. THE CRACK STARTED FROM THE THE SCREW HOLES. A NEW SPINNER WAS	 INSTALLED AND THE PROP WAS BALANCED.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081113		NE  	2008	11	13	CA080707009      	2	20080703	G	7230	0292208260	DIFFUSER        			AEROSP	AS355 	AS355*      	       	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINT FOR REPLACEMENT OF THE T2 BLADES AND WHEEL, AFTER REMOVING OUTER CASING OF THE M03 THE OUTSIDE SURFAC	E OF THE DIFFUSER WAS FOUND CRACKED FROM ONE SIDE TO THE OTHER.  A SERVICEABLE M03 WAS INSTALLED AND THE HELICOPTER WAS 	RETURN TO SERVICE. DAMAGED M03 WAS SENT TO MFG FOR INVESTIGATION. THE M03 HAD 1479.3 HRS TSO.				1	G	7	2 	3U	3	U		H11EU   	E19EU				 
	20081113		SO  	2008	11	13	CA080707010      	1	20080516	G	2750		WORM GEAR       	CALCO       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FLAP XMSN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSP, IT WAS NOTICED THAT BOTH FLAP TRANSMISSION WERE WORN OUT OF LIMITS. OVERHAULED FLAP TRANMISSIONS WERE 	INSTALLED. THEY WERE BOTH WITHIN LIMITS AT THE LAST INSP. ONCE THEY START TO WEAR THEY REALLY WEAR FAST.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081113		CE  	2008	11	13	CA080707011      	1	20080528	G	3020		BUSHING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ICE VANE LINK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT THE INSP IT WAS NOTICED THAT THE ICE VANE BUSHINGS WERE WORN CAUSING THE VANE TO MOVE ENOUGH TO ALLOW THE ICE V	ANE LIGHT TO COME ON.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
	20081113		EU  	2008	11	13	CA080707012      	1	20080629	G	5302		SKIN            			AEROSP	AS355 	AS355*      	       	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					TAILBOOM	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE HELICOPTER EXPERIENCED A HARD LANDING AFTER BEING PUSHED SIDEWAYS BY A GUST OF WIND. THE RT SKID CAUGHT THE GR	OUND FIRST AND THE HELICOPTER STARTED TO YAW SEVERLY, PILOT DROPPED COLLECTIVE AND LANDED THE HELICOPTER IMMEDIATELY. TH	E TAILBOOM SUSTAINED DAMAGE CAUSED BY THE SUDDEN YAW, SERVICEABLE TAILBOOM AND HARD LANDING INSP C/W IAW MM AND RETURNED	 TO SERVICE.			1	G	7	2 	3U	3	U		H11EU   	E19EU				 
	20081113		NE  	2008	11	13	CA080707013      	2	20080627	G	7210	310830601	SLEEVE          								PWA   	PT6   	PT6A67D     	 	NE  					NR 5 BRG JOURNAL	DISLODGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17526	7040 							(CAN) THE ASSEMBLY HAD ACCUMULATED IN EXCESS OF 7000 HOURS SINCE THE SLEEVE WAS INSTALLED ON THE NR 5 BEARING JOURNAL, A	ND THE POWER SECTION WAS BEING RETURNED TO THE SHOP FOR A SCHEDULED OVERHAUL.   DURING INSPECTION OF THE 2ND STAGE REDUC	TION CARRIER IAW OHM 3038337, SEC.72-10-00 INSPECTION, PARA.6AM IT WAS FOUND THAT THE NR 5 BEARING JOURNAL SLEEVE HAD MO	VED AWAY FROM THE CARRIER SHOULDER BY APPROXIMATELY 0.021. NO OTHER DEFECTS WERE NOTED ON THE SLEEVE.								4	T			E26NE				 
	20081113		SO  	2008	11	13	CA080707014      	1	20080606	G	3230	42042000	ARM             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT MLG RETRACT	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING TAKEOFF, COULDN`T GET GEAR UP, LT GREEN LIGHT STAYS ON. UPON INSP AFTER LANDING, LT RETRACTION ARM WAS FOUN	D BROKEN. CRACK WAS ORIGINATED FROM ONE OF THE BOLT HOLES. NEW PART WAS ORDERED.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20081113		SW  	2008	11	13	CA080708001      	1	20080622	G	2820	S0310015HT	O-RING          	GULSTM      		GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	COUPLING	WORN            	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) AFTER LANDING AND DURING WALK AROUND FLIGHT CREW FOUND FUEL LEAKING FROM RT WING OTBD OF NACELLE. FURTHER INSP BY 	MAINT FOUND FUEL LEAKING FROM FUEL INTERCONNECT PIPE COUPLING ASSY. NEW O-RINGS INSTALLED, LEAK CHECKS CARRIED OUT AND A	CFT RETURNED TO SERVICE.				1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
	20081113		EA  	2008	11	13	CA080708002      	1	20080706	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					RT TE FLAP	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ACFT WAS SET UP IN LANDING CONFIGURATION WITH FLAPS AT 45 DEGREES. ON SHORT FINAL, CREW RECEIVED A FLAP FAILURE IN	DICATION. FLIGHT DID LAND NORMALLY.  HOWEVER, WERE UNABLE TO RETRACT FLAPS ONCE ON THE GROUND.   RT BPSU SHOWN TO BE AT 	FAULT. BPSU REPLACED AND COMPLETE SYS RIG CARRIED OUT. FUNCTION CHECKED SERVICEABLE WITH NO FURTHER FAULTS FOUND.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081113		CE  	2008	11	13	CA080708004      	1	20080626	G	3230	PDLM60	CIRCUIT BREAKER 	BEECH       		BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	LANDING GEAR	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ACFT DEPARTED, OR AFTER SCHEDULED MAINT WAS COMPLETED. IN THE CLIMB OUT IT WAS NOTICED BY THE CREW THAT THE LANDIN	G GEAR FAILED TO RETRACT. THE ACFT LANDED WITHOUT INCIDENT. UPON INSP IT WAS FOUND THAT THE CIRCUIT BREAKER HAD FAILED B	UT HAD NOT ACTUALLY POPPED. THE BREAKER WAS BENCH TEST AND CONTINUED TO NOT ALLOW POWER THOUGH DESPITE BEING PROPERLY DE	PRESSED. THE BREAKER WAS REPLACED WITH A NEW ONE AND THE SYS FUNCTION TESTED NORMAL.			1	L	7	2 	3T	4	T		A14CE   	E2WE	6	C	P40EA	 
	20081113		CE  	2008	11	13	CA080708005      	1	20080708	G	2731	55657562	WHEEL           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR TRIM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN A SMALL FORCE WAS APPLIED TO THE INDICATOR POINTER AND THE TRIM WHEEL WAS ROTATED THE POINTER JUMPED OUT OF I	TS GROOVE. INSPECTION FOUND THAT THE GROOVES WERE NOT WORN AND THE SYSTEM LOOKED NORMAL BUT WHEN THE WHEEL WAS ROTATED W	ITH 1 FINGER APPLYING PRESSURE TO THE SIDE OF THE WHEEL IT WOBBLED AND ALLOWED THE PIN RIDING IN THE GROOVE TO BECOME DI	SENGAGED. PINCHING THE WHEEL WITH A THUMB AND FINGER OR TURNING THE WHEEL WITH THE PALM OF THE HAND ON THE TOP DID NOT A	LLOW THE PIN TO DISENGAGE.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081113		NE  	2008	11	13	CA080708006      	2	20080621	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYS	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			98   								(CAN) DURING A GROUND RUN OF THE ACFT THE ENGINE FUEL PUMP WAS LEAKING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081113		WP  	2008	11	13	CA080708007      	1	20080630	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			344  								(CAN) STARTER BENDIX IS NOT FUNCTIONING/STARTER WOULD NOT ENGAGE THE RING GEAR.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081113		WP  	2008	11	13	CA080708008      	1	20080629	G	6310	C0511	ACTUATOR        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CLUTCH	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE CLUTCH ACTUATOR LOWER MOTOR HSG FLANGE TO WORM GEAR FOUND LOOSE.						1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081113		SO  	2008	11	13	CA080708009      	1	20080620	G	8011		STARTER         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				641  							(CAN) THE STARTER WOULD NOT ENGAGE, REPLACED WITH A SERVICABLE STARTER.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081113			2008	11	13	CA080708010      	4	20080708	G	3452		TRANSPONDER     			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ATC	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MODE C ALTITUDE REPORTING INTERMITTENTLY REPORTS FALSE ALTITUDES. VISUAL INSP FOUND A CHAFED MODE C A1 CODE WIRE I	N THE ALTITUDE ENCODER WIRING. WIRE WAS CHAFFING (DUE TO VIBRATION) ON THE THROTTLE CABLE DIRECTLY BEHIND THE CENTER RAD	IO PANEL. WIRE WAS REPAIRED AND CHAFE PROTECTION WAS ADDED TO THE WIRE HARNESS. MODE C DATA INTEGRATION CHECK WAS PERFOR	MED IAW CARS STD 571 APPENDIX F, ITEM K.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081113		NM  	2008	11	13	CA080708011      	1	20080708	G	2497		WIRE            			BOEING	737   	737400      	138449A	NM  										COCKPIT	CHAFED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA			35061								(CAN) P5 OVERHEAD COCKPIT PANEL WAS OPENED DURING NORMAL MX ACTIVITIES AT THE C2 MX EVENT. ARCING WAS NOTED BETWEEN THE 	DOOR WARNING MODULE AND ADJACENT WIRE BUNDLES. DAMAGE TO WIRING WAS ALSO FOUND AT THE P5-13, ELECTRICAL METERS AND GALLE	Y POWER MODULE. INSPECTION REVEALED NO AFFECT TO ACFT STRUCTURE, BUT 6 WIRES WERE FOUND CHAFFED REVEALING THEIR RESPECTI	VE CONDUCTORS (REF A AND C). A 7TH WIRE WAS FOUND SEVERED. THE MODULES WILL BE TESTED FOR SERVICEABILITY AS A SMALL BURN	 MARK WAS FOUND AT THE CORNER OF THE CASE.   THE FOLLOWING WIRES ARE TO BE REPLACED TO CORRECT THE DEFECTS FOUND: 1. W03	6-650-22, WDM ATA 29-11-01. W036-8769-22, WDM ATA 24-31-11. W036-15A-24, WDM ATA 21-58-03 PG1 4. W036-043-22, WDM ATA 24	2	L	7	2 	4F			RT	A16WE   					 
	20081113		NE  	2008	11	13	CA080709001      	2	20080706	G	7320	7982133007	EEC             			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON TAKE OFF, THROUGH 400 FT WITH BLEEDS ON AND CLIMB POWER SET 90% NH + 900 RPM, ENGINE LT EXPERIENCED A SURGE. LT	 NH WENT 110%, THEN DROPPED TO 70%. RESTABILIZED AT 90%. REDUCED POWER TO BOTH ENGINES. RETURNED FOR LANDING. GROUND RUN	S WERE COMPLETED COULD NOT DUPLICATE, THE DATA FROM THE ONBOARD ACFT FLIGHT INFORMATION REPORTING SYSTEM (AFIRS) AND IT 	WAS FOUND THAT THERE WAS AN INCREASE IN FUEL FLOW TO THE ENGINE CAUSING THE POWER SURGE. THE ENGINE ELECTRONIC CONTROL U	NIT (EECU) WAS REPLACED THE ENGINES WERE GROUND RUN AND NO FAULTS WERE FOUND.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081113		EU  	2008	11	13	CA080709002      	1	20080708	G	3220	5322012289	DRAG LINK       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6663 								(CAN) NLG DRAG LINK FOUND CRACKED DURING PREFLIGHT INSP. DRAG LINK REPLACED WITH NEW. THIS IS THE 3RD ONE FOUND CRACKED 	ON 3 DIFFERENT ACFT IN THE LAST 6 MONTHS IN THE EXACT SAME SPOT. ALL DRAG BRACES SENT TO MFG FOR INVESTIGATION.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081113		NM  	2008	11	13	CA080709003      	1	20080709	G	2710		CONTROL CABLE   			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					AILERONS	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			2634 								(CAN) FOUND BALL END OF LT AND RT AILERON CONTROL CABLES NOT FULLY ENGAGED IN WW BELLCRANK CABLE SLOT.(FWD CABLE)  BALL 	END OF LT AND RT AILERON CONTROL CABLES IN WW BELLCRANK CABLE SLOT.(FWD CABLE) REENGAGED PROPERLY IN ACCORDANCE WITH AMM	 27-11-03-400-801.  SEE ATTACH PICTURE				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081113		NM  	2008	11	13	CA080709004      	1	20080709	G	5753	19092001405	CARRIAGE        			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					LT TE FLAP	GROOVED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2634 								(CAN) LT INBD FLAP MAIN 1 CARRIAGE ASSY (P/N 190-92001-405) FOUND GROOVED INSIDE BY LOOSE BOLT FROM TRACK ASSY.  ENGINEE	RING ADVISED THE ROOT CAUSE OF THE DAMAGE OF THE FLAP CARRIAGE IS CAUSE BY THE FLAP TRACK MECHANISM LOOSE BOLT.					2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081113		EU  	2008	11	13	CA080709005      	1	20080706	G	2720	RS87	RETAINING RING  	BRAERO      		BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	RUDDER PEDAL	MISSING         	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			500  								(CAN) RUDDER PEDAL BECAME DISENGAGED FROM PEDAL SPIGOT, RS87 RETAINING RING CAME OUT OF RETAINING SLOT. RETAINING RING S	EEMED TO HAVE INSUFFICIENT TENSION TO STAY IN SLOT. NEW RING INSTALLED AND NO FURTHER PROBLEMS. FLEETWIDE INSPECTION CAR	RIED OUT AND NO SIMILAR PROBLEMS FOUND.				2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
	20081113		NM  	2008	11	13	CA080709006      	1	20080703	G	2710	19005549401	CONTROL CABLE   			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1407 								(CAN) DURING CONTROL CABLES INSPECTION ON LT AND RT WINGS, FOUND AILERON CABLES (LT PN 190-04212-401, PN 190-04209-401, 	PN 190-05549-401, RT PN 190 -05551-401, PN 190-05550-401, PN 190-04209-401) WORN AND WITH SEVERAL WIRES BROKEN AT FAIRLE	AD.    EMBRAER CAME UP WITH 2 SERVICES BULLETIN:  SB190-27-0017 EMBRAER FLIGHT CONTROLS - AILERON - CABLES WEAR  SB170-2	7-0028 EMBRAER FLIGHT CONTROLS - AILERON - CABLES WEAR			2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081113		NM  	2008	11	13	CA080709007      	1	20080709	G	3220	19070150404	BUSHING         			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					NLG	MIGRATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2634 								(CAN) DURING INSPECTION FOUND BUSHING MIGRATED ON NLG RETRACK ACTUATOR LOWER ATTACHMENT (PRC BROKEN) AND ON RT MLG SIDE 	STAY LOWER ATTACHMENT.  NLG SHOCK STUT ASSY PN 190-70453-401 SN 00053  MLG SIDE STAY PN 190-70150-404 SN 00053  AFTER IN	VESTIGATION FOUND NO CLEARANCE FIT, EMBRAER HAS BEEN ADVISED OF THE PROBLEM. THIS PROBLEM HAS BEEN ALREADY FOUND ON NUME	ROUS ACFT			2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081113		EA  	2008	11	13	CA080709008      	2	20080704	G	8530		EXHAUST VALVE   								LYC   	O540  	O540*       	41532	EA  					ENGINE	SEIZED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) DURING A FLIGHT IN THE R44 HELICOPTER, THE PILOT NOTICED A SIGNIFICANT VIBRATION APPROX. 2 HOURS INTO THE FLIGHT. 	THE VIBRATION LASTED 45 SECONDS. THERE WERE NO AUDIBLE ALARMS & ALL GAUGES READ NORMAL.  THE A/C WAS DESCENDING WITHOUT 	CONTOL INPUTS,AFTER THE 45 SECOND VIBRATION SUBSIDED.A/C RETURNED TO BASE. THE A/C WAS STARTED THE FOLLOWING DAY THE VIB	RATION WAS NOTED @102% IN HOVER ,A/C LANDED,WAS SHUT DOWN AND SB388C(VALVE CLEARANCE CHECK) WAS CARRIED OUT.NUMBER 3 AND	 NR 6 EXHUAST VALVES WERE SEIZED WITH BENT PUSH RODS.CYLINDER NUMBER 1, 2,,4 VALVES WERE BELOW THE ALLOWABLE CLEARANCE							3	O			E295				 
	20081113		NE  	2008	11	13	CA080709009      	3	20080703	G	6111	SFA13N1ROA1D	BLADE           			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	PROP ASSY	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			10   								(CAN) 3 BLADES FOUND LEAKING AFTER 10 HRS OF INSTALLATION. THESE BLADES WERE ALREADY SENT  FOR TEFLON STRIP REPLACEMENT 	DUE TO THE SAME KIND OF SNAG EARLIER THIS SPRING.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
	20081113		NE  	2008	11	13	CA080709010      	2	20080706	G	8550		SCAVENGE PUMP   			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN) NR4 BMEP WENT TO 0. OIL TANK QUANTITY DROPPED FROM 25GALS TO 12 GALS IN A FEW MINUTES. ENGINE WAS FEATHERED AND LA	NDING CARRIED OUT WITHOUT FURTHER INCIDENT.					2	L	7	4 	4R	3	R		6A4     	ATC14	6	C	P871	 
	20081113		GL  	2008	11	13	CA080709011      	3	20080709	G	6111	A1851B	BEARING RACE    													HARTZL	HCB3R	HCB3R304    	GL  	PROPELLER	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER WAS RECEIVED IN SHOP FOR REMOVAL OF A BROKEN OFF GREASE NIPPLE IN BLADE CLAMP. BLADE CLAMP REQUIRED REMO	VAL TO EXTRACT BROKEN GREASE NIPPLE. WHEN THE CLAMP WAS REMOVED A CHIP OF THE OTBD BEARING FELL OUT. AFTER EXAMINING THE	 BEARING IT WAS DETERMINED THAT THE ENTIRE ASSEMBLY SHOULD BE REPLACED DUE TO EXCESSIVE RACE AND BALL WEAR. IT SHOULD BE	 NOTED THAT THE GREASE IN THIS CLAMP WAS BLACK FROM METAL WEAR WHEREAS THE GREASE IN THE OTHER 2 BLADE CLAMPS WAS IN NOR	MAL CONDITION FOR THIS PROP TYPE. BEARING WAS REPLACED AND PROPELLER RETURNED TO SERVICE.												5	C	P28EA	 
	20081113		SW  	2008	11	13	CA080710001      	1	20080708	G	5620	412670101	WINDOW          			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					PAX DOOR	MISSING         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			5    								(CAN) WHILE THE ACFT WAS IN A DIVE, IN ORDER TO REACH VNE FOR RADS READING, AFT RT PASSENGER DOOR WINDOW WAS LOST IN FLI	GHT AT 138 KNOTS.					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
	20081113		SW  	2008	11	13	CA080710002      	1	20080618	G	2550	26801500	CABLE           			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					CARGO HOOK ASSY	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			284  								(CAN) MANUAL RELEASE CABLE BROKE AT CARGO HOOK FITTING CAUSING HOOK TO RELEASE INFLIGHT.						1	G	7	1 	3U	3	U		R00001RC	E42NE				 
	20081113		EU  	2008	11	13	CA080710003      	1	20080704	G	2822	045004B145A	SWITCH          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  					FUEL PUMP	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			435  								(CAN) FUEL PUMP WOULD NOT TURN ON						1	G	7	1 	3U	3	U		H9EU    	E00054EN				 
	20081113		CE  	2008	11	13	CA080710004      	1	20080709	G	7120	J124532	MOUNT           			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	DEFORMED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1863 								(CAN) DURING ENGINE INSPECTION NOTED THAT THE LT AND RT FORWARD ENGINE MOUNTS WERE SAGGING TO THE POINT THAT DURING TAKE	OFF POWER ON ENGINE AND INTAKE PIPE HOSE CLAMP MADE CONTACT WITH THE UPPER PORTION OF ENGINE MOUNT.  THE LORD MOUNT APPE	ARED TO BE SAGGING/DROOPING BUT NOT SEPERATED ANYWHERE. BOTH FRONT ENGINE MOUNTS REPLACED WITH NEW.				1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
	20081113		NE  	2008	11	13	CA080710005      	2	20080708	G	8530		EXHAUST VALVE   								PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	DAMAGED         	W				O				OTHER                   				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			CA			1513 	1513 							(CAN) EXHAUST VALVE BROKE/SEPARATED DURING FLIGHT. BASE OF VALVE STAYED IN COMBUSTION SECTION OF CYLINDER AS ENGINE RAN 	CAUSING DAMAGE TO PISTON, AND UPPER CYLINDER COMBUSTION CHAMBER. PILOT REPORTED DECREASE IN POWER/VIBRATION AND UPON THR	OTTLING BACK, AN INCREASE IN VIBRATION.  ACFT LANDED WITHOUT INCIDENT. CYLINDER HEAD FOUND TO HAVE BEEN BROKEN OFF, MOST	 OF CYLINDER PARTS RECOVERED IN COWLING EXCEPT FOR EXHAUST SYSTEM. LOWER EX VALVE BASE SHOWS SIGN OF HAVING BEEN CRUSHED	 ABOVE PISTON REPEATEDLY UNTIL CYLINDER FAILED. UNKNOWN AS TO IF EXHAUST VALVE WAS REPLACED NEW, WITH SERVICEABLE, OR OV	ERHAULED AT LAST ENGINE OVERHAUL.						3	R			5E1				 
	20081113		SW  	2008	11	13	CA080710006      	1	20080709	G	5410	205030195030	BEAM            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317BLYC   	41616	NE  					LT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, NOTICED A CRACK ON THE LT MAIN BEAM CAP UPPER WEB NEAR THE FORWARD ENGINE FIRE WALL. THE ACFT W	AS GROUNDED. THE AIRFRAME TIME 15185 HOURS. THE TIME ON THE MAIN BEAM CAP IS UNKNOWN.					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081113		EU  	2008	11	13	CA080711001      	1	20080708	G	2121	BC112A2	FAN             			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F26 	NE  	CABIN	OVERHEATED      	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ON JULY 8/2008, SHORTLY AFTER TAKEOFF THE CREW NOTICED AN ELECTRICAL ODOR WHICH WAS ALSO CONFIRMED BY THE F/A. THE	 CREW DECLARED AN EMERGENCY AND PROCEEDED TO LAND WITHOUT INCIDENT. MX WAS DISPATCHED TO THE ACFT WHERE IT WAS NOTICED T	HAT WHEN THE FLIGHT DECK RECIRCULATION FAN WAS SELECTED THE CONTROL BREAKER POPPED. THE CENTER ISLE FLOOR BOARDS WERE RE	MOVED AND AN INSPECTION WAS CARRIED OUT ON BOTH FANS. IT WAS DETERMINED THAT THE FLIGHT DECK FAN HAD OVERHEATED AND WAS 	THE SOURCE OF THE PROBLEM. MX MEL`ED THE FAN AND THE CREW CARRIED OUT A TEST FLIGHT AS AN EXTRA PRECAUTION. THE ACFT WAS	 RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
	20081113			2008	11	13	CA080711002      	4	20080709	G	3451	6221234013	INDICATOR       			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	DME	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE CREW REPORTED A LOUD POP WHICH WAS FOLLOWED BY AN ELECTRICAL ODOR AND THE DME WENT OFF LINE. THE C	REW SHUT DOWN ALL NON-ESSENTIAL AVIONICS AND CONTINUED WITHOUT INCIDENT. THE ACFT WAS THEN POSITIONED AT THE HANGAR WHER	E MX REMOVED AND CARRIED OUT AN INSPECTION ON THE DME INDICATOR. UPON A CLOSER LOOK IT WAS NOTICED THAT THE CAPACITOR HA	D FAILED. IT WAS DETERMINED THAT THE INDICATOR WAS THE SOURCE OF THE PROBLEM.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081113		EA  	2008	11	13	CA080711003      	1	20080704	G	2810	2156400212	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  											LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A FUEL CELL CHANGE DUE TO A LEAK PROBLEM, THE TECHNICIAN DID A LEAK TEST ON THE NEW 1 THAT WAS COMING FROM 	THE STORE AND RECEIVED FROM DIRAZUR- ZODIAC GROUP ON JULY 2007,(WELL PRESERVE). H E FOUND THAT IT WAS LEAKING FROM THE C	ENT.  NOTE: WEVE HAD SO MANY PROBLEMS WITH THESE CELLS THAT WE MADE AN INTERNAL PROCEDURE TO TEST THEM BEFORE INSTALLAT	ION			2	H	7	2 	4T			RT	A14EA   					 
	20081113		GL  	2008	11	13	CA080711004      	1	20080627	G	2150	347074	BEARING         			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					ACM IMPELLER	DRAGGING        	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) CREW REPORTS THEY WERE ON TAXI WAY, HAVING JUST LEFT THE FBO WHEN THICK GREY SMOKE STARTED ROLLING OUT OF THE VENT	S. THE CABIN FILLED UP QUICKLY ENOUGH THEY WERE STARTING TO HAVE TROUBLE BREATHING. ONLY THING THEY MANAGED TO DO WAS SH	UT DOWN AND GET OUT OF ACFT. RAMP AGENT FOR THE FBO DROVE UP IN A TRUCK, SAW WHAT WAS GOING ON, AND CALLED THE FIRE DEPA	RTMENT. FD USED THERMAL IMAGING TO DETERMINE THERE WAS NO FIRE AND LEFT. NO EMERGENCY WAS DECLARED.			2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
	20081113		SO  	2008	11	13	CA080711005      	2	20080620	G	8530	AEC646263	PISTON          			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	SKIRT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			517  								(CAN) A PIECE OF NR 2 PISTON SKIRT WAS BROKEN OFF AT THE OIL CONTROL RING GROOVE.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
	20081113		NE  	2008	11	13	CA080711006      	2	20080701	G	7230		BLADES          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					COMPRESSOR	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL200, THE PILOT NOTED THE ENGINE TEMPERATURE RAPIDLY RAISING TO 850C WITH POWER TURBINE SPEED D	ECREASING. HE ELECTED TO SHUT THE ENGINE DOWN AND PERFORMED A SUCCESSFUL DEAD STICK LANDING.  POST FLIGHT ENGINE EXAMINA	TION REVEALED HEAVY RUBBING DAMAGE IN THE COMPRESSOR SECTION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADV	ISE OF ROOT CAUSE ONCE ESTABLISHED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
	20081113		CE  	2008	11	13	CA080711007      	1	20080626	G	7932	30B385103	SENSOR          			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					RT ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1155 	1155 							(CAN) DURING MX VISUAL CHECK OF RT ENGINE A SMALL AMOUNT OF OIL WAS NOTED AROUND THE ENGINE LOW LEVEL OIL SENSOR.  FURTH	ER INVESTIGATION FOUND OIL LEAKING INTERNALLY THROUGH SENSOR AND EXITING OUT OF CANNON PLUG. RT LOW LEVEL OIL SENSOR WAS	 REPLACED WITH NEW AND NO FURTHER LEAKS WERE DETECTED.				2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
	20081113		EA  	2008	11	13	CA080711008      	1	20080706	G	3240	AE87996E	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					NR 2 BRAKE ASSY	DISCONNECTED    	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			CA											(CAN) ACFT HAD A NORMAL LANDING ON ARRIVAL IN IND, HOWEVER WHILE ATTEMPTING TO TAXI OFF THE RUNWAY, EXCESSIVE POWER WAS 	REQUIRED TO TAXI.  IT WAS SUSPECTED THAT NR 2 BRAKE ASSEMBLY HAD SEIZED AS SMOKE COMING FROM THE NR 2 BRAKE. CONTRACT MX	 INVESTIGATED THE ACFT AND THE QUICK DISCONNECT HYDRALIC LINE TO THE NR 2 BRAKE OFF. THE QUICK DISCONNECT WAS RESECURED 	AND THE BRAKES WERE FUNCTION CHECKED SERVICEABLE. THERE HAS BEEN NO FURTHER OCCURANCES TO DATE. IT IS SUSPECTED THAT THE	 QUICK DISCONNECT CONNECTOR MAY HAVE BACKED OFF CAUSING THE DRAGGING BRAKE CONDITION.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081113		NE  	2008	11	13	CA080711009      	2	20080629	G	7261		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  						OIL CONSUMPTION 	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING T/O ROLL, THE PILOT RECEIVED A LOSS OF OIL PRESSURE WARNING AND ABORTED T/O. THE ACFT RETURNED TO THE RAMP 	WHERE THEY OBSERVED NO OIL ON THE SIGHT GLASS. OIL WAS NOTED IN THE EXHAUST AND A GROUND RUN SHOWED A CONSUMPTION OF 2 Q	UARTS IN 10 MIN. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20081113		EU  	2008	11	13	CA080711010      	1	20080705	G	7797		CONNECTOR       			BAG   	ATP   	ATP         	       	EU  	PWA   	PW120 	PW126A      	 	NE  					ENGINE	CONTAMINATED    	W				O				OTHER                   				R	X		PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE ENGINE TORQUE STARTED TO FLUCTUATE BETWEEN 60% TO 120% AND THE ENGINE SHUT ITSELF DOWN. TROUBLE	SHOOTING REVEALED HEAVY CONTAMINATION ON 1 OF THE CONNECTORS OF THE ENGINE ELECTRONIC CONTROL. THE CONNECTOR WAS CLEANED	, GROUND RUN PERFORMED AND ACFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A27NM   	E2ONE				 
	20081113		NE  	2008	11	13	CA080711011      	2	20080706	G	8530	399354	CYLINDER HEAD   			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA				372  							(CAN) IN FLIGHT ENGINE BECAME ROUGH - POPPING/BANGING SOUND PRECAUTION AND LANDING COMPLETED ENGINE INSPECTED - CYL NR 3	 HEAD FOUND BROKEN FROM BARREL. REMAINDER OF CYLS VISUALLY INSPECTED WITH NO DAMAGES FOUND. CYL NR 3 ASSY. REPLACED WITH	 OVERHAULED UNIT. - GROUND RUN SATISFACTORY. RERUN TO AWD 78-08-07 (VISUAL INSP.) CYLINDER FAILURE IS NOT UNHEARD OF ON 	THESE AIRPLANES			1	H	7	1 	3R	3	R	RC	A806    	5E1				 
	20081113		SO  	2008	11	13	CA080711012      	1	20080705	G	8011	MHB4016R	STARTER         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  						INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				48   							(CAN) THE STARTER WOULD NOT WORK AT ALL, REPLACED WITH A SERVICEABLE STARTER.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20081113		EA  	2008	11	13	CA080712001      	1	20080711	G	3240	2604141	HOUSING         			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					BRAKE PISTON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1057 							(CAN) DURING NDT AT OVERHAUL, 2 CRACKS DISCOVERED AT BOTTOM OF PISTON BORE IN BRAKE HOUSING. THESE HOUSINGS ARE NDT`D AT	 OVERHAUL AND EVERY BRAKE LINING CHANGE PER THE BF GOODRICH MANUAL 32-48-24 PAGE 512.					2	H	7	2 	4R	4	R	RT	A14EA   	E231				 
	20081113		CE  	2008	11	13	CA080714001      	1	20080708	G	5343		TRUNNION        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  						MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  ATTACHMENT HARDWARE THAT WAS FOUND INSTALLED IN THE CHANNEL-TRUNION BRACE WAS NOT WHAT IS CALLED FOR IN ACFT I.P.	C. 53-11-01 01 .THE INSTALLED HARDWARE WAS 4 AN3-5A BOLTS WITH AN960-3 WASHERS UNDER BOTH THE HEAD OF THE BOLTS AND UNDE	R THE NUTS. THE LENGTH OF THE BOLT AT THE FORWARD LT CORNER OF THE CHANNEL-TRUNION BRACE WAS TOO LONG WHEN INSTALLED AND	 INTERFERED WITH THE AFT TRAVEL OF THE STEERING ARM LOCATED JUST BELOW THE CHANNEL-TRUNION BRACE SUPPORT ASSEMBLY. THE I	.P.C. CALLS FOR 4MS27039-1-07 SCREWS AND 4 MS21042-3 NUTS (NO WASHERS ARE CALLED FOR IN THE INSTALLATION).		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081113		SO  	2008	11	13	CA080714003      	1	20080714	G	8120	4091709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			800  								(CAN) RT TURBOCHARGER FAILED SHORTLY AFTER T/O. ENGINE SHUTDOWN AND ACFT RETURNED TO AIRPORT FOR AN UNEVENTFUL LANDING.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20081113		NM  	2008	11	13	CA080714004      	1	20080712	G	8097		WIRE            			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					START VALVE	DAMAGED         	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE FROM TORONTO DURING THE CLIMB, THE CREW STARTED RECEIVING UNEXPECTED ECAM MSGS REGARDING THEIR NR 	2 ENGINE. THE CLIMB WAS STOPPED AT FL230 WHERE THE CREW TRIED TO WORK OUT THE ECAM ITEMS WITH MX. THE ENGINE LOST ALL PO	WER AND WAS SHUT DOWN. THERE WAS NO FIRE WARNING. THE FLIGHT RETURNED TO TORONTO WHERE AN UNEVENTFUL OVERWEIGHT LANDING 	TOOK PLACE. THERE WAS NO ADVERSE PASSENGER REACTIONS REPORTED BY THE FLIGHT CREW.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
	20081113		EA  	2008	11	13	CA080714005      	1	20080708	G	1400	TBC6EM106727	BOLT            			DHAV  	DHC6  	DHC6        	2802606	EA  										DRAIN VALVE	MISMANUFACTURED 	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) TBAL HAD A CUSTOMER REPORT OF THE LOCK WIRE TEARING THROUGH THE LOCK WIRE HOLE DURING INSTALLATION ON 2 OF THE 4 P	URCHASED DRAIN VALVE BOLTS.  ALL BOLTS IN STOCK WERE PULLED FROM THE SHELF AND EXAMINED. THE BOLTS CONFORMED TO THE TBAL	 DRAWING. THE BOLTS THAT WERE ON THE 1 END OF THE TOLERANCE WERE CLOSE TO THE EDGE. AN OEM BOLT WAS PURCHASED AND COMPAR	ED TO TBAL DRAWINGS. THE LOCK WIRE HOLE WAS CLOSER TO THE EDGE OF THE HEAD ON THE TBAL PART WHEN COMPARED AGAINST THE OE	M. A TOTAL OF 11 BOLTS WERE SOLD. THE CUSTOMER WITH THE 2 OF 4 BOLTS IS RETURNING 2 BAD ONES AND USING THE 2 GOOD ONES. 	WE ARE IN THE PROCESS OF CONTACTING THE REMAINING 4 CUSTOMERS WHO HAD PURCHASED THE BOLTS TO ADVISE THEM OF THE PROBLEM.	1	H	7	2 	3T			RT	A9EA    					 
	20081118			2008	11	18	CA080714006      	4	20080714	G	2565		LINE            	BFGOODRICH  																ESCAPE SLIDE	MISROUTED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FIRST VISIT IN SLIDE SHOP OF THE ERJ-175 SLIDE S/N ED0522 FTN 4W94YL DURING THE INCOMING INSPECTION IT WAS DISCOVE	RED THAT THE FOLLOWING PROBLEMS WOULD HAVE PREVENTED THE DEPLOYMENT OF THE SLIDE EITHER MANUALLY OR AUTOMATICALLY.  CORD	 WAS FORGOTTEN ON THE SPEED LACING LOOP THUS PREVENTING AUTO DEPLOY. PHOTO FIG. 1  THE MANUAL FIRING LINE WAS NOT ROUTED	 PROPERLY. PHOTOS ARE FIG. 2 AND 3.																 
	20081110		GL  	2008	11	10	CA080714007      	2	20080711	G	7250	9362M43P02	TURBINE WHEEL   								GE    	CF6   	CF680C2*    	 	GL  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			45222	13716							(CAN) DURING SHOP INSPECTION CRACKS FOUND ON FWD DOVETAIL SEPARATIONS IN EXCESS OF MANUAL LIMITS.											4	F			E23EA				 
	20081110		EA  	2008	11	10	CA080714008      	1	20080710	G	2820		SLEEVE          	GE          		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  						WORN            	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DEFECT: ON CLIMB OUT, "L FUEL LO PRESS" MSG WAS ON AS PER DEFECT 309471. THE "L EJECTOR MAIN" EICAS MASTER CAUTION	 CAME ON AND L ENGINE RUNNING ROUGH. "FUEL IMBALANCE" EICAS CAME ON, CENTER FUEL TANK NOW @ 1600 LBS. LT ENGINE SHUT DOW	N CARRIED OUT.  RECTIFICATION: AFTER INVESTIGATION, FOUND A COUPLING DISCONNECTED ON MAIN LT ENGINE FUEL FEED LINE LOCAT	ED IN THE CENTER TANK. REASON WHY THE CENTER TANK WAS @ 1600 LBS AND CAUSED AN IMBALANCE.   FOUND SLEEVE/COUPLING DAMAGE	D.  NEW COUPLING ASSEMBLY REINSTALLED PROPERLY ON ENGINE FUEL FEED LINE, ENGINE RUNS, LEAK CHECK CARRIED OUT AND ACFT BA	CK IN SERVICE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081110		NM  	2008	11	10	CA080715001      	1	20080625	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYDRAULIC SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			4584 								(CAN) DURING CRUISE FLIGHT EDP NR 1 FAILED AND HYDRAULIC PRESSURE WAS LOST. SPU TURNED ON THEN TURNED OFF DUE TO LOSS OF	 HYDRAULIC FLUID NR 1 SYSTEM. ACFT LANDED AT DESTINATION AIRPORT WITHOUT INCIDENT.   GROUND INSPECTIONS REVEALED METAL I	N CASE DRAIN FILTER. EDP REPLACED AND ACFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081110		CE  	2008	11	10	CA080715002      	1	20080715	G	5342	04310093	ATTACH FITTING  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  		CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11005								(CAN) LT ATTACH FITTING CRACKED AT LOWER OUTSIDE RADIUS ADJACENT TO AN 4-6A ATTACH BOLT.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081112		CE  	2008	11	12	CA080715003      	1	20080702	G	2421		COMMUTATOR      	KELLY       		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ALTERNATOR	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			CA				289  							(CAN) FLIGHT CREW NOTICED THE ALTERNATOR WAS NOT CHARGING ON DESCENT. UPON CLOSER INSPECTION IT WAS FOUND THAT THE COMMU	TATOR AND BRUSHES WITHIN THE RECENTLY O/H ALTERNATOR SHOWED SIGNS OF SIGNIFICANT ABNORMAL WEAR.  THE ALTERNATOR WAS LOW 	TIME AND HAD NOT GONE THROUGH ITS 500 HR INSPECTION YET SO IT WAS DETERMINED THAT THE WEAR HAD BEGUN FROM THE TIME OF O/	H.  THE ALTERNATOR WAS REPLACED WITH ANOTHER O/H ALTERNATOR & RETURNED TO SERVICE.			1	H	7	1 	3O	3	O		A4CE    	E5CE				 
	20081112		EU  	2008	11	12	CA080715004      	1	20080714	G	2421	31342001	SHAFT           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	GENERATOR	SHEARED         	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA				418  							(CAN) RT AC GENERATOR FAIL LIGHT ILLUMINATED IN FLIGHT, SYSTEM WAS DEFERRED AS PER THE MEL. WHEN ACFT WAS AT A MX BASE, 	THE AC GENERATOR WAS REMOVED AND FOUND TO HAVE A SHEARED SHAFT. GENERATOR WAS REPLACED. NO FURTHER ISSUES.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
	20081112		EU  	2008	11	12	CA080715005      	1	20080711	G	5415	417157001	BRACKET         			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101*     		NE  					FUEL FILTER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			175  								(CAN) DURING THE 100 HRS INSPECTION ON THE ENGINE, THE AME DISCOVERED 2 CRACKS ON THE ENGINE HIGH PRESSURE FUEL FILTER S	UPPORT, 1 AT THE TOP AND 1 AT THE BOTTOM ASSEMBLY HOLDING HOLES GOING FROM EACH HOLE TO THE EDGE OF SUPPORT.					1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
	20081112		SO  	2008	11	12	CA080715006      	2	20080708	G	8530		STUD            	SUPERIOR    		CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					CYLINDER HEAD	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA				735  							(CAN) A COMPLETE SEPARATION OF THE CYLINDER HEAD FROM THE BARREL OCCURRED. THE SEPARATION SEEMED TO HAVE STARTED IN THE 	EXHAUST PORT AREA.					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
	20081112		SW  	2008	11	12	CA080715007      	1	20080715	G	6410	206011809005	PITCH HORN      	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	25OC  	250C20R     	 	GL  					T/R HUB	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE PITCH HORN STUD FAILED WHILE INSTALLING A NUT P/N MS14145L5. A "CLICKER-TYPE" TORQUE WRENCH SET TO 60 INCH/LBS	 WAS USED TO INSTALL THE NUT. THE REQUIRED FINAL TORQUE FOR THIS NUT IS 50-60 INCH/LBS PLUS TARE. THE TIGHTENING TORQUE 	NEVER REACHED 60 INCH/LBS.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081112		CE  	2008	11	12	CA080716001      	1	20080715	G	2121	99101133	COOLING FAN     			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  						NOISY           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLOOD COOLING FAN NOISY.  FUNCTIONAL CHECK CONFIRMED SNAG, UNIT REMOVED FROM ACFT AND REPLACED WITH OVERHAULED UNI	T.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081112		EA  	2008	11	12	CA080716002      	1	20080710	G	2810	K215T640024	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  					NR 4	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAK FROM RT WING. CHANGED NR4 RT PN-K215 T64002-4 SN 89306.						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
	20081112		EU  	2008	11	12	CA080716003      	1	20080714	G	5415	417157001	BRACKET         			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101*     		NE  					FUEL FILTER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			790  								(CAN) CRACK DISCOVERED DURING ENGINE VISUAL INSPECTION ON THE HIGH PRESSURE FUEL ASSEMBLY SUPPORT, CRACK ON THE TOP HOLD	ING HOLE, FROM HOLE TO THE EDGE OF SUPPORT.					1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
	20081112		EU  	2008	11	12	CA080716004      	1	20080624	G	6220	350A31182703	FREQ ADAPTER    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					MAIN ROTOR HEAD	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			5299 								(CAN) WORN TO SERVICEABLE LIMITS, RUBBER DEBONDING FROM ITS METHC SURFACE. REPLACED WITH A NEW SET.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081112		EU  	2008	11	12	CA080716007      	1	20080707	G	5350		FAIRING         			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FIRST AIR HAS OBSERVED SEVERAL OCCURRENCES OF DEGRADATION IN THE SURFACE PROTECTION COATING ON THE ACFT LOWER CENT	ER SECTION FAIRING PANELS. THE MATERIAL IS APPLIED IN ACCORDANCE WITH ATR SERVICE BULLETIN ATR42-53-0102. INVESTIGATION 	HAS FOUND THAT THE DEGRADATION APPEARS TO BE ATTRIBUTED TO FLUID CONTAMINATION FROM THE HYDRAULIC SYSTEMS WHICH ARE HOUS	ED WITHIN THE LANDING GEAR BAY AREA WHICH IS FAIRED IN BY THE AFFECTED PANELS.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20081112		NM  	2008	11	12	CA080716008      	1	20080714	G	2781	H1010271	POSITION SWITCH 			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 6 L/E SLAT	MALFUNCTIONED   	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA				1450 							(CAN) ON APPROACH AN IN-TRANSIT INDICATION WAS ILLUMINATED ON THE NR 6 L/E SLAT. THE CREW ELECTED TO RETURN TO VANCOUVER	 WHERE THEY LANDED WITHOUT INCIDENT. INSPECTION REVEALED THAT THE NR 6 L/E SLAT WAS FUNCTIONING CORRECTLY BUT THE L/E SL	AT POSITION SWITCH WAS UNSERVICEABLE. THE SWITCH WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
	20081112			2008	11	12	CA080716009      	4	20080716	G	2562	E01G	G SWITCH        																	ELT	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL BENCH RECERTIFICATION OF ELT, THE OPS OF THE G-SWITCH WAS TESTED AND FOUND TO BE STICKING INTERMITTE	NTLY.  THE G- SWITCH WAS REPLACED AND OPS WAS TESTED SEVERAL TIMES TO ENSURE NEW G SWITCH IS OPERATING CORRECTLY.  NO FU	RTHER PROBLEMS NOTED																	 
	20081112		GL  	2008	11	12	CA080717001      	2	20080705	G	7323	23076061	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				246  							(CAN) DURING GROUND RUN THE GOVERNOR WOULD NOT MAINTAIN ENGINE RPM. REMOVED AND SERVICEABLE GOVERNOR INSTALLED.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081112		WP  	2008	11	12	CA080717002      	1	20080714	G	6310	C0512REVU	ACTUATOR        			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CLUTCH	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1067 								(CAN) THE CLUTCH WOULD NOT ENGAGE, FERRY FLIGHT PERMIT APPROVED AND ACFT RETURNED TO BASE. THE MICROSWITCH WAS FOUND FAU	LTY, CLUTCH ACTUATOR R&R WITH A SERVICEABLE ACTUATOR					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081112		NM  	2008	11	12	CA080717003      	1	20080716	G	5347	17003263001	SEAT TRACK      			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5800 								(CAN) EVIDENCE OF CORROSION FOUND AT SEVERAL AREAS.  REFERENCE: J/C NR Z220-005-U & NON-ROUTINE NR 46, 48 CORROSION FOUN	D ON FLOOR BEAM LOCATED AT Y = 225.0 AND Z = -490.0 JUNCTION WITH FRAMES 17 AND ON FLOOR BEAM LOCATED AT Y = -255.0 AND 	Z = -490.0 JUNCTION WITH FRAME NR 19.  SEAT TRACKS AFFECTED: P/N 170-03264-001 AND P/N 170-03263-001				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081112		EU  	2008	11	12	CA080717005      	1	20080715	G	6730	SC5083SN2353	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  						MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			2017 								(CAN) ON A EUROCOPTER AS350 B2  DURING HYDRAULIC TEST PROCEDURES FOR FIRST FLIGHT OF THE DAY THE PILOT ENCOUNTERED THE C	YCLIC BEING DRIVEN HARD OVER TO THE LT STOP. DURING TROUBLESHOOTING THIS PROBLEM WAS NOT EASILY REPEATABLE EVERYTIME THE	 TEST WAS COMPLETED. REMOVAL OF THIS COMPONENT HAS SO FAR REMOVED THE ISSUE. THE SERVO HAS BEEN SENT OUT FOR TEST AND RE	PAIR.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081112		SW  	2008	11	12	CA080718001      	1	20080713	G	6230		BEARING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					M/R MAST	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA			6478 	17   							(CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPS, UPON DESCENT WITH AN EXTERNAL LOAD, THE MASTER CAUTION WARNING INDICATI	ON ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED AND THE 	TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSURE. THE PIC DISCONTINUED ANY FURTHER OPS AND PROCEEDED TO LAND NOR	MALLY IN AN ADJACENT CUT BLOCK. A POST-SHUTDOWN INSPECTION BY THE AME REVEALED AN ABUNDANCE OF ALUMINUM METAL SHAVINGS I	N THE OIL SYSTEM AND OIL FILTER. FURTHER DISASSEMBLY AND INSPECTION OF THE OIL SUMP SCREEN AND SUBSEQUENT REMOVAL OF THE	 OIL PUMP INDICATED EVEN MORE METAL SHAVINGS BUT THE ORIGIN OF THE MATERIAL COULD NOT DETERMINED.  DURING THE FIELD REMO	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081112		EU  	2008	11	12	CA080718002      	1	20080715	G	3222	5322012289	DRAG LINK       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TAIL GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7560 								(CAN) THIS IS THE 4TH LINK WE HAVE FOUND CRACKED IN OUR FLEET IN SAME LOCATION. PLEASE SEE PREVIOUS SDR`S FOR PICTURES.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081112		EA  	2008	11	12	CA080718003      	1	20080712	G	5610	NP139322001	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) FLT NR 5820, CAPTAINS SIDE WINDSHIELD CRACKED. WINDOW CRACKED FROM LOWER LT CORNER TO UPPER RT CORNER. CALLED AMER	ICAN EAGLE AND THEY DETERMINED IT WAS THE INNER PLY. ACFT TO FERRY IN THE MORNING TO COS.  CAPTAIN SIDE WINDSHIELD R&R.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081112		EU  	2008	11	12	CA080718004      	1	20080717	G	3251	176SF2DT102W0162	POTENTIOMETER   			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE331*     	01514	WP  					STEERING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA			7    								(CAN) ON TAKE OFF ACFT ROTATED PILOT FELT SOMETHING ABNORMAL IN RUDDER PEDALS, SELECTED GEAR UP , GEAR HANDLE WOULD NOT 	MOVE, PILOT OBSERVED GEAR HANDLE LOCK STILL IN PLACE. ACFT FLOWN BACK TO BASE , PILOT DID A LOW FLYBY WHERE IT WAS CONFI	RMED THAT THE NOSE GEAR STEERING WAS ALL THE WAY TO THE LT.  ACFT LANDED SAFELY UPON NOSE TOUCHED DOWN IT CENTERED ITSEL	F AND WAS TAXIED BACK USING ENGINE DIFFERENTIAL POWER. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE STEERING POTENTI	OMETER HAD FAILED CAUSING THE NOSE GEAR TO GO LT DISENGAGING THE NOSE GEAR STEERING NOT ALLOWING THE NOSE GEAR CENTERING	 SWITCH TO CENTER GEAR FOR GEAR RETRACTION.	2	H	7	2 	4T	3	T	RT	A16EU   	E2WE				 
	20081112		EA  	2008	11	12	CA080718005      	2	20080714	G	7314	91380003	PUMP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				3516 							(CAN) AFTER REPLACING THE ENGINE, A LEAK CHECK WAS COMPLETED AND IT WAS FOUND THAT THE LP FUEL PUMP WAS LOOSING FUEL OUT	 THE VENT LINE. THE PUMP WAS REPLACED WITH NO FURTHER PROBLEMS.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081112		NE  	2008	11	12	CA080718006      	2	20080714	G	8530	127951	WASHER          			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					INTAKE VALVE	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1188 							(CAN) DURING AN OIL LEAK REPAIR ON THE R2800 RT ENGINE, IT WAS DISCOVERED THAT THE ROCKER CAP ON CYLINDER NR 4 WAS CRACK	ED. CAP WAS REMOVED AND FOUND THAT 1/3 OF THE INTAKE VALVE UPPER WASHER WAS BROKEN OFF AND THE PIECE WAS LAYING IN THE R	OCKER BOX AREA. INSPECTION REVEALED THAT THE WASHER PIECE HAD BEEN PUSHED AROUND THE ROCKER BOX AREA, CRACKING THE ROCKE	R CAP, DAMAGING THE INTAKE VALVE SPRING, AND SCRATCHING THE INTERIOR OF THE ROCKER BOX AREA.  MAIN ENGINE OIL SCREEN WAS	 CHECKED FOR CONTAMINATION. SMALL AMOUNT OF NON FERROUS METAL FOUND IN SCREEN. SCREEN CLEANED AND RE-INSTALLED. NR 4 CYL	INDER WAS REPLACED WITH AN OVERHAULED UNIT. ACFT RUN UP, ENGINES CHECKED FOR POWER AND LEAKS, AND ACFT WAS RETURNED TO S	2	H	7	2 	4R	4	R	RT	A14EA   	E231				 
	20081112		SW  	2008	11	12	CA080718007      	1	20080717	G	6320	206040184001	PUMP            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TRANSMISSION	DISLODGED       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		HO	HOVERING       	1			CA				28   							(CAN) THE SEAL FOR THE TRANSMISSION OIL PUMP BECAME DISLODGED, AND LOSS OF OIL OCCURRED.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081112		CE  	2008	11	12	CA080721001      	1	20080714	G	4997		WIRE            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					APU	CHAFED          	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			30   								(CAN) PATS APU INSTALLATION STC SA95-34 FIRE WARNING AFTER 20 MIN OF APU OPERATION PRIOR TO ENGINE START. APU AUTO SHUTD	OWN AND FIRE EXT FIRED. VISUAL INSPECTION OF EXTERIOR OF APU ENCLOSURE SHOWED NO EVIDENCE OF FIRE. APU REMOVED AND FOUND	 WIRES APU2002-20B, APU200-20A AND APU1019-16 CHAFED. APU2000-20A HAD SHORTED TO  FIRE LOOP IN 2 LOCATIONS RESULTING IN 	ARCING AND OVERHEAT OF THE LOOP IN THAT LOCATION. ALL WIRING REPLACED, HIGH TEMP SPIRAL WRAP INSTALLED TO PROTECT WIRING	. BOMBARDIER ADVISED VIA FIELD SERVICE REP.		2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
	20081112		CE  	2008	11	12	CA080721003      	1	20080721	G	5552	26340231	FITTING         	CESSNA      		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					BEARING SUPPORT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE MOVEMENT OF THE ELEVATOR WAS NOTED AS NOT BEING `SMOOTH`. ON INVESTIGATION IT WAS FOUND THAT THE BEARING IN TH	E SUPPORT BRACKET WAS SEIZED AND THAT THE SUPPORT BRACKET ALSO HAD CORROSION. THE BRACKET (AND BEARING) WILL BE REPLACED	 WITH NEW BEFORE NEXT FLIGHT.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081112		WP  	2008	11	12	CA080721005      	1	20080721	G	6310	C0511	ACTUATOR        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CLUTCH	DAMAGED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 INSPECTION AND ACTUATOR FUNCTION TEST, 1 OF THE COLUMN SPRINGS SWITCH DID NOT RESPOND. FANWHEEL ASSY RE	MOVED AND SWITCHES CHECKED MANUALLY AND FOUND SERVICEABLE. IT SEEMS LIKE THE SPRINGS ON 1 SIDE DID NOT PUSH THE SWITCH C	OMPLETELY AND THERE WAS ONLY 1 SWITCH ACTIVE. ACTUATOR ASSEMBLY SENT TO R.H.C.				1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081112		SW  	2008	11	12	CA080722001      	1	20080713	G	6320		BEARING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					M/R MAST	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA			6478 	17   							(CAN) UPON DESCENT WITH AN EXTERNAL LOAD, MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PAN	EL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED, TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSU	RE. A POST-SHUTDOWN INSP BY AME REVEALED AN ABUNDANCE OF ALUMINUM METAL SHAVINGS IN THE OIL SYS AND OIL FILTER. FURTHER 	DISASSEMBLY AND INSP OF OIL PUMP INDICATED EVEN MORE METAL SHAVINGS BUT ORIGIN OF THE MATERIAL COULD NOT DETERMINED.  DU	RING THE FIELD REMOVAL OF THE TRANSMISSION, IT WAS DISCOVERED THAT THE LOWER BEARING RACE RETAINING NUT ON THE MAST ASSY	 HAD BROKEN FREE OF IS TORQUE AND LOCKING DEVICE. NUT BACKED OFF ALL THE WAY TO LAST THREAD CARVING A ONE INCH DEEP GROO	1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081112		EU  	2008	11	12	CA080722002      	1	20080707	G	2731	EM40112	ACTUATOR        	PIAGIO      		PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	ELEVATOR TRIM	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA				605  							(CAN) THE HORIZONTAL STABILIZER PRIMARY TRIM FAILED IN THE DOWN MODE ONLY. THE ACFT THEN PROCEEDED TO THE NEAREST AIRPOR	T. MAINT CONFIRMED THE SNAG ON THE GROUND. AFTER REPLACING THE HORIZONTAL TRIM ACTUATOR THE SYS FUNCTIONED NORMAL.					1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE	 
	20081112		EU  	2008	11	12	CA080722003      	1	20080716	G	6310	350A351069	GIMBAL PIN      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  						DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACFT WAS INSPECTED FOLLOWING A HARD LANDING, MAIN AND TAIL ROTOR STRIKES IAW  MET 05.53.00.603, 604 AND 605. GIMBA	L PINS (ALL 4 OF THEM) WERE SENT ALONG WITH OTHER PARTS FOR NDT (NO REQUIREMENT TO CHECK THE GIMBAL PINS AFTER AN INCIDE	NT), AND 3 OF 4 WERE FOUND TO HAVE CRACKS IN THE FLANGED END, CAUSING REJECTION OF THE 3 PINS.  PINS ARE PART OF ENG TO 	MAIN GEAR BOX COUPLING, HOLDING COUPLING TUBE TO GIMBAL RING AND GIMBAL RING TO ROTOR BRAKE HSG.  DAMAGED ACFT HAS YET T	O BE REASSEMBLED TO FLIGHT CONDITION).		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081112		NE  	2008	11	12	CA080722004      	2	20080718	G	7314		SEAL            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL PUMP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			4973 								(CAN) ON DAILY INSP, FUEL WAS DISCOVERED IN THE OIL SEAL DRAIN COLLECTOR CAN. FURTHER INVESTIGATION FOUND FUEL LEAKING F	ROM THE SEAL ON THE FUEL HIGH PRESSURE PUMP. THERE WAS NO INDICATION OF GREASE WASH OUT OF THE FCU BRG. THE FUEL PUMP WA	S REPLACED WITH A SERVICEABLE UNIT.				1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20081230		EU  	2008	12	30	CA080722005      	1	20080716	G	6230	350A37122021	STOP            	TMECA       		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					M/R SHAFT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			6074 								(CAN) ON ROUTINE MAST RECONDITIONING AND INSP (6 YEAR INSP REQUIREMENT), THE RING WAS SENT FOR NDT ALONG WITH THE REST O	F THE PARTS FROM THE ASSY (NO NDT REQUIREMENT FOR THE RING AT ANY POINT, OR FOR ANY PART OF THE ASSY AT THE 6 YEAR INSP)	. THERE WAS A STRESS CRACK DURING MPI CHECK, WHICH WAS CAUSE FOR REJECTION OF THE PART.  THE RING IS LOCATED AT THE TOP 	OF THE MAIN ROTOR SHAFT, WHERE THE ROTOR HEAD ATTACHES, AND ROTATES WITH THE MAIN ROTOR SHAFT/HEAD. THE CUSTOMER WAS NOT	IFIED OF THE DEFECT AND THE PART WAS REPLACED.		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081112		EA  	2008	11	12	CA080722007      	1	20080718	G	5700	C6FSM244335	BUSHING         			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING LUG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BUSHINGS MISSING FROM WING PICKUP LUGS ON ORIGINAL FRAMES INSTALLED IN ACFT.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081112			2008	11	12	CA080722008      	2	20080722	G	7414	M3548	ROTOR           																	MAGNETO	BROKEN          	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA			364  								(CAN) MAGNETO INSPECTED FOR SB 2-08/3-08 COMPLIANCE. DISTRIBUTOR GEAR FAILED, ROTOR GEAR FAILED, CARBON BRUSH FAILED. DU	RING REMOVAL OF ROTOR GEAR FOR REPLACEMENT, BROKEN POST LODGED IN GEAR. DISTRIBUTOR GEAR AND ROTOR GEAR WERE HOLDING THE	 BROKEN POST IN PLACE DURING OPERATION. EDGE OF BROKEN POST WAS WORN INDICATING BREAK OCCURRED SOME TIME AGO.																	 
	20081112		NE  	2008	11	12	CA080722009      	1	20080722	G	7603	S6130620173	THROTTLE PLATE  			SKRSKY	S61   	S61A        	814210C	NE  											FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) S61 ENGINEERS WERE REPLACING A EMERGENCY THROTTLE PLATE P/N S6130-62017-3 WITH A PLATE THAT HAD BEEN RECEIVED. ON 	INSTALLATION WHEN TIGHTENING THE BOLTS, THE PLATE SHATTERED AT THE FWD BOLT HOLE. ALL 10 PLATES RECEIVED IN FROM THIS VE	NDOR HAVE BEEN ACCOUNTED FOR AND ARE IN QUARANTINE. PRELIMINARY INSP OF THE PART HAVE REVEALED THE FOLLOWING:  DEFECTIVE	 PLATE WAS IDENTIFIED WITH THE PROPER P/N IAW THE S61 IPC FIGURE 118 ITEM 25 AND APPEARED TO MEET FIT FORM AND FUNCTION.	  A TEST DONE ON ONE OF THE PLATES REMOVED FROM SERVICE WHICH INDICATED THE PART TO BE FERROUS, HOWEVER WAS EXTREMELY BR	ITTLE AS IT FAILED INSTANTLY UNDER MINIMAL PRESSURE WITHOUT BENDING. SUSPECTED BOGUS PARTS.	2	G	7	2 	4U				H2EA    					 
	20081112		NM  	2008	11	12	CA080723001      	1	20080720	G	3260	7002537	CONTROL UNIT    			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			LD	LANDING        	1			CA			673  								(CAN) LANDING GEAR INOPERATIVE CAUTION LIGHT ILLUMINATED DURING DESCENT, LIGHT WAS CONTINUOUS ALL THE WAY BACK TO BASE. 	REMOVED AND REPLACED ADVISORY CONTROL UNIT IAW AMM 33-13-00. PERFORMED LANDING GEAR RETRACTION TEST-RESULTS SATISFACTORY	.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081112		NE  	2008	11	12	CA080723002      	2	20080708	G	7261		RETAINING NUT   								PWC   	PW308 	PW308C      	52182	NE  					OIL PUMP ASSY	DISLODGED       	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			791  								(CAN) THE LOW OIL PRESSURE WARNING ACTIVATED DURING TAKEOFF ROLL AND TAKEOFF WAS ABORTED. SUBSEQUENT INSP REVEALED THE O	IL PUMP GEARSHAFT RETAINING NUT AND TAD WASHER COMPLETELY DISLODGED FROM THE SHAFT. MFG WILL INVESTIGATE TO REVIEW ASSY 	PROCEDURES AND REPORT ON ROOT CAUSE ONCE ESTABLISHED.									4	F			E00065EN				 
	20081112		GL  	2008	11	12	CA080723003      	3	20080718	G	6111		SEALANT         			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	BLADE CLAMP	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT PILOT EXPERIENCED A BUILD UP OF GREASE ON WINDSHIELD. PILOT ABORTED LOAD IN DESIGNATED AREA AND R	ETURNED TO BASE. UPON INSP GREASE APPEARED TO BE COMING FROM 1 OR 2 BLADE CLAMPS. BLADE CLAMP SEALS WERE REPLACED IN BOT	H UNITS. NO OBVIOUS DAMAGE WAS FOUND ON REMOVED SEALS OR PROP ASSY. SEALANT MAY HAVE FAILED. ACFT WAS RETURNED TO SERVIC	E AFTER GROUND FUNCTION CHECKS.			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
	20081112		EU  	2008	11	12	CA080723004      	1	20080527	G	6710	350A27134320	STOP            			AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COLLECTIVE	DAMAGED         	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) ACFT WAS CLIMBING AT APPROX 6000` ASL. (OAT 1C). COLLECTIVE HIT ITS UPPER STOP DURING A POWER INCREASE. AT THIS P	OINT TORQUE READING WAS APPROX 65 PERCENT. T4 AND NG WERE WELL WITHIN MAX CONTINUOUS LIMITATIONS.  ON 14 MAY 2006, SB 67	.00.12 REV. 2 WAS CARRIED OUT ON THE ACFT. THIS MODIFICATION INVOLVED THE INSTALLATION AND POSITIONING OF A NEW STOP PLA	TE ON THE UPPER PART OF THE COLLECTIVE QUADRANT. POSITIONING THIS STOP PLATE (P/N 350A27-1343-20) IAW INSTRUCTIONS PROVI	DED IN SB 67.00.12 REV. 2 PARAGRAPH 2.B.2 RESULTS IN THE UPPER COLLECTIVE TRAVEL BEING LIMITED. END RESULT WAS THE SERVO	 INPUT RODS UPWARD TRAVEL BEING LIMITED BY APPROX 6MM AT FULL COLLECTIVE. PARAGRAPH 2.B.3. OF SB 67.00.12 REQUIRES THAT 	1	G	7	2 	3U	3	U		H11EU   	E4CE				 
	20081112		EU  	2008	11	12	CA080723005      	1	20080722	G	2730	Z4244120000	CABLE           			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	ELEV TRIM TAB	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1899 								(CAN) CABLE WAS DISCOVERED FRAYED DURING REGULARY SCHEDULED MAINT.						1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
	20081112		CE  	2008	11	12	CA080723006      	1	20080721	G	2421		ALTERNATOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  		FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, PILOT NOTICED KX155 NAV/COM FLASHING ITS DISPLAY AND VOR NEEDLE ERATIC. PILOT DECLARED NORDO AND LA	NDED SAFELY WITHOUT FURTHER INCIDENCE. MAINT ATTEPTED TO START ACFT AND DISCOVERED BATTERY ALMOST DEAD. ACFT CHARGING SY	S HAD MALFUNCTIONED DURING FLIGHT AND PILOTS WERE UNAWARE OF THE PROBLEM. MFG INSTALLED AMMETER SHOWS VERY LITTLE NEEDLE	 DEFLECTION WHEN SYS IS OPERATING NORMALLY, EVEN UNDER HEAVY LOAD. ALSO, EARLIER 152`S WERE PROVIDED WITH AN OVERVOLT RE	D LIGHT ONLY. LATER 152S INCORPORATE AN UNDERVOLT LIGHT WHICH IS MORE USEFULL. MAINTENANCE CHARGED BATTERY AND REPAIRED 	BROKEN RING TERMINAL ON ALTERNATOR FIELD WIRE, ACFT RETURNED TO SERVICE.	1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081112		WP  	2008	11	12	CA080724001      	1	20080707	G	2822	C81878	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL BOOST	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			610  								(CAN) FUEL PUMP WARNING LIGHT ILLUMINATED IN FLIGHT. AUX. PUMP HAD FAILED. ENGINE CONTINUED RUNNING ON MECHANICAL PUMP. 	A/C FLOWN TO MAINT BASE, ELECTRIC PUMP REPLACED. FUNCTION AND LEAK CHECK PERFORMED. CAUSE OF PUMP FAILURE UNKNOWN.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081112		WP  	2008	11	12	CA080724003      	2	20080717	G	7230	31037081	BEARING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COMPRESSOR	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1917 								(CAN) SN OF THE PART IS MS030633106124 WAS UNABLE TO PUT THIS INTO SN FIELD.  A/C WAS DOWN FOR A ROUTINE OIL SAMPLE. AT 	THIS TIME THE OIL SAMPLE WAS NOTED TO HAVE A UNUSUAL AMOUNT OF METAL IN THE OIL SAMPLE. THE ENGINE SHOP WAS INFORMED TO 	HAVE A LOOK AT THE METAL AND IT WAS DETERMINED FROM ENGINE SHOP THAT THE ENGINE NEEDED REPAIR AT THAT TIME. UPON DISSASE	MBLY OF THE ENGINE GEAR BOX IT WAS FOUND THAT THE COMPRESSOR BALL BEARING WAS STARTING TO HAVE METAL SPAWLING COMING FRO	M THE INNER RACE. THE ENGINE WAS REPAIRED ON WING AND WITH A NEW COMPRESSOR BEARING ALL METAL FLUSHED FROM ENGINE AND TH	E A/C WAS RETURNED TO SERVICE WITH NO MORE ISSUES.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081112		CE  	2008	11	12	CA080724004      	1	20080721	G	7720		INDICATOR       			BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ITT	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) WHILE RETURNING TO HOME BASE AT CRUISE FLIGHT, FLIGHT CREW NOTICED THAT THE LT ITT GAUGE WAS ERRATIC. THERE WAS NO	 NOTICE IN ENGINE PERFORMANCE NOR WERE ANY OF THE REMAINING ENGINE INSTRUMENTS SUPPORTING ENGINE PERFORMANCE ISSUES. UPO	N RETURN TO BASE, MAINT TROUBLESHOT THE ITT SYS AND DISCOVERED THAT THE ITT HARNESS HAS 3000 OHMS TO GROUND WHERE THE MI	NIMUM LIMITS ARE 100000 OHMS. A NEW HARNESS HAS BEEN ORDERED AND WILL BE INSTALLED. THIS SDR HAS BEEN REPORTED PREVIOUSL	Y UNDER SDRS 20080103005 AND 20070223002. SUPPLEMENTARY SDR TO FOLLOW WITH ASSY AND PART FAILURE INFORMATION.		1	L	7	2 	3T	4	T		A14CE   	E2WE	6	C	P40EA	 
	20081112		NE  	2008	11	12	CA080724006      	2	20080717	G	7321	0164548250	FUEL CONTROL    								TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			561  								(CAN) MAIN ROTOR RPM KEPT DECREASING AFTER ADJUSTMENT, OIL ALSO FOUND IN THE INPUT SEAL DRAIN TUBE. NO LONGER ABLE TO AD	JUST IAW MM. UNIT REPLACED WITH SERVICEABLE FCU AND DEFECTIVE UNIT SENT TO MFG FOR INVESTIGATION AND WARRANTY REPAIR.										3	U			E19EU				 
	20081112		WP  	2008	11	12	CA080724007      	1	20080722	G	3411		PITOT SYSTEM    			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	NR 2	CLOGGED         	W				C				ABORTED TAKEOFF         				G			MULTIPLE FAILURE          			TO	TAKEOFF        	1			CA											(CAN) BOTH NR 1 AND NR 2 PITOT SYS INDICATED NO AIRSPEED ON TAKEOFF RUN. TAKEOFF WAS ABORTED. BUGS AND SIMILAR DEBRIS FO	UND IN BOTH PITOT SYS. APAR LINES BLOWN OUT, PITOT SYS FUNCTION CHECKED SERVICEABLE.					2	L	7	4 	4R	3	R		6A4     	ATC14	6	C	P871	 
	20081113			2008	11	13	CA080724008      	4	20080628	G	6122	1219310	PLUG            	WOODWARD    		DIAMON	DA40  	DA40        	2990002	GL  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROP GOVERNOR	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA			300  								(CAN) WE WERE CLIMBING OUT OF KSBM GOING THRU 4,000 FEET MSL, WHEN THE ENGINE/PROP OVER SPEEDED. IT TOPPED OUT AT SOMETH	ING OVER 3,100 RPM. IT TOOK ABOUT 5 TO 10 SECONDS TO GET THE POWER PULLED OFF. BY CAREFUL USE OF THE THROTTLE (2650 RPM 	MAX), WE WERE ABLE TO MAINTAIN FLYING SPEED, LEVEL FLIGHT AT ABOUT 80 TO 85 KTS.  DIVERTED AND DECLARED AN EMERGENCY. TH	E LANDING WAS ACCOMPLISHED WITHOUT ANY PROBLEMS AND NO FURTHER DAMAGE WAS SUSTAINED TO THE ACFT.   BEGAN THE INVESTIGATI	ON INTO WHAT CAUSED THE FAILURE. AFTER ELIMINATING SOME OTHER PROBABLE CAUSES WE CAME TO THE PROPELLER GOVERNOR.  IT LOO	KS AS IF A SCREW PLUG BACKED OUT OF AN INTERNAL PASSAGE WITHIN THE GOVERNOR, DUMPING THE OIL PRESSURE AND CAUSING THE PR	1	L	7	1 	3O			NT	A47CE   		5	C	P920	 
	20081112		CE  	2008	11	12	CA080725001      	1	20080709	G	2460	70002450	CIRCUIT BREAKER 			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  					LT POWER FEED	TRIPPED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			261  								(CAN) LT POWER FEED CIRCUIT BREAKER (ONE OF 3 IN PARALLEL) POPS OPEN IN FLIGHT. P/N 700-024-50 REPLACED NEW.						2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20081112		NE  	2008	11	12	CA080725002      	1	20080716	G	2913	66WAP2001	BOLT            			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					HYD PUMP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON POST FLIGHT INSP, ONE BOLT HEAD WAS FOUND DETACHED FROM THE PUMP ASSY.  HAVE EXPERIENCED ONE PREVIOUS OCCURENCE	, SEE SDR20060818006.					2	G	7	2 	4U	4	U		1H15    	1E3				 
	20090102		EU  	2009	1	2	CA080725003      	1	20080720	G	2910		HYDRAULIC SYSTEM			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  						MALFUNCTIONED   	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) AT GROUND IDLE, THE NORMAL PROCEDURE IS TO TEST ACCUMULATORS BY PUSHING THE ACCUMULATORS BUTTON ON, AND THE HYD LI	GHT ILLUMINATES , AND PROCEED TO TEST THE ACTUATORS BY MOVING THE CYCLIC FWD AND AFT, ABOUT 4-5 INCHES TRAVEL, EIGHT TIM	ES, THEN RT AND LT, THE SAME. NORMAL (NORMALLY,  DO NOT TOTALLY DEPLETE THE ACCUMULATORS PRESSURE). THIS WAS NORMAL, NO	 PROBLEM ANY OF THE TEST OF THIS SYS AT ANY TIME. PUSH THE SWITCH AGAIN, AND THE ACCUMULATORS BACK ON, HYD LIGHT OUT.  T	HE HYD CUT OFF TEST. STILL OPERATING AT GROUND IDLE. COLLECTIVE LOCKED DOWN, SWITCHING OFF THE HYD SWITCH ON COLLECTIVE,	 HYD LIGHT ILLUMINATES, AND WHAT THE CYCLIC IS SUPPOSED TO DO IS PULL IT SELF TO THE CENTER NEUTRAL POSITION, WITH RESIS	1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
	20081112		NM  	2008	11	12	CA080728001      	1	20080723	G	2432	20412	BATTERY         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	MASTER	OVERTEMP        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			14134	594  							(CAN) DURING CRUISE THE CREW RECEIVED A MAIN BATTERY HOT WARNING MESSAGE. THE HIGH TEMP WAS CONFIRMED ON THE BATTERY TEM	P MONITOR. THE CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT.  THE BATTERY TEMPERATURE WAS EVALUATED AT 180C. 	THE BATTERY COMPARTMENT WAS CLEANED, THE BATTERY REPLACED. ACFT WAS RELEASED AND RETURNED INTO SERVICE.  BATTERY HAS BEE	N RETURNED TO THE COMPANY IN-HOUSE COMPONENT SHOP TO DETERMINE THE CAUSE OF THE THERMAL RUN-AWAY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081112		NM  	2008	11	12	CA080728003      	1	20080725	G	2710		PCU             			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					AILERONS	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENROUTE, CREW NOTICED HYD SYS (A) QUANTITY DECREASING RAPIDLY. SYS (A) HYDR WERE SHUTOFF AND EMERGENCY DECLARED. U	PON ARRIVAL AT DESTINATION, A/C REQUIRED TOWING TO RAMP WHERE MAINT DISCOVERED THE AILERON PCU HAD FAILED. THE AILERON P	CU WAS REPLACED AND A/C RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
	20081112		EU  	2008	11	12	CA080728004      	1	20080708	G	2530	8001060000LH	OVEN            			AIRBUS	310   	A310304     	3930339	EU  											DIRTY           	W				A				UNSCHED LANDING         				W	B		INADEQUATE Q C            	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			CA			7873 	5582 							(CAN) FLIGHT RETURNED TO THE STATION DUE TO CABIN SMOKE FROM FWD OVEN (DARK SMOKE). CABIN DETECTOR ACTIVATED. BOTH FWD O	VENS INSPECTED AND ELECTRICAL CONNECTION CHECKED AND FOUND SERVICEABLE. LT OVEN INSERTS FOUND DIRTY (FOOD RESIDUE). OVEN	 REPLACED AND SERVICEABLE IAW MM25-30-00. OVEN ROUTED TO REPAIR SHOP FOR INVESTIGATION.				2	L	7	2 	4F			RT	A35EU   					 
	20081112		EU  	2008	11	12	CA080728005      	1	20080721	G	2897	NSA931322100	CIRCUIT BREAKER 			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					FUEL PUMP	BURNED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TROUBLESHOOTING OF THE INOPERATIVE LT OUTER TANK FUEL PUMP (DEACTIVATED IAW MEL) THE CIRCUIT BREAKER 3QA WA	S FOUND BURNED, BODY CRACKED AND ONE LEG MISSING. CIRCUIT BREAKER WAS REPLACED AND SYS TESTED SERVICEABLE. A DETAILED VI	SUAL INSPECTION CAMPAIN WAS INITIATED TO INSPECT ALL CIRCUIT BREAKERS IN THE 101VU ELECTRICAL PANEL.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
	20081112		NM  	2008	11	12	CA080728006      	1	20080725	G	2897	F759857SC	WIRE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	SWITCH	CHAFED          	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			40501	40501							(CAN) DURING TAXI, NR2 TANK FUEL LOW LEVEL CAUTION LIGHT ILLUMINATED. MAINT GROUND RUN AND NR2 TANK LOW LEVEL LIGHT INTE	RMITTENT. ACFT DISPATCHED UNDER MEL FOR FUEL LOW LEVEL INDICATION. LATER MAINT INSP DURING SWITCH REPLACEMENT, FOUND SWI	TCH WIRE CHAFED ON CONDUIT. SWITCH ASSY REPLACED. (NOTE: PART IS CONSIDERED AN EXPENDABLE AND PART TIMES NOT TRACKED. TI	ME PROVIDED ARE ACFT TIMES).			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081112		SW  	2008	11	12	CA080728007      	1	20080722	G	5280		STRUCTURE       			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG DOOR	BENT            	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH PILOT EXTENDED GEAR AND HAD GREEN INDICATION FOR NOSE AND LT MAIN GEAR ONLY, INTRANSIT LIGHT WAS ON FO	R RT GEAR. PILOT RECYCLED GEAR AND ALL 3 GREEN INDICATIONS WERE NOW PRESENT. ACFT LANDED WITHOUT FURTHER PROBLEMS. MAINT	 WAS CALLED AS THE RT GEAR DOORS WERE BENT JUST AFT OF THE FRONT HINGE. IT APPEARED THAT THE DOOR WAS HUNG UP ON THE FRO	NT EDGE OF THE GEAR DOOR AND WAS BENT WHEN THE GEAR WAS SELECTED DOWN.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081112			2008	11	12	CA080728008      	4	20080722	G	6122	31039391	FITTING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROP GOVERNOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION, IT WAS DISCOVERED THAT THERE WAS AN OIL LEAK AROUND THE RT ENGINE PROP GOVERNOR. UPON FURTHER INSPE	CTION IT WAS FOUND THAT THE FITTING WAS CRACKED HALF WAY AROUND THE FITTING.   FITTING REPLACED AND ACFT RETURNED TO SER	VICE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081112		EU  	2008	11	12	CA080728009      	1	20080719	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2989 	2989 							(CAN) FOUND T/R BLADE CRACKED NEAR TIP OF BLADE AND TRAILING EDGE ON DAILY INSPECTION. BLADE REMOVED FOR EVALUATION BY M	FG.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081112		SW  	2008	11	12	CA080728010      	1	20080704	G	6730	212076005011	PILOT VALVE     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					LT CYCLIC	CHATTERING      	W				A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			CA											(CAN) ACFT ENCOUNTERED VIBRATION, FELT THROUGH FLIGHT CONTROLS. VIBRATION WORSENED RAPIDLY DURING RETURN TO BASE. UPON A	RRIVAL TO BASE, ENGINEER INSPECTED ACFT AND FOUND LT CYCLIC SERVO PILOT VALVE TO BE CHATTERING EXCESSIVELY, CAUSING UNCO	MMANDED CYCLIC INPUTS. ACFT WAS GROUNDED. CYCLIC SERVO REPLACED, A/C TEST FLOWN AND WAS RELEASED FOR RETURN TO SERVICE. 	SUSPECT SERVO WAS SENT TO O/H FACILITY FOR EVALUATION, FOUND EXCESSIVE WEAR ON PILOT VALVE ASSY.			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081112		EU  	2008	11	12	CA080729001      	1	20080718	G	2120		GUARD           			PILATS	PC12  	PC1247      	7090552	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	REEFER PACK	CUT             	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) THE REFRIGERATION PACK MOTOR BELT SLIPPED ON THE MOTOR GEAR CAUSING THE WEAR ON THE GEAR. THE MOTOR GEAR LIP TO ST	OP THE BELT FROM GOING OUT OF THE GEAR IS WORN OUT ALSO, CHAFING THE BELT PLASTIC GUARD. THE GUARD IS CUT.					1	L	7	1 	4T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081112		SO  	2008	11	12	CA080729003      	1	20080724	G	5310	MS212505	BOLT            			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	FUSELAGE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			5040 								(CAN) ENROUTE, THE LOAD MASTER OBSERVED AN UNUSUAL SOUND FROM THE CARGO BAY AREA. UPON INVESTIGATION AN UNUSUAL GAP WAS 	NOTICED BETWEEN THE LANDING GEAR BAY WEB AND THE BOTTOM EDGE OF THE DRAG ANGLE VERTICAL FLANGE. THE GAP WAS ESTIMATED AT	 .125 FROM STA 570 TO 580. THE CREW ELECTED TO RETURN  WHERE THE ACFT LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED TH	AT AN APPARENT FASTENER FAILURE COMMON TO THE STA 577 BEAM AND THE DRAG ANGLE GENERATED THE GAP. THE ACFT WAS REPOSITION	ED UNDER PERMIT WHERE FURTHER ASSESSMENT IS ONGOING.		2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
	20081113		EU  	2008	11	13	CA080729006      	1	20080727	G	2913	AIR29804	COVER           	LKHEED      		BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					HYDRAULIC PUMP	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE ENROUTE FROM YBK TO YTH FAMO EXPERIENCED LOSS OF HYDRAULIC PRESSURE. AN EMERGENCY WAS DECLARED AND THE ACFT 	DIVERTED TO YTH WHERE AN UNEVENTFUL LANDING WAS MADE. DURING THE FLIGHT HYDRAULIC PRESSURE WAS SEEN TO RISE AND FALL A N	R OF TIMES. EMERGENCY U/C ACTUATION WAS NOT REQUIRED. UNDER INSPECTION THE RT HYDRAULIC PUMP WAS FOUND TO BE LEAKING. TH	E PUMP WAS CHANGED AND THE SYSTEM EXHIBITED NO DEFECTS DURING FUNCTION TESTING. THE PUMP WAS INSPECTED AND THE LEAK WAS 	FOUND TO BE FROM THE TOP EDGE OF THE END COVER THROUGH A NR OF PIN HOLES IN THE CASTING. THERE WERE NO LEAKS THROUGH THE	 PUMP FIXTURES AND FITTINGS. THE PUMP WILL BE SENT FOR STRIP EVALUATION.	2	L	7	2 	3T	4	T		A24EU   	A196				 
	20081112		GL  	2008	11	12	CA080729007      	1	20080725	G	5730		SKIN            			DIAMON	DA40  	DA40        	2990002	GL  										WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A INSP CARRIED OUT ON WING, SHOWED GAPS IN THE SPAR TO SKIN BOND LINES. DO NOT BELIEVE THIS TO BE AN IMMEDIATE SAF	ETY ISSUE BUT ARE WORKING QUICKLY AND DILIGENTLY TO GET TO ROOT CAUSE AND CORRECTIVE ACTION.					1	L	7	1 	3O			NT	A47CE   					 
	20081112		NE  	2008	11	12	CA080730001      	2	20080623	G	7220	4037T84P03	NUT             								GE    	CF34  	CF343B1     	30070	NE  					ENGINE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SHOP VISIT, ONE VARIABLE VANE SPINDLE NUT WAS FOUND MISSING ON STAGE 5 VANE. THE LEVER ARM REMAINED ENGAGED	. A NUT WAS INSTALLED IAW THE ENGINE MANUAL 72-32-00 AS RECOMMENDED IAW SB 72-0184.										4	F			E15NE				 
	20081112		NM  	2008	11	12	CA080730002      	1	20080730	G	2611	774001	SMOKE DETECTOR  			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 6	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA				2774 							(CAN) ON CLIMB THROUGH FL290 CARGO SMOKE 6TH POSITION LIGHT ILLUMINATED AND FIRE WARNING BELL SOUNDED. ACFT RETURNED. ON	 ARRIVAL, NO SMOKE DETECTION LIGHTS WERE ILLUMINATED ON FE PANEL. CARGO AREA INSPECTED FOR SMOKE. NONE FOUND. SUSPECTED 	FAILURE OF NR 6 SMOKE DETECTOR. PART REMOVED AND REPLACED. SYSTEM FUNCTION CHECKED SERVICEABLE.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081112		SO  	2008	11	12	CA080730003      	2	20080730	G	8530		SPRING          	ECI         							CONT  	O520  	IO520F      	17032	SO  					EXHAUST VALVE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13   								(CAN) CYLINDER WAS PULLED DUE TO LOW COMPRESSION. WHEN THE ROCKER COVER WAS REMOVED IT WAS DISCOVERED THAT BOTH THE INNE	R AND OUTER EXHAUST VALVE SPRINGS WERE BROKEN INTO MANY PIECES.										3	O			E5CE				 
	20081112		EA  	2008	11	12	CA080730004      	1	20080714	G	5522	85520056	SKIN            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			40619	40619							(CAN) DURING MAINT, VISUAL INSP OF VERTICAL FIN/HORIZONTAL STABILIZER , A CRACK 2.25 INCHES LONG ENCOMPASSING (2) RIVETS	 AT RIB YH 13.80 EXTENDING FWD FROM A POINT3.5 INCHES FROM THE AFT T/E, WAS NOTED. DAMAGE REPAIR IAW REPAIR DRAWING RD8-	55-1968 AND SRM PRACTICES.  AIRCRAFT RETURNED TO SERVICE. DAMAGE BELIEVED TO BE FATIGUE RELATED AS NO NOTED IMPACT DAMAG	E.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081112		NE  	2008	11	12	CA080730005      	2	20080728	G	7321	0164548540	FUEL CONTROL    			SNIAS 	350   	AS350*      	       	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) FLUCTUATION OF NG (+/- 2 PERCENT) IN CRUISE FLIGHT. ACFT LANDED AT THE BASE NORMALLY. ENGINE INSPECTED. RUN-UP CAR	RIED OUT, NG FLUCTUATION CONFIRMED ON THE GROUND (82.5 TO 84.5 PERCENT), NR FLUCTUATION ON THE GROUND (374 - 380). FCU R	EPLACED (PART REMOVED WAS 1369.6 HOURS TSO). TEST FLIGHT CONDUCTED AFTER FCU REPLACEMENT AND FOUND SATISFACTORY.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081112		EA  	2008	11	12	CA080730006      	2	20080713	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) 10 MINUTES AFTER TAKEOFF, THE ENGINE OIL PRESSURE AND TORQUE INDICATION DECREASED BELOW ALLOWABLE LIMITS. THE ENGI	NE WAS SHUTDOWN AND SECURED BY THE FLIGHT CREW.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE	 ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081112		EA  	2008	11	12	CA080730007      	2	20080706	G	7250		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 1	ERRATIC         	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL THE NR 1 ITT DROPPED TO 230 DEGREES AND WAS ERRATIC. THE PILOT ELECTED TO ABORT THE TAKEOFF AN	D RETURNED TO THE GATE. TROUBLESHOOTING DISCLOSED FAULT CODE (FC) 973 T6 OPEN CIRCUIT. FURTHER INTERROGATION OF FC CONFI	RMED 973 PRESENT ON BOTH A&B CHANNELS. THE T6 HARNESS WAS REPLACED AND THE ACFT RETURNED TO SERVICE. ERRATIC ITT INDICAT	ION WAS NOTED BY THE CREW DURING THE PREVIOUS FLIGHT.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081112		NE  	2008	11	12	CA080730008      	2	20080503	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						POWER LOSS      	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB AT APPROX 3,000 FEET ABOVE GROUND LEVEL, PILOT HEARD A LOUD BANG AND EXPERIENCED COMPLETE LOSS OF POW	ER . PILOT DECLARED EMERGENCY AND PERFORMED A DEAD STICK LANDING. AN UNEVENTFUL LANDING WAS ACCOMPLISHED. POST INSP REVE	ALED CT BLADE DISTRESS. ENGINE WAS REMOVED AND SENT FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND AD	VISE OF ROOT CAUSE ONCE ESTABLISHED.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081112		CE  	2008	11	12	CA080730009      	1	20080424	G	7930		OIL SYSTEM      			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, THE CHIP DETECTOR LIGHT CAME ON ACCOMPANIED BY A RAPID LOSS OF OIL PRESSURE AND RAPID RAISE IN OIL TE	MPERATURE. THE PILOT IMMEDIATELY SHUTDOWN THE ENGINE. ON-GROUND INSP, REVEALED METAL IN OIL FILTER AND ON THE CHIP DETEC	TOR. THE ENGINE WAS REMOVED AND SHIPPED FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT	 CAUSE ONCE ESTABLISHED.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081112		SW  	2008	11	12	CA080731001      	1	20080727	G	3222	55010011	DRAG BRACE      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A DAILY INSP BY MAINT PERSONNEL, THE NR 3 LUG SECURING THE UPLOCK HOOK TORQUE SHAFT TO THE DRAG BRACE WAS F	OUND CRACKED IN HALF AND SEPARATED FROM THE DRAG BRACE.  REPLACED WITH A SERVICEABLE DRAG BRACE, RIGGED AND ADJUSTED WIT	H NO FURTHER ISSUES.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
	20081112		SW  	2008	11	12	CA080731002      	1	20080729	G	6320	212040143001	BEARING         	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					TRANSMISSION	ROUGH           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				875  							(CAN) UPON A SCHEDULED INSPECTION OF THE TRANSMISSION WAFFER FILTER AN EXCESSIVE AMOUNT OF FERROUS METAL WAS FOUND. THER	E HAD BEEN NO METAL FOUND ON THE CHIP DETECTOR OR IN THE COURSE INLET SCREEN. A SWEEP OF THE SUMP WITH A MAGNET FOUND NO	 METAL. AFTER DISSASEMBLY AND INSPECTION OF THE TRANSMISSION, GEARS, AND BEARINGS, THE BEARING SET P/N 212-040-143-001 I	N THE HYDRAULIC PUMP AND TACHOMETER DRIVE ASSEMBLY OFFSET QUILL WAS FOUND TO BE ROUGH.			1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081112		EU  	2008	11	12	CA080801001      	1	20080726	G	2910		FLEX LINE       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	HYD SYSTEM	CHAFED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE CREW OBSERVED A LOSS OF HYDRAULIC PRESS AFTER GEAR WAS SELECTED DOWN. THE ACFT LANDED WITHOUT FUR	THER INCIDENT.  MAINT IDENTIFIED THE HYDRAULIC LINE FROM THE PUMP THE HIGH PRESSURE FILTER AS THE SOURCE OF THE LEAK. TH	E LINE WAS REPLACED AND THE ACFT RETURNED TO SERVICE.				2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
	20081112		EU  	2008	11	12	CA080801002      	1	20080728	G	2460	SM400D30	CONTACT         			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	DC BUSS	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DEPARTING, CREW OBSERVED A NR 1 DC BUSS FAIL INDICATION WITH NO GENERATOR FAULT INDICATION. THE CREW OBSERVED THAT	 THE NR 1 DC BUS WAS RECOVERED WHEN THE NR 1 GENERATOR WAS SELECTED OFF. THE ACFT RETURNED TO POINT OF DEPARTURE WITHOUT	 FURTHER PROBLEM. MAINT REPLACED THE NR 1 GENERATOR CONTACTOR (12PU) AND THE ACFT WAS RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20081112		NE  	2008	11	12	CA080801003      	2	20080728	G	7200		ENGINE          			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  						POWER LOSS      	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE AIRCRAFT WAS IN CRUISE ENROUTE, THE ACFT EXPERIENCED AN UNCOMMANDED POWER LOSS, DECELERATING TO FLIGHT IDLE.	 THE CREW SELECTED NR 2 THRUST TO IDLE AND THE ACFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. T	HE ACFT FERRIED FOR ENGINE REPLACEMENT.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
	20081112		EU  	2008	11	12	CA080801004      	1	20080723	G	5754	A5724853200000	ACCESS PANEL    			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					SLAT TRACK	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ARRIVAL, LEADING EDGE SLAT TRACK ACCESS PANEL 512HB FOUND MISSING. ADJACENT PANEL 512JB ALSO FOUND DAMAGED. LOS	T IN FLIGHT.  PANEL 512HB REPLACED AND PANEL 512JB REPAIRED IAW SRM.					2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20081112		CE  	2008	11	12	CA080801005      	1	20080729	G	2750	C1452501	MOTOR           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TE FLAPS	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			238  	238  							(CAN) AFTER TAKEOFF THE CREW SELECTED FLAP UP AND THE CIRCUIT BREAKER POPPED. AIRCRAFT FLEW TO MAINT BASE WERE THE CREW 	SELECTED PROPER FLAP WITH THE STANBY FLAP SYS AND LANDED WITHOUT INCIDENT.					1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20081112		NE  	2008	11	12	CA080801007      	2	20080801	G	7414		BEARING         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			487  								(CAN) MAG WAS RECEIVED FOR 500 HOUR INSP BEFORE DISASSEMBLY THE ROTOR BEARING END PLAY WAS MEASURED AT 0.003 INCH. THE A	LLOWABLE END PLAY IS 0.0005 TO 0.0015 INCH. WHEN DISASSEMBLED THE COIL WAS FOUND TO BE SLIGHTLY LOOSE IN THE MAG HOUSING	. THE BEARINGS WERE RESHIMMED AND INSPECTED, THE COIL CLAMPS WERE REPLACED AND THE COIL WAS NO LONGER LOOSE IN THE HOUSI	NG. THE REST OF THE 500 HOUR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE.			1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081112		NE  	2008	11	12	CA080801008      	2	20080801	G	7414		COIL            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			487  								(CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. WHEN DISASSEMBLED THE COIL WAS FOUND SLIGHTLY LOOSE IN THE MAG HOUSING. THE CO	IL CLAMPS WERE REPLACED AND THE COIL WAS NO LONGER LOOSE IN THE HOUSING. THE REST OF THE 500 HOUR INSP WAS CARRIED OUT A	ND THE MAG WAS RETURNED TO SERVICE.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081112		EU  	2008	11	12	CA080804001      	1	20080731	G	3340	RG1007AA03	FLASHER         			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					EXTERIOR LIGHT	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPPER SLOWER BEACON AND STROBE LIGHTS INOP. FOUND FLASHER UNIT U/S (RECEPTACLE CONNECTOR BURNED & PARTIALLY MELTED	 INSIDE). CONNECTING ELECTRICAL PLUG INSULATION SLIGHTLY BURNED AND PINS DAMAGED. CONNECTOR P/N E0052R14B15SNE AND TIMER	 UNIT REPLACED. PARTS ROUTED TO ENGINEERING FOR INVESTIGATION.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
	20081112		EU  	2008	11	12	CA080804002      	1	20080801	G	2131		CONTROLLER      			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					CABIN PRESSURE	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CREW DID AN EMERGENCY DESCENT DUE ECAM WARNING EXCESSIVE CABIN ALTITUDE WITH CPC NR 1 FAULT. THE EMERGENCY DESCENT	 STARTED FROM FL320 TO FL090. THE CABIN ALTITUDE REACHED 12000 FT.  DURING THE DESCENT THEY GOT MESSAGE "CABIN PR SAFETY	 VALVE OPEN". DURING TROUBLESHOOTING NR 1 CPC INTERROGATION WAS SHOWING NR 1 DELTAP SYS.  SYS RESET AND ALL INDICATION T	ESTED SERVICEABLE. AFTER RETURN FLIGHT TO BASE, BOTH SAFETY VALVES WERE REPLACED AS PRECAUTIONARY.			1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
	20081112		CE  	2008	11	12	CA080804003      	1	20080718	G	7931		OIL SYSTEM      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT, THE MASTER CAUTION WARNING SYS CAME ON IN CONJUNCTION WITH THE LOW OIL PRESSURE ANNUNCIATOR.	 THE CREW ELECTED TO SHUT THE ENGINE DOWN WHEN THE OIL PRESSURE WAS AT OR BELOW 30 PSI. AN UNEVENTFUL SINGLE ENGINE LAND	ING FOLLOWED. TROUBLESHOOTING COULD NOT IDENTIFY THE PROBLEM AND THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGAT	ION AND REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081113		GL  	2008	11	13	CA080805001      	1	20080707	G	3246		FLOAT           			AMTR  	TUNDRA	TUNDRA      	05607NZ	GL  										LEFT NOSE	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ON RETRACTING LANDING GEAR AFTER TAKEOFF IT WAS NOTICED THAT THE LT NOSE GEAR ONLY PARTIALLY RETRACTED. GEAR WAS C	YCLED 3 TIMES BUT LT NOSE GEAR STAYED IN A SEMI RETRACTED STATE. DECISION WAS MADE TO LAND ON RUNWAY WITH GEAR RETRACTED	 - NO DAMAGE, NO INJURY. INVESTIGATION BY OWNER REVEALED THE ROD WHICH ACTIVATES NOSE GEAR ONLEFT FLOAT BROKE. MONTANA F	LOAT COMPANY, THE MANUFACTURER WILL SUPPLY 2 NEW RODS 7/16" THICK - OLD RODS 3/8" THICK.			1	H	7	1 	3O			NT	EXPA1H71					 
	20081113		EA  	2008	11	13	CA080805002      	2	20080728	G	7313	311991901	SLEEVE          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FUEL NOZZLE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT A SCHEDULED HOT SECTION INSPECTION ON THE ABOVE ENGINE, IT WAS DISCOVERED THAT 2 NOZZLE SHEATHS	 WERE OF AN INCORRECT PART NR FOR THE MODEL OF ENGINE INSTALLED. THE PART NRS ARE BOTH FOR A PT6A-50 ENGINE. EVEN THOUGH	 WE OPERATE THIS MODEL OF ENGINE, OUR INVENTORY RECORDS DO NOT SHOW THIS PART EVER BEING ISSUED TO THIS ACFT. THERE IS A	 POSSIBILITY THAT THESE 2 SHEATHS HAD BEEN INSTALLED AT ENGINE OVERHAUL, T.S.O. 3522 HRS. 2 REPLACEMENT SHEATHS OF THE C	ORRECT PART NR WERE INSTALLED AND THE ENGINE RETURNED TO SERVICE.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
	20081112		SW  	2008	11	12	CA080805003      	1	20080803	G	5302		SKIN            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2798 								(CAN) CRACK FOUND BETWEEN THE TAIL ROTOR SUPPORT AND TAILBOOM AT FUSELAGE STA 375 APPROX. ALSO SEVERAL RIVETS WERE FOUND	 SMOKING. THE HELICOPTER WAS USED TO MOVE DRILL ON A REGULAR BASIS WITHOUT EXCEEDING THE LOAD CAPACITY. TAILBOOM REMOVED	 P/N407-530-014-101 S/N 53037 AND SERVICEABLE TAILBOOM INSTALLED P/N 407-030-801-205D PROCURED FROM MFG.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20081119		NM  	2008	11	19	CA080805005      	1	20080731	G	3231	483025	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG DOOR	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING DEPARTURE, THE LANDING GEAR WAS SELECTED UP, THE RT MLG DOOR WAS SLOW TO CLOSE (APPROX 10 MINUTES). THE F/A	 VERIFIED THE DOOR WAS OPEN. THE DOOR THEN CLOSED WITHOUT ACTION FROM THE PILOT. PSEU FAULT CODE RGDCL UNREASONABLE FAR.	   RT MLG SOLENOID SEQUENCE VALVE REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081119		NM  	2008	11	19	CA080805006      	1	20080801	G	2913	6617303	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYD SYSTEM	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING APPROACH, NR 2 HYD PUMP CAUTION LIGHT ILLUMINATED. PTU WAS SELECTED ON SO ALL SYSTEMS OPERATED NORMAL FOR R	OUTINE LANDING.   EDP CASE HALVES LOOSE AND PUMP NOT MAKING PRESSURE. PUMP REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081119		EA  	2008	11	19	CA080805007      	2	20080801	G	8530	65678	BOLT            	CURTIS      		GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  					EXAUST ROCKER	SHEARED         	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT, THE NR 1 ENGINE LOST POWER AND BEGAN TO BACKFIRE. ENGINE SHUT DOWN AND FEATHERED. UPON INSPECTIO	N OF ENGINE NR 9 CYLINDER EXHAUST ROCKER BOLT FOUND SHEARED AT NUT AND BOLT HAD DISENGAGED FROM CYLINDER EAR ASSEMBLY. N	EW BOLT AND NUT ASSEMBLY INSTALLED, VALVE CLEARENCES ADJUSTED, MAIN OIL SCREEN AND NO CONTAMINATION FOUND. ENGINE GROUND	 RUN SERVICEABLE AND RETURNED TO SERVICE.			2	H	7	2 	4R	4	R		A25WE   	E259				 
	20081119		NE  	2008	11	19	CA080805008      	2	20080805	G	7414	106006169	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			608  								(CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. BEFORE DISASSEMBLY 0.003 INCH END PLAY WAS NOTICED ON THE ROTOR BEARINGS (0.00	15 INCH IS MAX. ALLOWABLE). WHEN DISASSEMBLED THE WASHER THAT RETAINS THE DISTRIBUTOR GEAR ON THE SHAFT WAS SLIGHTLY LOO	SE. MFG HAS BEEN CONTACTED IN THE PAST ABOUT THIS ISSUE AND HAS INSTRUCTED US TO USE A PRESS ON THE END OF THE SHAFT TO 	REFLARE IT TO RETAIN THE WASHER. THE COIL WAS ALSO FOUND MOVING SLIGHTLY AGAINST THE HOUSING POLES AND WHEN THE COIL CLA	MP SCREWS WERE REMOVED TO INSPECT THIS THE SCREWS WERE FOUND TO BE NOT VERY TIGHT. THE ROTOR BEARINGS WERE RESHIMMED, TH	E DIST. GEAR SHAFT WAS REFLARED, AND THE COIL CLAMP SCREWS WERE TIGHTENED. THE REST OF THE 500 HOUR INSP. WAS CARRIED OU	1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081119		NE  	2008	11	19	CA080805009      	2	20080805	G	7414	10160858	HOUSING         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			608  								(CAN) MAG WAS RECEIVED FOR 500 HOUR INSP. A CRACK WAS NOTICED IN ONE OF THE MOUNTING EARS OF THE MAG HSG. THIS IS A NEW 	STYLE OF HSG CASTING FROM MFG WITH THE LARGE RAISED LETTERS ON THE OUTSIDE OF THE HSG AND THE WORD "EMPIRE" INSIDE THE H	SG NEXT TO THE BRG AREA. WE HAVE NOTICED A HIGHER NR OF THESE NEW STYLE HSGS CRACKING AT THIS LOCATION. OLDER CASTINGS W	OULD OCCASIONALLY CRACK IF THE MOUNTING NUTS WERE OVERTORQUED, WHEREAS THESE NEW ONES SEEM TO BE WEAKER AND CRACK MORE O	FTEN. THE MAG WAS REMOVED FROM SERVICE.		1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081119		NM  	2008	11	19	CA080805010      	1	20080802	G	3060		HEATER          	HAMSTD      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROP BLADE	BURNED          	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA			10316	10316							(CAN) THE CREW OBSERVED SPARKS COMING FROM THE FRONT OF THE RT ENGINE. THE CREW SHUTDOWN THE ENGINE IN FLIGHT AND DECLAR	ED AN EMERGENCY. THE ACFT LANDED SHORTLY AFTER WITHOUT INCIDENT. INVESTIGATION REVEALED THAT THE RT PROPELLER BLADE NR2 	ELECTRICAL HEATER BURNED CAUSING THE HEATING ELEMENT TO PRODUCE ELECTRICAL SPARKS. THE BLADE ASSY WAS REPLACED, THE BLAD	E ANTI-ICING SYS TESTED AND THE ACFT RETURNED INTO SERVICE. THE BLADE WAS SENT TO AN EXTERNAL SHOP FOR REPAIR.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081119		GL  	2008	11	19	CA080805011      	2	20080801	G	7230	3896888M	SCROLL          			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21976								(CAN) WHILE CARRYING OUT A DAILY CHECK, A CRACK WAS FOUND ON THE COMPRESSOR SCROLL ON TOP, PARALLEL TO SHROUD HSG AND NE	AR THE RT ELBOW. ACFT WAS GROUNDED. COMPRESSOR ASSY IS AN ON-CONDITION ITEM BUT THERE IS AN INSP EVERY 2000 HOURS. AS YO	U CAN SEE THIS SCROLL WAS VERY HIGH TIME. SINCE LAST 2000 HOUR INSP 374.8 HOURS.  TO THE 2000 HR INSP INVOLVES INSPECTIN	G THE SPUR ADAPTER GEAR AND ITS MATING GEAR. BELIEVE THAT THE SCROLL IS THE SAME TIME AS THE COMPRESSOR ASSY.			1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081117		CE  	2008	11	17	CA080805012      	1	20080730	G	3234	1013841377	SELECTOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  					LANDING GEAR	DEFECTIVE       	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) UPON APPROACH THE CREW WAS UNABLE TO EXTEND THE GEAR NORMALLY AND HAD TO PERFORM AN EMERGENCY EXTENSION. A SUCCESS	FUL LANDING WAS CARRIED. UPON INVESTIGATION, IT WAS DETERMINED THE PROBLEM WAS IN THE LANDING GEAR SELECTOR ASSY. THE PI	VOT SCREW FOR THE MICROSWITCH ACTUATING LEVER HAD BACKED OUT SEVERAL THREADS. THIS ALLOWED THE LEVER TO MIGRATE OUT WITH	 THE SCREW. WHEN THE GEAR WAS SELECTED UP THE ACTUATING LEVER CAME TO REST ON PART OF THE GEAR SELECTOR HSG. AS SUCH, WH	EN THE CREW SELECTED GEAR DOWN THE SWITCHES WERE NOT RELEASED AND THE GEAR REMAINED IN THE RETRACTED POSITION. THREAD LO	CKING COMPOUND WAS APPLIED TO THE PIVOT SCREW AND THE SCREW WAS TIGHTENED. SEVERAL GEAR SWINGS WERE SUCCESSFULLY COMPLET	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081117			2008	11	17	CA080805013      	4	20080805	G	6113	35323012	BULKHEAD        			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSP FWD SPINNER BULKHEAD WAS FOUND TO BE CRACKED AT SCREW ATTACHMENT HOLE.  NEW PART WAS ORDERED FR	OM MFG IAW APPLICABLE PARTS CATALOGUE.  NEW PART RECEIVED WAS STAMPED WITH CORRECT PN AS ORDERED, BUT WAS PHYSICALLY DIF	FERENT IN DEPTH AND WOULD NOT FIT.   MFG WAS CONTACTED (VIA AVIATION UNLIMITED AND A SECOND SPINNER BACK PLATE IS BEING 	SHIPPED).			1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
	20081117		SO  	2008	11	17	CA080805014      	2	20080709	G	8530		CAMSHAFT        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSP , NR2 CYL WAS REMOVED DUE TO LOW COMPRESSION. DISCOVERED LIFTERS ON NR1 CYL HAD PITTING AND SPALLING. 	FURTHER INVESTIGATION REVEALED THE CAMSHAFT WAS CORRODED AND WORN ALSO. ENGINE REMOVED FOR REPAIR. ENGINE HAS 670 HOUR T	SOH. UPON TEARDOWN, CRANKSHAFT HAD CORROSION, AND THE OIL PUMP WAS DAMAGED DUE TO METAL CONTAMINATION IN ENGINE, AND MOR	E LIFTERS HAD DAMAGE. THE ACFT HAS ALWAYS BEEN HANGERED, OUT OF THE COLD. WHEN IT WAS OUT IN THE COLD, A PREHEAT SYS WAS	 UTILIZED. ACFT FLEW ON THE AVERAGE 3 TO 4 HOURS PER WEEK WITH APPROX 2 HOUR DURATION PER FLIGHT. CANNOT DETERMINE WHAT 	THE CAUSE OF THE CORROSION IS WHICH CAUSED THE METAL CONTAMINATION.	1	H	7	1 	3O	3	O		3A24    	E3SO	5	C	P47GL	 
	20081117		NE  	2008	11	17	CA080806001      	2	20080723	G	7321		FUEL CONTROL    			BEECH 	200   	200CBEECH   	1152926	CE  	PWA   	PT6   	PT642A      		NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) DURING LANDING, THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION WHICH CAUSED THE PILOT TO HAVE DIFFICULTY CONTR	OLLING THE ACFT, CAUSING IT TO SKID IN THE GRASS AND MUD AT THE SIDE OF THE RUNWAY. THE FUEL CONTROL WAS REPLACED AND TH	E RIGGING WAS ADJUSTED. THE FUEL CONTROL WILL BE INVESTIGATED AND UPDATES PROVIDED.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081117			2008	11	17	CA080806002      	4	20080729	G	3160	8221577012	DISPLAY         			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					COCKPIT	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REPORTED, DURING PREFLIGHT. THEY STARTED THE APU. AFTERWARDS, PILOT SELECTED THE AIR SOURCE TO (NORMAL) THEN	 SMOKE BEGAN EMITTING FROM THE RT SIDE OF THE COCKPIT BETWEEN THE GLARESHIELD AND WINDOW. PILOT SELECTED THE AIR SOURCE 	TO (OFF) THEN SHUTDOWN THE APU. FOUND COPILOT`S MFD AS THE SOURCE OF THE SMOKE.  REMOVED AND REPLACED COPILOT`S MFD. OPS	 GOOD. EXTENSIVE GROUND TESTING INCLUDING OPS OR AIR COND SYS WAS CARRIED OUT AND ALL WAS FOUND TO BE NORMAL.			2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
	20081117		EA  	2008	11	17	CA080806003      	2	20080726	G	7260		GEARBOX         			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	DISCONNECTED    	W				O				OTHER                   				X			ENGINE FLAMEOUT           			AP	APPROACH       	1			CA											(CAN) DURING FINAL APPROACH, THE ENGINE FLAMED OUT. RELIGHT ATTEMPT WAS UNSUCCESSFUL. AN UNEVENTFUL SINGLE ENGINE LANDIN	G FOLLOWED. POST EVENT TROUBLESHOOTING, FOUND THAT THE ENGINE COULD NOT BE RE-STARTED. ACCESSORIES GEARBOX DE-COUPLE IS 	CONFIRMED. THE AFFECTED COMPONENTS WILL BE REMOVED AND FWDED FOR INVESTIGATION.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20081117		NE  	2008	11	17	CA080806004      	2	20080729	G	7200		ENGINE          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING T/O, THE ENGINE STARTED TO SURGE FOLLOWED BY A RISE IN INDICATED TEMPERATURE. THE PILOT ELECTED TO RETURN T	O HIS POINT OF DEPARTURE, WHERE A SAFE LANDING WAS PERFORMED. THE ENGINE TEMP REACHED 970C FOR ONE MINUTE. THE ENGINE W	ILL BE REMOVED AND FWDED FOR INVESTIGATION AND REPAIR.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
	20081117		CE  	2008	11	17	CA080806005      	1	20080801	G	8120		TURBOCHARGER    			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  	LT ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) PILOT REPORTED LOW MANIFOLD PRESSURE ON LT ENG IN CLIMB OUT, ACFT RETURNED TO THE AIRPORT. MAINT BACK FLUSHED THE 	LT TURBO WASTEGATE AND CONTROLLER, GROUND RUN OK. NO OTHER DEFECTS NOTED, ACFT RETURNED TO SERVICE.					1	L	7	2 	3O	3	O		A12CE   	E10EA	5	C	P31EA	 
	20081117		EA  	2008	11	17	CA080806006      	1	20080804	G	7110		COWLING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NR 2 ENGINE	DEPARTED        	W				K				NONE                    				P			NO WARNING INDICATION     			TX	TAXI/GRND HDL  	1			CA											(CAN) AS INDICATED BY MAINT CONTROL, ACFT DEPARTED. MISSING COWLING FROM NR2 ENGINE WAS DISCOVERED DURING WALKAROUND INS	P BY GROUND MAINT. IT WAS ALSO APPARENT THAT PORTIONS OF THE COWLING THAT DEPARTED ENGINE, STRUCK THE LEADING EDGES OF T	HE LT AND RT HORIZONTAL STAB.  CREW DID NOT HAVE ANY ABNORMAL INDICATIONS DURING FLIGHT, IAW MAINT CONTROL COMMENT TO FS	R. PLEASE REFER TO ADR RRAD-C08-21754681.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081117		NE  	2008	11	17	CA080806007      	2	20080805	G	7260		GEARBOX         			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF348E5A1   	30062	NE  					NR 1 ENGINE	DEFECTIVE       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, CREW NOTICED THEY LOST THE NR1 ENGINE OIL INDICATION AND GOT THE RED LED.  SHUTDOWN ENGINE AND MADE	 AN UNEVENTFUL LANDING. CREW NOTICED A PUDDLE OF OIL UNDER THE NR1 ENGINE AFTER LANDING.  DURING THE TROUBLESHOOTING, TH	EY REMOVED THE DRAIN MAST AND INSTALL PLASTIC BAG TO THE DIFFERENT DRAIN LINES. AFTER STARTING THE ENGINE, THE PLASTIC B	AG FOR THE ACCESSORY GEAR BOX DRAIN WAS FULL OF OIL.  SHUTDOWN THE ENGINE, THEY ARE NOW WAITING FOR THE MRP TO CHANGE TH	E AGB.		2	L	7	2 	4F	4	F	RT	A21AE   	E00063EN				 
	20081117		NM  	2008	11	17	CA080806008      	1	20080730	G	2133	88060B010003	OUTFLOW VALVE   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	CABIN PRESSURE	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ACFT RETURNED DUE TO DEPRESSURIZATION AND BURNING ODOR IN THE COCKPIT. ATC CALLED LOCAL STANDBY, NO PAN/MAYDAY DEC	LARED. ACFT LANDED SAFELY AND WITHOUT INCIDENT.   MAINT INTEROGATEED THE CDS, THE FOLLOWING CODES IDENTIFIED: AFT OUTFLO	W VALVE FAIL CPC/OFF VALVE DATA FAIL.  AFT OUTFLOW VALVE REPLACED. FUNCTION CHECKS OF ECS SYSTEM CARRIED OUT COULD NOT I	DENTIFY ANY ODORS. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081117		EA  	2008	11	17	CA080806009      	1	20080718	G	2730	C6CTM102827	DRIVE ASSY      	DHAV        	C6CT10103   	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ELEVATOR	STRIPPED        	W				A				UNSCHED LANDING         				Z	E		SIGNIFICANT FAILURE REPORT	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT AT 800 FEET ALTITUDE THE ACFT SUDDENLY STARTED TO SHAKE VIOLENTLY. THE PILOT ABORTED THE CLIMB, P	ROCEEDED STRAIGHT AHEAD FOR 4 MILES TO A LANDING STRIP AND LANDED SAFELY WITH NO INJURIES TO PERSONS ON BOARD. UPON INVE	STIGATION AS TO THE CAUSE OF THE SHAKING IT WAS DISCOVERED THAT THE CLEVIS END P/N C4CM1956-11 HAD PULLED COMPLETELY OUT	 OF THE SCREW DRIVE P/N C6CTM1028-27 IN THE ELEVATOR SCREW JACK ASSY P/N C6CT1010-3. THIS ALLOWED THE TRIM TAP TO FLUTTE	R WHICH IN TURN CAUSED THE ELEVATOR TO FLUTTER INDUCING A VIOLENT SHAKING OF THE ACFT.		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
	20081117		EA  	2008	11	17	CA080806010      	1	20080705	G	7603	74491147	CABLE ASSY      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					THROTLE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			18500								(CAN) WHILE ATTEMPTING TO REDUCE RT ENGINE PWR AFTER TAKEOFF AND CLIMB, FLT CREW REPORTED THAT THE RT ENG WOULD NOT RESP	OND TO THROTTLE LEVER INPUTS. THE RT ENGT WAS SHUTDOWN VIA FIRE PUSH SWITCH/LIGHT, ACFT DIVERTED TO IAD AND LANDED WITHO	UT FURTHER INCIDENT.   PRIOR TO TAKEOFF (ON TAXI OUT), THE FLT CREW NOTICED THAT THE RT THROTTLE LEVER WAS VERY STIFF TH	AT THEY ATTRIBUTED TO FRICTION LOCKS. UPON ADDING POWER FOR TAKEOFF, THEY NOTICED THAT THE THROTTLE LEVERS WERE VERY STI	FF AT FIRST, THEN THERE WAS A DEFINITE "POP" AND THEN THE LEVERS ADVANCED EASILY TO THE FLEX THRUST SETTING (87 PERCENT)	. THE REMAINDER OF THE TAKEOFF WAS NORMAL. WHEN ADVANCING PWR LEVERS TO CLIMB THRUST (92 PERCENT N1), BOTH ENGINES RESPO	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081117		CE  	2008	11	17	CA080806011      	1	20080716	G	2550	D2010103	ARM             	DART        	D500560041  	DART  	G     	G           	2700102	CE  										CARGO BAY	CRACKED         	W				O				OTHER                   				O			OTHER                     			UK	UNKNOWN        	1			CA											(CAN) MFG HAS RECEIVED A REPORT THAT UNDER CERTAIN CIRCUMSTANCES ON THE D500-560-041 CARGO MIRROR INSTALLATION AT CHG001	 THE D2010-103 ARM MAY CRACK DURING FLIGHT CAUSING THE D2011-101 MIRROR TO SEPARATE FROM THE ASSY. SB08-3 IS BEING ISSUE	D TO ALL CUSTOMERS WHO HAVE PURCHASED ASSEMBLIES.				1	L	7	1 	3R				TC674   					 
	20081117		EA  	2008	11	17	CA080806012      	2	20080801	G	8530	SL360000WA20P	CYLINDER HEAD   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			1854 								(CAN) DURING CLIMB OUT WITH GLIDER IN TOW, THE PILOT REPORTED AN ENGINE VIBRATION. THEY IMMEDIATELY INSTRUCTED THE GLIDE	R TO RELEASE AND THEN PREFORMED A DOWN WIND LANDING AND RETURN TO HANGER. UPON SHUTDOWN AND INSP IT WAS FOUND THAT CYL N	R1 HEAD HAD CRACKED AND SEPARATED FROM THE REMAINDER OF THE CYL.				1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
	20081117		SW  	2008	11	17	CA080806013      	1	20080728	G	3244	280250	TIRE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TAIL WHEEL	DAMAGED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			125  								(CAN) TAIL WHEEL FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND CUT TH	E TUBE. TIRE, BATCH NR WAS EITHER 0321672 OR 0422043.					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
	20081117		SW  	2008	11	17	CA080806014      	1	20080727	G	3244	280250	TIRE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TAIL WHEEL	DAMAGED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			124  								(CAN) TAIL WHEEL FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND CUT TH	E TUBE. TIRE, BATCH NR WAS EITHER 0321672 OR 0422043.					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
	20081117		SW  	2008	11	17	CA080806015      	1	20080728	G	3244	280250	TIRE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TAIL WHEEL	DAMAGED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			160  								(CAN) TAIL WHEEL TIRE FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND C	UT THE TUBE.					1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
	20081117		SW  	2008	11	17	CA080806016      	1	20080625	G	5711	31692	SPAR            			BBAVIA	8     	8GCBC       	1220803	SW  										WING	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			976  								(CAN) PART FOUND CORRODED AT SPAR ATTACHMENT BOLT HOLE.						1	H	7	1 	3O				A21CE   					 
	20081117		SW  	2008	11	17	CA080806017      	1	20080625	G	5711	31692	SPAR            			BBAVIA	8     	8GCBC       	1220803	SW  										WING	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			976  								(CAN) PART FOUND CORODED AT SPAR ATTACHMENT BOLT HOLE.						1	H	7	1 	3O				A21CE   					 
	20081117		NM  	2008	11	17	CA080807001      	1	20080729	G	2520	5045802158003	SEAT BELT       			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					CABIN	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3059 								(CAN) F/A SEAT LAP BELTS AT DOOR LT NR1 AND DOOR RT NR2 FRAYED SEVERAL PLACES.						2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081117		NM  	2008	11	17	CA080807002      	1	20080806	G	2520	5045802158003	SEAT BELT       		5045804078  	EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					CABIN	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5704 								(CAN) F/A SEAT LAP BELT AT DOOR LT NR1, NR2 AND DOOR RT NT2 FRAYED SEVERAL PLACES.						2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081119		NE  	2008	11	19	CA080807003      	3	20080718	G	6110	7149A0	THRUST WASHER   	HAMSTD      												HAMSTD	23E	23E50       	NE  	BLADE SHANK	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				471  							(CAN) THE CRACKED BLADE RING IS PART OF THE BLADE ASSEMBLY. A CRACKED RING TYPICALLY RESTRICTS BLADE ROTATION AND CAN SE	T UP A VIBRATION. PROPELLER WAS REMOVED AND AFTER TEAR DOWN AND INSPECTION A CRACKED BLADE RING (THRUST WASHER) WAS DETE	RMINED AND OTHER DAMAGE TO THE BARREL ASSEMBLY. REPLACED BLADE THAT HAD THE BROKEN BLADE RING AND OTHER DAMAGED PARTS. P	ROPELLER ASSEMBLED BALANCED AND RETURNED TO SERVICE.													6	C	P603	 
	20081119		NM  	2008	11	19	CA080807004      	1	20080806	G	2761		HOUSING         	SMITHSIND   		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ACTUATOR	FRACTURED       	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			44413								(CAN) WHEN THE FLIGHT/TAXI SWITCH WAS SELECTED TO FLIGHT IN PREPARATION FOR TAKE OFF, THE CREW RECEIVED SOME HYDRAULIC C	AUTION LIGHTS ASSOCIATED WITH A LOW HYDRAULIC LEVEL INDICATION ON THE NR 1 SYSTEM . THE ACFT RETURNED TO THE GATE AND A 	MAJOR HYDRAULIC LEAK WAS OBSERVED AT THE RT WING. MX FOUND THE INBD FLIGHT SPOILER ACTUATOR CASING CRACKED. THE ACTUATOR	 WAS REPLACED, LEAK CHECKED, TESTED AND THE ACFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081117		EA  	2008	11	17	CA080807005      	1	20080807	G	5520	C6TEM101229	HINGE FITTING   			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ELEVATOR	MISMANUFACTURED 	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) THE HINGE ARM ASSY WAS RECEIVED FROM THE OEM WITH THE BONDING STRAP AND TAB INSTALLED ON THE UPPER ARM OF THE ASSY	 WHICH IF INSTALLED WOULD RESTRICT TRAVEL OF THE ELEVATOR. THE BONDING STRAP IS A FIXED LENGTH AND RIVETED IN PLACE. ADD	ITIONALLY TO MAKE THE TAB BOND PROPERLY TO THE ARM PAINT WAS REMOVED FROM THE ASSY AND NOT REFINISHED. THE AREA THIS PAR	T IS INSTALLED IN IS EXPOSED TO THE ENGINE GAS PATH THEREBY MAKING IT A HIGH CORROSION AREA. ALSO UPON FURTHER EXAMINATI	ON THE BONDING TAB WAS FOUND LOOSE DUE TO THE COUNTER SINK(S) SIZE. THIS PART HAS BEEN SENT BACK TO THE OEM FOR REPLACEM	ENT.	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
	20081117		EU  	2008	11	17	CA080807006      	1	20080701	G	7160	1350P5103	SEAL            			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101750A1 	41560	NE  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				X			ENGINE FLAMEOUT           			IN	INSP/MAINT     	1			CA											(CAN) CONVERTED LAST FEB, AT THE SAME TIME INSTALLED AN FDC ENGINE AIR FILTER. JULY 1ST 2008 THE PILOT WAS STARTING THE 	ENGINE GOT TO AROUND 60 PERCENT TORQUE WHEN COMPRESSOR STALLS OCCURRED. HE SHUTDOWN. UPON INSP FOR COMPRESSOR STALLS IT 	WAS FOUND THE COMPRESSOR WAS FOD.  FOUND THAT A PIECE OF THE SEAL P/N 1350P5-103 HAD COME OFF AND FOD THE ENGINE.				1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
	20081117			2008	11	17	CA080807007      	4	20080805	G	6113	C4383	SUPPORT         			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	SPINNER	BROKEN          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA			215  								(CAN) PLASTIC SPINNER SUPPORT CRACKS AND BREAKS INSIDE SPINNER CAUSING VIBRATION, SEEMS PLASTIC IS SOFTER DURING THE HOT	 SUMMER MONTHS AND FLEXES MORE.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
	20081117		EU  	2008	11	17	CA080808001      	1	20080807	G	3233	A5341130500200	ATTACH FITTING  			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					NLG ACTUATOR	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON LDG GEAR UP SELECTION NOSE GEAR SHOWED UNSAFE DOOR NOT UP. ECAM/QRH CARRIED OUT.  ACFT RETURNED TO THE STATION.	  FOUND NLG UP LOCK ACTUATOR ATTACHMENT FITTING ASSY P/N A5341130500200 WITH BROKEN LUGS. NEW ATTACHMENT FITTING INSTALL	ED.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20081117		CE  	2008	11	17	CA080808002      	1	20080731	G	8011	534685	BEARING         	CONT        	643259A18   	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	STARTER	WORN            	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ACFT WAS IN CRUISE FLIGHT WHEN PILOT NOTICED OIL PRESSURE STARTED TO FLUCTUATE. A PRECAUTIONARY LANDING WAS MADE. 	IT WAS OBSERVED THAT THE OIL LEVEL WAS LOW AND AN EXCESSIVE AMOUNT OF OIL WAS IN THE ENGINE COMPARTMENT AND IN THE BELLY	 OF THE ACFT. UPON MAINT INSP, IT WAS FOUND THAT THE STARTER ADAPTER PULLEY BEARING WAS BADLY WORN, DAMAGING THE OIL SEA	L ALLOWING FOR AN OIL LEAK. THE STARTER ADAPTER WAS REPLACED, OIL FILTER CHECKED FOR FOREIGN MATERIAL, OIL REPLENISHED, 	AND A LEAK CHECK WAS CARRIED OUT. THE AIRCRAFT WAS RETURNED TO SERVICE.		1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
	20081119			2008	11	19	CA080808004      	1	20080722	G	2910	25W711008171	LINE            								GARRTT	TFE731	TFE73140    	29001	NE  					HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			1219 								(CAN) ON APPROACH INTO TORONTO PEARSON THE CREW NOTICED THAT THE AUX HYDRAULIC LOW PRESSURE ANNUNCIATOR AND FLUID LOW LE	VEL LIGHT ILLUMINATED ON THE ACFT. AFTER STABILIZING THEIR APPROACH, ALL LIGHTS WENT OUT. AFTER LANDING THE LOW LEVEL LI	GHT CAME ON ONCE AGAIN WITH NO FURTHER LOW AUX HYD PRESSURE NOTED. AN INVESTIGATION FOUND THE RESERVOIR TANK LOW AND THE	 LINE FROM THE AUX PUMP AREA TO THE HYDRAULIC FILTER HAD A VERY FINE CRACK THAT HAD ORIGINATED ALONG A TOOLING MARK, THA	T WAS ONLY VISIBLE WHEN RUNNING AND UNDER A 10 POWER MAGNIFYING GLASS. THE LINE WAS REPLACED AND RESERVOIR SERVICED WITH	 NO FURTHER PROBLEMS.						4	F			E1NM				 
	20081117		WP  	2008	11	17	CA080808005      	2	20080805	G	7321		VALVE           	WOODWARD    		SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FUEL CONTROL	INOPERATIVE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA				1162 							(CAN) CREW REPORTED MINOR ISSUE WITH STIFF POWER LEVER ON ONE ENGINE. MAINT EXAMINED THE CONTROL LINKAGE AND FOUND THAT 	THE FUEL CONTROL`S MANUAL FUEL VALVE (MFV) WOULD NOT REACH FULL TRAVEL (APPROX 85 PERCENT OF TRAVEL)  REMOVED THE UNIT F	OR REPAIR.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
	20081117		SO  	2008	11	17	CA080811001      	1	20080729	G	2434	2CM353C1H	ALTERNATOR      			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON DESCENT, CREW OBSERVED THE NR 2 GENERATOR FAIL WAS ILLUMINATED. THE NR2 ENGINE WAS SHUTDOWN AND THE ACFT RETURN	ED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER PROBLEM. MAINT REPLACED THE NR2 GENERATOR AND THE ACFT WAS RETURNED 	TO SERVICE.				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
	20081117		NE  	2008	11	17	CA080811002      	2	20080806	G	8530		CYLINDER        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	NR 1 ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				Z			SIGNIFICANT FAILURE REPORT			CR	CRUISE         	1			CA											(CAN) NR 1 ENGINE BACKFIRED IN FLIGHT.  ENGINE WAS SHUTDOWN AND PROP FEATHERED.  NR 2 CYLINDER EXHAUST EAR WAS FOUND CRA	CKED.  CYLINDER WAS REPLACED AND ENGINE GROUND RUNS SERVICEABLE.					2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
	20081117		NM  	2008	11	17	CA080811003      	1	20080810	G	3242	214664	BRAKE ASSY      		214664      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				986  							(CAN) WHILE THE ACFT WAS BEING TOWED OFF THE RAMP A STRANGE NOISE WAS HEARD IN THE RT WHEEL AREA.  UPON INVESTIGATION IT	 WAS FOUND THAT 3 OF THE 6 TORQUE PLATE TO PISTON HSG RETAINING BOLTS ON THE RT INBD BRAKE UNIT HAD SHEARED. NO OTHER DA	MAGE WAS NOTICED. THE BRAKE UNIT WAS REPLACED WITH A SERVICEABLE UNIT AND THE ACFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081117		SW  	2008	11	17	CA080811004      	1	20080808	G	2910	205076302001	TUNING UNIT     			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					HYDRAULIC SYS	CRACKED         	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			K	F		FLUID LOSS                	FLT CONT AFFECTED         		CR	CRUISE         	1			CA			13967								(CAN) TUBE ASSY WAS REPLACED EARLIER IN APRIL 2008 DURING WINTER MAINT. SINCE SINGLE HYDR SYS PARTS ARE HARD TO FIND ITE	MS, SERVICEABLE PART WAS INSTALLED WITH APPROPRIATE CERTIFICATION. VISUAL INSP DIDN`T REVEALED ANY DAMAGE AND NO LEAK WA	S NOTICED AT THIS TIME. PART HAD 79 HRS SINCE INSTALLATION WHEN FAILED.				1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081119		SW  	2008	11	19	CA080811006      	1	20080807	G	7603	2761000009	ROD END         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					RT POWER LEVER	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE FUEL CONTROL WAS BEING REPLACED ON THE RT ENGINE. WHEN THE STARTER GENERATOR WAS REMOVED IT WAS APPARENT THAT 	THE POWER LEVER, WHERE IT ATTACHES TO THE PROP PITCH CONTROL BY A ROD END, WAS SEVERELY WORN. THE TIME SINCE INSTALL IS 	NOT KNOWN, HOWEVER THE ROD END DID NOT LOOK PARTICULARLY OLD. THE CAD PLATING WAS STILL ON THE PART. IT HAD BEEN APPROX 	80-90 HOURS SINCE THE LAST SCHEDULED INSPECTION. THIS IS THE THIRD INSTANCE IN RECENT MONTHS WITH THE SAME PART NR ROD E	ND. (SOME WORSE THAN OTHERS) THE PART APPEARS TO BE FINE AT INSPECTION THEN FAILS SUDDENLY. AT A CERTAIN POINT IN THE LA	ST FEW YEARS THE PART CHANGED, THE NR IS THE SAME BUT THE PART WAS PHYSICALLY DIFFERENT. THE NEWER ONES ARE THE PROBLEM 	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20081118		EA  	2008	11	18	CA080811007      	2	20080807	G	7322	383493	PLUG            		25245009    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SERVO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE ACCOMPLISHING REPETITIVE INSP (50HR) FOR AD2008-08-14, FOUND BOTH ENGINE FUEL SERVO PLUGS LOOSE. BOTH PLUGS 	REMOVED, INSPECTED, RETORQUED AND SAFETIED IAW AD REQUIREMENTS. NO ENGINE PERFORMANCE SNAGS REPORTED. LT ENGINE: TIO-540	-J2BD S/N: L6203-61A, SERVO P/N: 2524500-9 S/N: 83731, TSO: 345.5 HRS RT ENGINE: LTIO-540-J2BD S/N: L2363-68A, SERVO P/N	 2524500-9 S/N: 52869, TSO: 345.5 HRS.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081117		CE  	2008	11	17	CA080812001      	1	20080716	G	3340	S21601	SWITCH          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					STROBE LIGHT	FAULTY          	W				A				UNSCHED LANDING         				B	B		SMOKE/FUMES/ODORS/SPARKS  	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) ON JULY 16, 2008 AT APPROX. 13:00, PILOT REPORTED SMOKE IN COCKPIT AND PLASTIC BURNING SMELL. ACFT ELECTRONICS WER	E SHUTDOWN AND SMOKE DISSIPATED.  DURING POST FLIGHT INSP, MAINT DISCOVERED A FAULTY STROBE LIGHT SWITCH, AND REPLACED T	HE DEFECTIVE SWITCH. ACFT SYS TESTED WITH NO FURTHER DEFECTS FOUND.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081117		CE  	2008	11	17	CA080812002      	1	20080808	G	3252	22430211	CLEVIS          	CESSNA      	24421141    	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	SHIMMY DAMPER	BROKEN          	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			9102 								(CAN) DAMPER SHAFT CLEVIS BROKE AT NOSE STRUT ATTACHMENT ALLOWING UNRESTRAINED MOTION OF SHIMMY DAMPER.						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
	20081117		EA  	2008	11	17	CA080812003      	2	20080808	G	8530	LW13623	PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	DAMAGED         	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA			244  								(CAN) TOP COMPRESSION RING BROKEN, OIL RING SEIZED, PISTON BURNED FROM BLOWBY, CONNECTING ROD UPPER BRG LOOSE, BRG BORE 	OUTSIDE SERVICE LIMITS.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081124		NE  	2008	11	24	CA080812004      	2	20080721	G	7261	MS920807	BOLT            			DHAV  	DHC8  	DHC8314     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE OIL LINE	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, THE NR 1 ENGINE LOST OIL PRESSURE AND WAS SUBSEQUENTLY SHUTDOWN. THE ACFT RETURNED TO THE A	IRPORT FOR AN APPROACH, HOWEVER, THE VISIBILITY WAS TOO LOW, A MISSED APPROACH WAS EXECUTED FOLLOWED BY A NR OF HOLDS UN	TIL THE WEATHER WAS APPROPRIATE TO TRY A SECOND APPROACH. THE ACFT LANDED SAFELY AFTER A SECOND APPROACH. FURTHER INSPEC	TION FOUND THE OIL LINE FLANGE BOLTS LOOSE ON THE NR 1 ENGINE, ALLOWING ALL THE OIL TO BE PUMPED OUT OF THE ENGINE. THES	E BOLTS ARE NOT DRILLED AND THEREFORE CANNOT BE SAFETY WIRED. PRATT SB 21178 REPLACES THE INSERTS WITH SELF LOCKING INSE	RTS. THE BOLTS WERE RETORQUED, OIL REPLENISHED AND THE ACFT WAS RETURNED TO SERVICE.	2	H	7	2 	4T	4	T	RT	        	E20NE	6	C	P7NE	 
	20081117		NE  	2008	11	17	CA080812005      	2	20080803	G	8530	71167	EXHAUST VALVE   	PWA         	399359      	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	CYLINDER	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			6862 	1070 							(CAN) EXHAUST VALVE BROKE IN CRUISE FLIGHT 15 MIN AFTER DEPARTURE. PARTIAL POWER LOSS - ENGINE VIBRATION. PRECAUTIONARY 	LANDING EXECUTED.  SERVICEABLE CYL COMPLETE INSTALLED AFTER LOCATING THE DEFECT/FAILURE. ACFT RETURNED TO SERVICE.					1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
	20081119		SW  	2008	11	19	CA080813002      	1	20080813	G	6410	206011809109	PITCH HORN      			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					TAIL ROTOR	LOOSE           	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) THE STUD WHICH HOLDS THE PITCH LINKS ONTO THE PITCH HORN CAME LOOSE. THIS CAUSED A VIBRATION FELT IN THE PEDALS. T	HE TAILROTOR HUB WAS 2400 HOURS TSO AND BLADES WERE 2300 TSN. THERE IS NO REQUIREMENT TO OVERHAUL THE PITCH HORNS SO NO 	RECORD AS TO TOTAL TIME SINCE NEW ON THE PITCH HORNS. IF LEFT UNATTENDED THIS MAY HAVE CAUSED FURTHER FLIGHT SAFETY AND 	UNCONTROL OF THE TAIL ROTOR.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081117		EA  	2008	11	17	CA080813003      	1	20080812	G	2910	AE4760H0592055	HYDRAULIC LINE  			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A2     	30067	NE  					HYDRAULIC SYS	BURST           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			4785 								(CAN) IN FLIGHT NR 2 HYDR "LO PRESS" CAME ON, FWD BY "LO LEVEL".  NR 2 HYDR FLUID COMPLETLY LOST THROUGH A BURST HYDR PR	ESSURE HOSE IN RT NACELLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081117		CE  	2008	11	17	CA080813004      	1	20080806	G	3250	55656195	ARM             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NLG STEERING	DAMAGED         	W				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			CA			6500 								(CAN) CAMPAIGN NOTICE 851-53-11-047 WAS BEING ACCOMPLISHED WHEN DAMAGE TO THE NOSE GEAR STEERING ARM WAS DISCOVERED. THE	 FWD ATTACHMENT HARDWARE REMOVED FROM THE CHANNEL-TRUNION BRACE WAS FOUND TO BE MS27039-1-10 AND AN960-3 WASHERS, WHEN M	S27039-1-07 AND NIL WASHERS ARE CALLED FOR IN THE MFG IPC. THE LENGTH OF THE INSTALLED SCREWS WERE SUCH THAT WHEN FULL N	OSE WHEEL DEFLECTION WAS ACHIEVED THERE WAS INTERFERENCE BETWEEN THE SCREW AND THE STEERING ARM CAUSING THE DAMAGE.  STE	ERING ARM P/N 5565619-5 REPAIRED IAW ASEO 851-32-50-0212 BLEND REPAIR.  CORRECT HARDWARE (MS27039-1-07 SCREWS AND MS2104	2-3 NUTS) INSTALLED ON CHANNEL-TRUNION BRACE.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081117		EA  	2008	11	17	CA080813005      	1	20080812	G	2751	756158	TORQUE SENSOR   			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	TE FLAP	INOPERATIVE     	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) FLAP DRIVE CAUTION LIGHT IN CRUISE. ELECTED TO RETURN A/C TO DEPARTURE FOR REPAIR.  CONFIRMED FAULT TO TORQUE SENS	OR ASSY S/N:0570 (ROGUE UNIT).  WHEN LT SWITCH IS COLD SPRAYED "FLAP DRIVE" CAUTION LIGHT COMES ON WITH TQ SENSOR CENTER	ED.  TORQUE SENSOR ASSY P/N:756158 REQUIRES REPLACEMENT.  (RESOLVED ON W/O: 27127 TASKCARD: NR-00001)  FLAP DRIVE TORQUE	 SENSOR ASSY REPLACED. RII INSPECTION COMPLETED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081119		EA  	2008	11	19	CA080813006      	2	20080801	G	8520	SL18840	CAMSHAFT        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	WORN            	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA			1150 								(CAN) NR 3 AND NR 4 INTAKE LOBE IS ROUNDED OFF AND SUBSEQUENTLY METAL WAS FOUND IN THE OIL FILTER DURING ROUTINE MX.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081117		EU  	2008	11	17	CA080813007      	1	20080812	G	5544	5554012215	COVER PLATE     		5554012038  	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RUDDER	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA			19069								(CAN) PILOT INDICATES RUDDER MOVEMENT STIFF.  MORE RT RUDDER REQUIRED AT TAKE-OFF. INSP BY MAINT REVEALED THAT THE COVER	 PLATE AT THE BOTTOM OF THE RUDDER WAS BENT OUT OF SHAPE CAUSING INTERFERENCE WITH THE RUDDER MOVEMENT. INSP OF OTHER AC	FT REVEALS THAT THIS COVER PLATE CAN RUB ON THE RUDDER STOP OVER TIME AND MAY BE THE BEGINNING OF THE CAUSE OF THIS PROB	LEM.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081117		CE  	2008	11	17	CA080813008      	1	20080813	G	3097		WIRE            			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	DEICE SYS	CHAFED          	W				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) PILOT REPORTED INTERMITTENT "DE-ICE PRESSURE" ANNUNCIATOR ILLUMINATION WHEN DE-ICE WAS NOT SELECTED. ON INVESTIGAT	ION A CHAFED WIRE WAS FOUND IN ZONE 527. THE WIRE HAD CHAFED ON THE LT CABIN ENTRY LIGHT FIXTURE CAUSING AN INTERMITTENT	 SHORT TO GROUND ACTIVATING THE LIGHT.				1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
	20081118		SW  	2008	11	18	CA080813009      	1	20080320	G	6420	212011701	BELLCRANK       	BELL        	212011701   	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TAIL ROTOR	IMPROPER PART   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING T/R RIGGING CHECK, IT WAS NOTED THAT WHEN FULL LT PEDAL WAS APPLIED, THE COUNTERWEIGHT LINK TO COUNTER WEIG	HT ARM HARDWARE WOULD CONTACT T/R CROSSHEAD ASSY. UPON INVESTIGATION THE WRONG P/N OF COUNTERWEIGHT BELLCRANK ASSY`S WER	E INSTALLED FOR THE PARTICULAR P/N OF THE T/R HUB ASSY. THIS A/C HAS T/R HUB ASSY P/N 212-011-701-125 INSTALLED AT THIS 	TIME.			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081118		SW  	2008	11	18	CA080813011      	1	20080526	G	6410		BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TIAL ROTOR	UNKNOWN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSP OF T/R HUB AND BLADE ASSY REVEALED AN INTERFERENCE BETWEEN BOTH T/R BLADES AND T/R YOKE AT THE LEADING EDGE/R	OOT. T/R BLADES REMOVED AND DRESSED OUT TO PROVIDE .010" CLEARANCE BETWEEN YOKE AND BLADES (IAW PSE). YOKE INSPECTED FOR	 DAMAGE, NONE FOUND.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081119		NE  	2008	11	19	CA080813012      	2	20080811	G	7250		TURBINE         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					ENGINE	FAILED          	W				B	R			EMER. DESCENT           	AUTOROTATION            			K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) HELICOPTER WAS RETURNING TO AIRPORT, ENGINE CHIP LIGHT CAME ON, FOLLOWED SHORTLY BY A POPPING SOUND FROM ENGINE, A	 VIBRATION IN AIRFRAME & LOW ROTOR HORN. AN AUTOROTATION INITIATED & WHEN PILOT FLARED TO LAND, NOTICED ENGINE STILL DEV	ELOPING POWER.  ACFT LANDED UNDER POWER WITH NO FURTHER INCIDENT.  INITIAL INVESTIGATION SHOWED MANY BIG CHUNKS OF METAL	 ON CHIP PLUGS & IN OIL STRAINERS. METAL ALSO FOUND ON ENGINE DECK. REAR BEARING VENT LINE FOUND OFF THE 2 OCLOCK VENT 	STRUT & A LARGE AMOUNT OF OIL BLOWN OUT VENT ONTO ENGINE, ENGINE DECK & TAILBOOM (APPROX. 2 QUARTS LOST). THIS WOULD EXP	LAIN INTENSE SMOKE OBSERVED COMING FROM ENGINE DURING AUTOROTATION & LANDING. RUBBING NOISES CAN BE HEARD WHEN TURNING C	1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081118		NE  	2008	11	18	CA080814001      	2	20080703	G	7200		ENGINE          			BAG   	ATP   	ATP         	       	EU  	PWA   	PW120 	PW126A      	 	NE  						FLAMED OUT      	W				K				NONE                    				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE ENGINE FLAMED OUT AND THEN RELIT (AUTO RELIGHT) WITHIN 2 SEC. THE OCCURRENCE HAPPENED APPROXIMATELY 10 MIN. AF	TER ENCOUNTERING SEVERE WEATHER INCLUDING HAIL AND MODERATE TURBULENCE. THE FLIGHT CONTINUED TO DESTINATION WITHOUT FURT	HER PROBLEMS. POST FLIGHT INSPECTION SHOWED NO DAMAGE AND THE A/C CONTINUED IN SERVICE.				2	L	7	2 	4T	4	T	RT	A27NM   	E2ONE				 
	20081118		NE  	2008	11	18	CA080814002      	2	20080428	G	7200		PLANETARY GEAR  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	DISTRESSED      	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER T/O, THE PILOT NOTED ENGINE VIBRATION FOLLOWED BY AN OIL PRESSURE DROP. HE RETURNED TO THE POINT OF DEPARTUR	E WHERE AN UNEVENTFUL LANDING WAS PERFORMED UNDER POWER. THE ENGINE WAS FWDED TO MFG WHERE 1ST STAGE PLANET GEAR DISTRES	S WAS FOUND. THE AFFECTED HARDWARE WILL BE RETURNED TO MFG FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT 	AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081118		NE  	2008	11	18	CA080814003      	2	20080730	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FOD             	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) PILOT ABORTED TAKE-OFF DUE TO ENGINE POWER LOSS. POST FLIGHT INSP REVEALED POWER TURBINE AND 1ST STAGE COMPRESSOR 	FOD. ENGINE WAS REMOVED AND SENT FOR EVALUATION AND REPAIR. SUSPECT HARDWARE WILL BE FWDED TO MFG FOR INVESTIGATION. MFG	 WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081119		NE  	2008	11	19	CA080814004      	2	20080809	G	7261		LINE            			BOEING	767   	7673Y0      	       	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					ENGINE OIL SYS	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NR 1 ENGINE DUE HOC OCCURRED AUG 8/9. ON INVESTIGATION IT APPEARS THERE IS A LEAK FROM THE TAIL BEARING HOUSING FE	ED TUBE NEAR THE AFT SUMP HOUSING &  REPLACED THE OIL FEED LINE. ACTUAL ROOT CAUSE IS NOT YET KNOWN (CRACKED LINE LOOSE 	OR DAMAGED FITTING). OIL TRENDING DID NOT SHOW ANY CONSUMPTION OR PRESSURE ANOMALIES PRIOR TO THE EVENT.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
	20081118		NE  	2008	11	18	CA080814005      	2	20080730	G	7200		ENGINE          			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					LEFT	POWER LOSS      	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF, THE LT ENGINE POWER ROLLED BACK ABOUT 8-10 PERCENT. WHILE ON CLIMB AND WHILE LEVELING-OFF AT 6,00	0 FT, SEVERAL OTHER ROLL-BACKS WERE NOTED. ACCORDING TO THE PIC, THESE SEEMED TO OCCUR AFTER A TLA ADJUSTMENT. CREW STAB	ILIZED ACFT AT 6,000 FT AND DECIDED TO DIVERT. AN UNEVENTFUL DUAL ENGINE LANDING WAS ACCOMPLISHED. TROUBLESHOOTING REVEA	LED POSSIBLE ISSUE WITH LT ENGINE FCU. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISH	ED.		2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
	20081118		EA  	2008	11	18	CA080814006      	1	20080812	G	7732	6233M30A	TRANSDUCER      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					VIBRATION ANLYZR	UNSERVICEABLE   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) ON THE TAKE-OFF ROLL AT APRX 60KTS, THE FLIGHT CREW REJECTED TAKE-OFF DUE TO AN N2 ENGINE VIBRATION CAUTION MESSAG	E.   VIBE ICON ON LT ENG APPROX 87 PERCENT. SECOND RUN REVEALED NO VIBE RISE ON INDICATOR BUT GETTING VIBE AMBER MESSAGE	. CREW DID NOT FEEL ANYTHING BUT WANTED INSP BEFORE APPLYING MEL.   LT N2 VIBE `VIB` ICON INDICATES CORE HAS EXCEEDED 1.	7 MILS. N1 VIBE INDICATION AND NEEDLES WILL NOT CORRELATE TO AN N2 VIBE INDICATION. NO CHIP FLAGS NOTED. BORESCOPE INSP 	OF COMPRESSOR AND HP TURBINE CARRIED OUT AND FOUND WITHIN LIMITS.  NR1 ENGINE VIBE TRANSDUCER REPLACED. HIGH POWERED RUN	S CARRIED OUT AND VIBE INDICATIONS ALL CHECK OK. SYSTEM CHECKED SERVICEABLE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081118		EU  	2008	11	18	CA080814007      	1	20080814	G	3246	Z0DN6068757295	WHEEL HALF      		PARKER40270 	SOCATA	TBM   	TBM700      	8682000	EU  										RT MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) DURING LANDING ROLL, PILOT NOTICED ABNORMAL "FEEL" OF ACFT AND STEERING.  DISCOVERED FLAT TIRE ON RT MAIN WHEEL. A	CFT RECOVERED FROM RUNWAY. DISASSEMBLED WHEEL AND PERFORMED DYE PENETRANT INSP ON WHEEL HALVES. CRACK INDICATION VERY EV	IDENT IN INNER BEAD RADIUS OF OUTER WHEEL HALF SUB-ASSEMBLY, AND ALSO VISIBLE ON OUTER SURFACE. PART IS SUBJECT TO REPET	ITIVE NDT INSPECTIONS. WHEEL HALF SUB-ASSEMBLY REPLACED.			1	L	7	1 	3T			RT	A60EU   					 
	20081118		NE  	2008	11	18	CA080814008      	2	20080802	G	7200		ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					LEFT	MALFUNCTIONED   	W				K				NONE                    				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			CA											(CAN) WHILE ON APPROACH, THE LT ENGINE ROLLED BACK AND WOULD NOT RESPOND TO THROTTLE MOVEMENTS. WHILE CREW WAS PERFORMIN	G EMERGENCY CHECKLIST FOR ENGINE SHUTDOWN.  THE LT ENGINE SHUTDOWN ON ITS OWN.  ACFT LANDED WITHOUT INCIDENT. MFG WILL C	ONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
	20081118		NE  	2008	11	18	CA080814009      	2	20080804	G	7200		ENGINE          			EMB   	120   	EMB120      	3260201	SO  	PWA   	PW118 	PW118B      	 	NE  						MALFUNCTIONED   	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) WHILE ON INITIAL TAKEOFF ROLL PHASE, PILOT APPLIED POWER ON BOTH ENGINES BUT NOTICED FUEL AND OIL PRESSURE DECREAS	ING ON ONE ENGINE. PILOTS DECIDED TO ABORT TAKEOFF, SHUTDOWN THE AFFECTED ENGINE AND RETURN TO GATE.   MFG WILL CONTINUE	 INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
	20081118		NE  	2008	11	18	CA080814010      	2	20080804	G	7200		ENGINE          			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  					NR 1	SHUTDOWN        	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA											(CAN) THE ACFT WAS ON A FIREFIGHTING MISSION. JUST AFTER A WATER DROP, AS THE PILOT APPLIED FOR POWER, THE NR1 ENGINE WE	NT INTO AUTOFEATHER AND SHUTDOWN BY ITSELF. THE PILOT FOLLOWED PROCEDURES AND RESTARTED THE ENGINE. THE ACFT LANDED SAFE	LY. TROUBLESHOOTING IS FOCUSING ON ELECTRICAL HARNESS AND POSSIBLE OVERTORQUE. MFG WILL CONTINUE INVESTIGATING THE EVENT	 AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
	20081119		NM  	2008	11	19	CA080814011      	1	20080806	G	5330		LAP JOINT       			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					FUSELAGE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7037 								(CAN) INITIALLY SNAGGED BY A FAA INSPECTOR FOR TRACES OF AIR LEAK AT THE LAP JOINT BELOW THE 7TH WINDOW ON THE LT SIDE (	NEAR FR74, STR12L). FURTHER INVESTIGATION IN YYZ DISCOVERED THAT THERE WAS A TOTAL OF 12 LEAK POINTS ON THE LT AND 11 ON	 THE RT SIDE. THE ACFT DID PASS THE AMM CABIN PRESSURIZATION LEAKAGE TEST (21-31-00).				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081119		NE  	2008	11	19	CA080814012      	2	20080804	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				M	B	J	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TO	TAKEOFF        	1			CA											(CAN) AT THE BEGINNING OF THE TAKE-OFF ROLL, PILOT REPORTED NO RESPONSE TO THROTTLE LEVER MOVEMENT, WITH T4.5 INDICATED 	TEMPERATURE PEAKING AT 870 TO 900 C. THE TAKE-OFF WAS SAFELY ABORTED. THE ENGINE TEMPERATURE REMAINED HIGHER THAN THE SI	STER ENGINE AFTER SHUTDOWN AND A BURNED ODOR WAS NOTICED, WITH SOME SMOKE COMING FROM THE EXHAUST. ENGINE IS BEING REMOV	ED AND SENT FOR INVESTIGATION.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLI	SHED.		2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
	20081119		EA  	2008	11	19	CA080814013      	2	20080812	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					LEFT	FAILED          	W				C				ABORTED TAKEOFF         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING TAKE OFF ROLL AT AROUND 60 KNOTS, LT ENGINE ITT ENGINE WARNING ILLUMINATED AND CREW FELT THE ACFT YAW. ENGI	NE WAS SECURED AND ACFT RETURNED TO GATE WITHOUT INCIDENT. METALLIC DEBRIS OBSERVED ON THE RUNWAY AND IN ENGINE EXHAUST 	DUCT. ENGINE TO BE REMOVED AND SENT TO PWC FOR INVESTIGATION. MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADV	ISE OF ROOT CAUSE ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081119		WP  	2008	11	19	CA080815001      	2	20080811	G	7321		FUEL CONTROL    			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE3315     	01514	WP  					NR 1 ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) ACFT WAS RELEASED TO A SATISFACTORY TEST FLIGHT FOLLOWING NR 1 ENGINE CHANGE.  A NTS IN FLIGHT SHUT DOWN WAS TO BE	 PERFORMED BEFORE ACFT COULD BE RELEASED BACK TO SERVICE. ACFT DEPARTED AND HAD A NORMAL TAKE OFF AND PROCEED WITH NTS S	HUT DOWN. PILOT PROCEEDED TO PULL SPEED LEVER BACK FOR FUEL SHUT AND THEN TO FEATHER POSITION AND THEN ENGINE SHUT DOWN 	AND FEATHERED & ALL WAS NORMAL. PILOT THEN PROCEEDED TO TAKE SPEED LEVER OUT OF FEATHER TO SPEEDS LOW TO RESTART ENGINE 	AND FOUND THE SPEED LEVER WAS JAMMED AND WOULD NOT MOVE. PILOT THEN LANDED ACFT SINGLE ENGINE WITH NO PROBLEMS. SPEED LE	VER CONTROLS WERE CHECKED AND FOUND THAT THE LEVER ON THE FCU WAS OVERCENTERING CAUSING THE JAMMING OF THE CONTROLS. ENG	2	H	7	2 	4T	4	T	RT	A16EU   	E4WE				 
	20081119		NM  	2008	11	19	CA080815002      	1	20080813	G	2432	4011769	BATTERY         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MASTER	OVERHEATED      	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA			21080	478  							(CAN) DURING CLIMB OUT FROM YWK, THE CREW RECEIVED A "MAIN BAT HOT" RED WARNING MSG ASSOCIATED WITH A HIGH TEMPERATURE O	N THE BATTERY TEMPERATURE MONITOR. THE ACFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. MX CONFIRMED THE BATTERY SUFFE	RED FROM A THERMAL RUN-AWAY. THE MAIN BATTERY WAS REPLACED AND THE ACFT RETURNED INTO SERVICE. THE BATTERY TEMPERATURE W	AS NOT RECORDED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081119		NE  	2008	11	19	CA080815004      	2	20080812	G	7200		ENGINE          			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  					RIGHT	FIRE            	W				A				UNSCHED LANDING         				A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA											(CAN) DURING A FIRE FIGHTING MISSION, RT ENGINE WAS SHUT DOWN DUE TO A FIRE WARNING. AN EMERGENCY WAS DECLARED, ACFT DIV	ERTED AND LANDED SAFELY. POST FLIGHT INSPECTION REVEALED EVIDENCE OF A FIRE EXTERNAL TO THE ENGINE CASING WITH DAMAGE TO	 FIREWALL. A MANUFACTURER FIELD SUPPORT REPRESENTATIVE WILL BE ON SITE 14 AUG TO SUPPORT ON SITE INVESTIGATION.  MANUFAC	TURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
	20081119		EA  	2008	11	19	CA080815005      	2	20080803	G	7314		SPLINE          			BEECH 	STC   	STC90BEECH  	       	    	PWA   	PT6   	PT6A20      	52043	EA  					FUEL PUMP	WORN            	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) DURING SKYDIVING OPS, SHORTLY AFTER TAKE-OFF ACFT CRASHED UNDER UNKNOWN CIRCUMSTANCES. IT WAS REPORTED THAT PILOT 	WAS ATTEMPTING TO RETURN TO THE POINT OF DEPARTURE WHEN THE ACCIDENT OCCURRED. PRELIMINARY ASSESSMENT OF ENGINES REVEALE	D LT ENGINE WITH SEVERELY WORN FUEL PUMP SPLINE. ENGINES WILL BE FORWARDED TO MANUFACTURER MONTREAL FOR INVESTIGATION. M	ANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	L	7	2 	3O	3	T		3A20    	E4EA				 
	20081119		EA  	2008	11	19	CA080815006      	2	20080713	G	8520	LW15288	CONNECTING ROD  			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  					NR 4 CYLINDER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ENGINE FAILED DUE TO FAILURE OF NR 3-4 CONNECTING RODS. I WAS NOT ABLE TO REMOVE NR 3 OR 4 CYLINDER DUE TO FLANGES	 BENT OVER ON INSIDE OF CRANK CASE CRANK SHAFT MAY HAVE FAILED.  FOR FURTHER INFO CONTACT: FRANK FILION					1	L	7	2 	3O	3	O		A19S0   	E286				 
	20081112		NM  	2008	11	12	CA080815009      	1	20080117	G	3240		BRAKE           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					MLG	CHATTERING      	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											(CAN) AS REPORTED BY FLIGHT CREW: LT BRAKE CHATTERS WHEN PRESSED, VERY PRONOUNCED AT TIMES CARBON DISK FAILURE CONFIRMED	.					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081112		NM  	2008	11	12	CA080818001      	1	20080814	G	2913	661733	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			4815 								(CAN) DURING CRUISE OPERATION FLIGHT CREW OBSERVED NR 1 HYDR SYS CAUTION LIGHT ON, FLIGHT DIVERTED TO BASE. CREW CONFIRM	ED NO PRESSURE FROM NR 1 EDP SELECTED SPU CONFIRMED PRESSURE 3000 PSI AND NO QUANTITY LOSS. ON GROUND TROUBLESHOOTING RE	VEALED EDP HAD 5 PUNCTURES THROUGH CASING & SOURCE OF SMALL AMOUNT OF HYDR FLUID LOSS. NR 1 ENGINE DRIVEN PUMP REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081113		CE  	2008	11	13	CA080818002      	1	20080707	G	2730		CONTROLLER      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ELEVATOR	FROZEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) APPROXIMATELY 50 MIN OUT, AUTOPILOT BEGAN TO CLIMB, THE A/P WAS DISCONNECTED AND ACFT MANUALLY BROUGHT BACK TO ALT	ITUDE. A/P WAS REENGAGED AND THEN BEGAN TO DESCEND FOLLOWED BY THE AP TRIM FAIL ANN. A/P DISCONNECTED, ELECTRIC TRIM CHE	CK AND APPEARED SERVICEABLE FLIGHT WAS CONTINUED. ON DESCENT, TRIM WAS NOTED TO HAVE LITTLE EFFECT AND EXCESSIVE CONTROL	 FORCES WERE REQUIRED. AFTER LANDING THE TRIM WAS INSPECTED AND THE ELEVATOR WAS FOUND TO BE FROZEN IN A NOSE UP POSITIO	N. AN AME WAS DISPATCHED TO INSPECT THE FLIGHT CONTROLS AFFECTED. THE ENTIRE ELEVATOR AND TRIM SYS WAS INSPECTED WITH NO	 DISCREPANCIES NOTED. AUTOPILOT SYS AND SERVOS INSPECTED AND TESTED WITH NO FAULTS NOTED. ELEVATOR AND TRIM JACKS WERE L	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
	20081113		EU  	2008	11	13	CA080818003      	1	20080806	G	7500	32156281	O-RING          			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					BLEED SYSTEM	FAILED          	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA			3008 	3008 							(CAN) RT BLEED LEAK LIGHT ILLUMINATED IN CLIMB OUT. AC RETURNED TO BASE. CONFIRMED LT BLEED LEAK ON GROUND DURING HIGH P	OWER ENGINE RUNS. COULD NOT DUPLICATE RT BLEED LEAK ON GROUND. FOUND BOTH BLEED SWITCHING VALVES LEAKING FROM REGULATOR 	FITTING ASSY.  DUE TO BAKED O-RINGS ALLOWING HIGH PRESSURE BLEED AIR INTO AFT EQUIPMENT BAY AREA. THIS CAUSED THE SUBSEQ	UENT ACTIVATION OF BLEED LEAK WARNING ILLUMINATION AT 250 DEG F. BOTH VALVES REPLACED O-RING NOT FIELD REPLACEABLE.			2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
	20081113		CE  	2008	11	13	CA080819001      	1	20080814	G	2510	5055301401	CABLE ASSY      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					SEAT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			325  								(CAN) ON AUGUST 14, 2008, PILOT REPORTED "PILOT SEAT DOESN`T MOVE BACK, COULD NOT GET OUT". INVESTIGATION BY MAINT FOUND	 THAT THE CABLE ASSEMBLY FOR THE PILOT SEAT SECONDARY SEAT STOP HAD FAILED PREVENTING THE INERTIAL REEL FROM RELEASING T	O ALLOW THE SEAT TO MOVE. THE CABLE HAD BROKEN IMMEDIATELY AFTER THE SWAGED END.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081113		EA  	2008	11	13	CA080819002      	1	20080715	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) "F/O SIDE WINDOW SHATTERED JUST AFTER TAKE OFF (RETURNED), DETERMINED TO BE CENTER PANE". REMOVED AND REPLACED THE	 F/O`S SIDE WINDSHIELD.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081113		EA  	2008	11	13	CA080819003      	1	20080715	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) "F/O WINDSHIELD SHATTERED ENROUTE, DIVERTED ". REMOVED AND REPLACED THE F/O`S WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081113		EA  	2008	11	13	CA080819004      	1	20080815	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5     	30050	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			14795								(CAN) "DISC - AFTER TAKEOFF CAPTAIN`S WINDSHIELD CRACKED. NO OTHER PROBLEMS NOTED. REMOVED AND REPLACED PILOTS WINDSHIEL	D.					2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081113		EA  	2008	11	13	CA080819005      	1	20080816	G	5610	NP13932210	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5     	30050	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			12265								(CAN) DISC - IN CRUISE FLIGHT, F/O SIDE WINDSHIELD CRACKED AND WINDSHIELD HEAT ON RT SIDE FAILED.. ACFT RETURNED. NO PRE	SS PROBLEM. ALL OTHER SYS NORMAL. REMOVED AND REPLACED F/O SIDE WINDOW.					2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081113		NM  	2008	11	13	CA080819006      	1	20080818	G	2913	5116403	PUMP            			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					HYD SYSTEM	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) WHILE ENROUTE, THE NR 1 HYD SYS FAILED. AFTER CONSULTATION WITH MAINT, FLIGHT CONTINUED AND LANDED WITHOUT INCIDEN	T.  NR 1 EDP REPLACED REF AMM 29-11-01 PB 401,-422 AND TESTED REF AMM 29-11-01 P 501-5  12.  NO FAULTS OR LEAKS.					2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081118		EU  	2008	11	18	CA080819008      	1	20080805	G	6230		NUT             			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					MAIN ROTOR	LOOSE           	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) VIBRATION NOTICEABLE ON COLLECTIVE CONTROL PWR CHANGES. FURTHER INVESTIGATION REVEALED THAT THE MAIN ROTOR MAST HA	D .2500 INCH VERTICAL PLAY. ON THE REMOVAL PROCEDURE OF THE MAIN ROTOR MAST FROM THE GEARBOX IT WAS NOTED THAT THE MAST 	NUT HAD NO TORQUE. A THOROUGH INSPECTION OF THE ACCESSIBLE GEARBOX COMPONENTS WAS CONDUCTED WITH NO FAULTS DETECTED, THE	 MAIN ROTOR MAST WAS REINSTALLED AND THE ACFT FLOWN WITH NO FURTHER VIBRATION DETECTED.			1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
	20081118		GL  	2008	11	18	CA080819009      	1	20080815	G	3234	17C17616A3	VALVE           			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					LANDING GEAR	UNKNOWN         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING FINAL APPROACH THE PILOT SELECTED THE LANDING GEAR DOWN AND THERE WAS NO MOVEMENT. MOMENTARILY THE PROX SYS	 FAULT CYAN CAS POSTED, BUT CLEARED WITHIN SECONDS. THE PILOT PUT THE GEAR HANDLE BACK UP. THEN SELECTED IT BACK DOWN. A	GAIN THE GEAR DID NOT MOVE.  HE THEN GRABBED THE QRH AND CARRIED OUT THE EMER PROCEDURES TO DEPLOY THE GEAR. WHEN THE EM	ER LG HANDLE WAS PULLED THE GEAR DEPLOYED AND ACHIEVED 3 GREEN IN A FEW SECONDS. THE LANDING WENT SMOOTHLY.			2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
	20081118		SW  	2008	11	18	CA080819010      	1	20080808	G	2435	23079010	STARTER GEN     			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	29081	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	RIGHT	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			DE	DESCENT        	1			CA				710  							(CAN) UPON DESCENT, THE RT GENERATOR FAILED AND COULD NOT BE RESET. MAINT WAS CALLED UPON LANDING AND FOUND THE AFT PART	 OF THE STARTER GENERATOR HAD FAILED. REAR COVER WAS DESTROYED, REAR FAN BLADES WERE ALL BROKEN AND REAR BEARING WAS DES	TROYED. UNIT REPLACED AND ACFT CHECKED SERVICEABLE. INVESTIGATION INTO FAILURE PENDING.				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081124		SW  	2008	11	24	CA080819011      	1	20080810	G	7500	8943825	TUBE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE BLEED	FRACTURED       	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) TUBE HAD BROKEN AT WELDMENT THAT ATTACHES THE TUBE TO THE FLANGE THAT BOLTS IT TO THE ENGINE BLEED.  AIR PORT WAS 	CRACKED 90% OF THE WAY AROUND WELD.  THIS CAUSED THE ENGINE TO NOT REACH TARGET TORQUES UNLESS WATER METH WAS USED.  UNI	T WAS REPLACED AND ACFT RETURNED TO SERVICE.				2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE	 
	20081118		EU  	2008	11	18	CA080819012      	1	20080817	G	2750	945020220	DRIVE SHAFT     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAP	SHEARED         	W				K				NONE                    				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			6330 								(CAN) LT INBD FLAP FLEXABLE DRIVE SHAFT SHEARED AT INBD DRIVE END.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081120			2008	11	20	CA080819013      	4	20080812	G	6122	10185	COTTER PIN      			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	GOVERNOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENG INSP, TWO COTTER PIN TAILS WERE FOUND IN ENG ACCY SUMP. INVESTIGATION INTO SOURCE OF PIN TAILS REVEALED	 THAT COTTER PIN (P/N 10185) SECURING NUT (P/N 23212) FOR GOVERNOR DRIVE GEAR SHAFT (P/N 2715) IN ACCY SECTION WAS MISSI	NG. THERE WAS EVIDENCE OF PIN HAVING GONE THROUGH THE GEARS AND REDUCED TO METAL PARTICLES. OVERHAUL SHOP WAS CONTACTED 	AND REVEALED THAT THEY HAD A NEW EMPLOYEE ASSEMBLING THIS SECTION OF ENG, AND WAS USING STANDARD COTTER PIN INSTALLATION	 PROCEDURE. IN THIS LOCATION, IF THE PIN IS INSTALLED WITH  TAIL FOLDED BACK OVER END OF SHAFT, IT WILL CONTACT INSIDE O	F GOVERNOR BASE AND BREAK OFF. ONCE THIS HAPPENS, THE SHORT END OF COTTER PIN CAN ROTATE AND ALSO CONTACT THE INSIDE OF 	1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P28EA	 
	20081118		EA  	2008	11	18	CA080820001      	2	20080817	G	7261	766859C	SCAVENGE PUMP   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 ENGINE	LOOSE           	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA			3083 								(CAN) AT 15000 FT IN THE DESCENT, THERE WAS A SUDDEN LOSS OF OIL PRESSURE ON THE NR 2 ENG. GAUGE INSTANTLY SHOWED ZERO W	ITH THE NR 2 OIL PRESS WARNING AND CHIME. CREW IMMEDIATELY SHUT DOWN THE NR 2 ENG, TAKING ABOUT 5 TO 10 SECONDS TO COMPL	ETE MEMORY ITEMS. AFTER ENGINE/PROP FEATHERED, THERE SEEMED TO BE NO OTHER PROBLEMS.   CASTELLATED NUT ON THE OIL SCAVEN	GE PUMP FOUND LOOSE. WITH INPUT SHAFT ROTATING THE SPUR GEAR WAS NOT ROTATING WHICH WAS DRIVE FOR THE ADJACENT SHAFT.  R	GB SCAVENGE IS LOCATED ON THIS SHAFT WHICH WAS NOT ROTATING. OIL SCAVENGE PUMP BEING REPLACED.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081118			2008	11	18	CA080820002      	4	20080815	G	5301		RELEASE MECH    			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  						MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			HO	HOVERING       	1			CA											(CAN) HELI BASKET D407-663-011 INSTALLED IAW INSTRUCTIONS. DURING TRAINING (SLING OPERATION) MANUAL RELEASE WAS USED AND	 FUNCTIONED AS NORMAL DURING THE TRAINING SEQUENCE. ON THE NEXT PICK UP, THE LOAD WAS HOOKED UP ON THE HOOK AND THE PILO	T PULLED INTO AN HOVER AND THEN THE CABLE RELEASED WITHOUT ANY ACTION FROM THE PILOT. HE LANDED IMMEDIATELY.  FURTHER IN	VESTIGATION FOUND THE MANUAL RELEASE CABLE SNAG ON THE OUTSIDE OF THE HOLE CENTER FRAME P/N D2796 STATION 115.75 WHICH P	REVENTED THE HOOK TO CLOSE SECURELY. MFG HAS BEEN INFORMED ABOUT THE INCIDENT AND PICTURES WERE FORWARDED AS WELL.		1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20081118		NM  	2008	11	18	CA080821001      	1	20080215	G	3242	900005831PR	BRAKE           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					NR 1 BRAKE	MALFUNCTIONED   	W				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) NUMEROUS LANDING GEAR NO DISPATCH AND EMERGENCY BRAKE FAULT MESSAGES AFTER TOUCHDOWN NR1 BRAKE REPLACED. CONSIDERE	D SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081118		NM  	2008	11	18	CA080821002      	1	20080704	G	3242	900005832PR	DISK            			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					NR 4 BRAKE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 4 MAIN WHEEL BRAKE CARBON DISK BADLY DETERIORATED.						2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081118		NM  	2008	11	18	CA080821003      	1	20080714	G	3242	900005832PR	BRAKE           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					NR 1	DAMAGED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BRAKE ASSY BREAKING UP.						2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081118		NM  	2008	11	18	CA080821004      	1	20080719	G	3242	900005831PR	BRAKE ASSY      			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					NR 4	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ON PUSHBACK REPORT OF NR 4 BRAKE ASSY FAILURE, AS REPORTED BY STATION SERVICES CREW  BRAKE ASSY REPLACED.						2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081118		NM  	2008	11	18	CA080821005      	1	20080802	G	3242	900005831PR	BRAKE ASSY      			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					NR 2	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI OUT TO THE RUNWAY, ECAS MESSAGE "BRK LT FAULT" CAME ON. FOUND NR 2 BRAKE ASSY FAILED. (CARBON FAILURE)						2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081118		CE  	2008	11	18	CA080821006      	1	20080818	G	3221	030A311201	ATTACH FITTING  			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	29053	NE  	HARTZL	HCB4T	HCB4TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15949	15949							(CAN) DURING ROUTINE INSP, THE NOSE LANDING GEAR TRUNNION ATTACH FITTING WAS FOUND TO BE CRACKED. THE CRACK WAS MEASURED	 AT .3125 OF AN INCH. FITTING REPLACED.					1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
	20081118		NM  	2008	11	18	CA080821007      	1	20080809	G	3242	900005831PR	BRAKE           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					LT MLG	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) LT MAIN BRAKE TEMPS OB 365/IB149, RT BRAKES IB 148/OB130, BRAKES FELT SOFT,  BRAKES REPLACED.  CAUSE: CARBON OXIDA	TION.					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081120		SW  	2008	11	20	CA080821008      	1	20080820	G	5311		FRAME           			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUSELAGE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HYDR SERVO PILOT VALVE SUPPORT RUBBING AGAINST MAIN FRAME. WEAR MARK IS APPARENT ON LT SUPPORT. PICTURES AVAILABLE	 ON REQUEST AND INFO FWD TO MFG CUSTOMER SUPPORT FOR ACTION.					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
	20081118		NM  	2008	11	18	CA080821009      	1	20080809	G	3242	90000582WT	BRAKE           			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					NR 1	DISINTEGRATED   	W				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) BRAKE NR 1 DISINTEGRATED AND M/W CHANGED DUE TO BRAKE STUCK IN TIRE. BRAKE NR 1 CHANGED.						2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081118		EU  	2008	11	18	CA080821010      	1	20080821	G	3040	320570	SPLICE          			PILATS	PC12  	PC1247      	7090552	EU  	PWA   	PT6   	PT6A67      	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDSHIELD HEAT	BURNED          	W				O				OTHER                   				M	W		OVER TEMP                 	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA			19   								(CAN) DURING AN UNRELATED INSTALLATION OF A SATPHONE SYS AN AMP TYPE SPLICE IN THE EXISTING ACFT WIRING WAS NOTED TO BE 	BURNED AND DISCOLORED. FURTHER INSP INDICATED THAT THE WIRING WAS FOR THE WINDSHIELD HEAT SYS. THE WIRE, NR 1H81A12 AS W	AS ALSO DISCOLORED AND BURNED. THERE WERE NO INDICATIONS OF BURNING IN THE SURROUNDING AREA. THE BURNED SPLICE WAS FOUND	 TO BE POORLY CRIMPED TO THE WIRE. WHEN THE WIRE WAS UNTIED FOR REPAIR IT FELL OUT OF THE SPLICE. THE ADJACENT SPLICE AS	 DAMAGED AND REQUIRED REPLACEMENT. A FURTHER INSP FOUND ALL 4 SPLICES WERE IMPROPERLY CRIMPED. REMAINDER OF THE WINDSHIE	LD HEAT WIRING WAS COMPLETED AND NO FAULTS FOUND. THE WIRES 1H83A12,1H85A12,1H80B12,1H81A12 AND SPLICES WERE ALL REPLACE	1	L	7	1 	4T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081118		SW  	2008	11	18	CA080821011      	1	20080215	G	6210	206010200133	BALANCE WEIGHT  		206010200133	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					BLADE	DEBONDED        	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA			3104 								(CAN) IT WAS THOUGHT THAT THE BLADE TIE DOWN WAS LEFT ON THE ACFT. THIS WAS NOT THE CASE IAW A REPORT. THE FOLLOWING OCC	URRED. INSP AND SCRAPPED THE M/R BLADE DUE TO WEIGHT POCKET RETAINING HOLES DAMAGED BEYOND LIMITS. DAMAGE CAUSED BY TELL	 TALE LEAD COUPON (SIZE 1.0`X1.0`X.5`) BONDED TO THE TOP SIDE OF INNER SPAR AT STN. 113.5 DEBONDED INFLIGHT AND BEING FL	UNG BY CENTRIFUGAL FORCE OUT THE TIP CAP OF BLADE. THE CENTRIFUGAL FORCE OUT THE TIP CAP OF COUPON HAD ENOUGH INERTIA TO	 PUSH OUT THE WEIGHT POCKET ON THE T/E SIDE AND TEAR THE SCREWS OUT OF THE SPAR RETAINING HOLES OF TOP AND BOTTOM SPAR A	T T/E SIDE OF SPAR. TIP CAP WAS BENT ON L/E AND T/E UNTIL THEIR WAS SUFFIENT OPENING TO ALLOW THE LEAD COUPON TO EXIT BL	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081118		CE  	2008	11	18	CA080821012      	1	20080817	G	5610	66561000010	WINDSHIELD      			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					COCKPIT	BROKEN          	W				O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE AT FLT 400 ENROUTE, THE RT WINDSHIELD OUTTER PLY SHATTERED, CAUSING A LOUD BANG. NO DEPRESSURISATI	ON OCCUR, RT WINDSHILED HEAT BECAME INOPERATIVE. RT WINDSHIELD REPLACED WITH NEW ONE. ACFT RETURN TO SERVICE.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
	20081118			2008	11	18	CA080821013      	4	20080818	G	3416	066030620010	ALTIMETER       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  		DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA				466  							(CAN) PILOT REPORTED THAT AUTOPILOT CAUSING ACFT TO PORPOISE ON DESCENT FROM 18,000 FT (WHEN BARO RESET), THEN GOES AWAY	. REPLACED ENCODING ALTIMETER AND PROBLEM SOLVED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081118		WP  	2008	11	18	CA080822001      	1	20080728	G	6310	C0511	ACTUATOR        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CLUTCH	FAILED          	W				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			CA			788  								(CAN) THE CLUTCH ACTUATOR WOULD NOT FULLY ENGAGE, SERVICABLE ACTUATOR INSTALLED.						1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081118		NE  	2008	11	18	CA080822002      	2	20080731	G	7322	25766304	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			1595 								(CAN) THE ENGINE HAD ROUGH IDLING, TROUBLESHOOTING REVEALED AN EXCESSIVE AMOUNT OF FUEL WAS BEING INJECTED OUT OF THE FU	EL INJECTORS. INSTALLED A SERVICABLE FUEL SERVO.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		WP  	2008	11	18	CA080822003      	1	20080803	G	6310	C0511	ACTUATOR        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CLUTCH	FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE CLUTCH WOULD NOT ENGAGE DURING ACFT START. REPLACED CLUTCH ACTUATOR.						1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081118		WP  	2008	11	18	CA080822004      	1	20080804	G	2435	BC3151004	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						INOPERATIVE     	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				372  							(CAN) THE STARTER WOULD NOT ENGAGE, REPLACED WITH SERVICABLE STARTER.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		SW  	2008	11	18	CA080822005      	1	20080805	G	2432	RG206	BATTERY         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN	DISCHARGED      	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			157  								(CAN) DURING ACFT START, THE BATTERY WAS FOUND WITH NO CHARGE, BATTERY REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081118		WP  	2008	11	18	CA080822006      	1	20080715	G	6310	C0512	CLUTCH ACTUATOR 			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			667  								(CAN) CLUTCH WOULD NOT ENGAGE, SERVICABLE CLUTCH ACTUATOR INSTALLED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		WP  	2008	11	18	CA080822007      	1	20080730	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			623  								(CAN) THE STARTER WAS GRINDING DURING START, STARTER REPLACED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		WP  	2008	11	18	CA080822008      	1	20080729	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			CA											(CAN) THER STARTER WOULD NOT START.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		WP  	2008	11	18	CA080822009      	1	20080727	G	2435	BC3151004	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				687  							(CAN) STARTER FAILED ON START UP, STARTER REPLACED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		NE  	2008	11	18	CA080822010      	2	20080714	G	7322	25766304	FCU             			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			1996 								(CAN) THE ENGINE WAS RUNNING TOO RICH, TROUBLESHOOTING REVEALED COULD NOT ADJUST FUEL INJECTOR SERVO, REPLACED FCU.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		SO  	2008	11	18	CA080822011      	1	20080725	G	3710	441CC7	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	VACUUM SYS	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			452  								(CAN) DURING INSPECTION THE LT ENGINE VACUUM PUMP FOUND SEIZED, REPLACED.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081118		WP  	2008	11	18	CA080822012      	1	20080718	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						DAMAGED         	W				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			CA			55   								(CAN) THE STARTER WAS INTERMITTENT, ON INSPECTION WAS FOUND TO HAVE TEETH MISSING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		NE  	2008	11	18	CA080822013      	2	20080703	G	7322	25766304	FCU             			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION THE MIXTURE CONTROL FOUND TO BE BINDING IN THE RICH POSITION, REMOVED DUE TO STIFF MIXTURE LEVER	.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		GL  	2008	11	18	CA080822014      	2	20080707	G	7261		LABYRINTH SEAL  			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, OIL WAS FOUND POOLING IN EXHAUST COLLECTOR, SUSPECT NR 5 LAB SEAL.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081124		CE  	2008	11	24	CA080822015      	1	20080822	G	3060		WIRE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110N   	29062	NE  	MCAULY	4HFR34	4HFR34C660  	NE  	PROP DE-ICE BOOT	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) AFTER LANDING, THE ACFT EXPERIENCED A SMALL AMOUNT OF SMOKE IN THE COCKPIT, FOLLOWED IMMEDIATELY BY THE SWITCH CIR	CUIT BREAKER POPPING.  THE AMMETER FOR THE PROP DE-ICE WAS PEGGED TO THE FULL RT, ONCE THE SYSTEM WAS SWITCHED OFF THE M	ETER STILL INDICATED IN THE GREEN.  MX INSPECTION REVEALED THE WIRE LEAD OFF THE PROP DE-ICE BOOT WAS TOO LONG AND WAS R	UBBING AGAINST THE INSIDE OF THE SPINNE.  THE SHORT TO GROUND WENT THROUGH THE BRUSH BLOCK ASSEMBLY TO THE AMMETER IN TH	E COCKPIT.		1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	5	C	3PNE	 
	20081118			2008	11	18	CA080822016      	4	20080820	G	3421	1013800803	GYRO            			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	ATTITUDE	FAILED          	W				O				OTHER                   				I			FLT. ATTITUDE INST.       			UK	UNKNOWN        	1			CA											(CAN) THE RT ATTITUDE INDICATOR IS AN AIR DRIVEN UNIT. THIS ACFT HAS HAD NUMEROUS FAILURES. INTERVALS RANGE FROM SEVERAL	 MONTHS OR MORE TO A FEW DAYS. GENERALLY IF ONE FAILS, THE NEXT ONE FAILS, AND THEN MAY LAST FOR MONTHS. THESE UNITS HAV	E TYPICALLY COME FROM SEVERAL DIFFERENT VENDORS.  THE ACFT SYSTEMS HAVE BEEN CHECKED THOROUGHLY WITH NO FAULTS FOUND. IT	 RUNS ON VACUUM, AND THE SUCTION IS EXACTLY IN THE MIDDLE OF MM SPECS.  CONTINUING TO MONITOR AND INVESTIGATE THE DEFECT	. THERE HAVE BEEN FAILURES ON OTHER ACFT AS WELL, BUT NOT AT THE SAME RATE AS THIS ONE.		2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
	20081118		NM  	2008	11	18	CA080825001      	1	20080825	G	6120	666000459	CONTROL UNIT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 ENGINE	SHORTED         	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) DURING FLIGHT THE PROP SPEED SHOWED 1070 RPM IN DESCENT WITH PEC CAUTION. CREW PREFORMED NR2 ENGINE IFSD AND RETUR	NED TO BASE.  MAINT REVIEWED CDS AND FOUND FC 160 CH A&B. FIM TASK FOLLOWED AND FOUND MPU SHORTED TO GROUND. MPU REPLACE	D AND EGR C/O SATIS. ACFT RELEASED FOR SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081118		EU  	2008	11	18	CA080825002      	1	20080822	G	2913	993378	PUMP            	VICKERS     	PPEV3008EA  	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYDRAULIC SYS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			AP	APPROACH       	1			CA			2220 	2220 							(CAN) ON LANDING, HYDR PUMP CONTINUED TO CYCLE, AFTER LANDING WHEN ACFT PARKED, HYDR FLUID DRIPPING FROM FUSELAGE NEAR H	YDR PUMP LOCATION. WHEN PUMP OPERATED FLUID SPRAYED FROM CRACK IN END PLATE OF PUMP, PUMP ASSY REPLACED WITH SERVICABLE 	UNIT.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081120		SO  	2008	11	20	CA080825003      	1	20080814	G	2750	487084	SOLENOID        		4018542     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TE FLAP	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) FLIGHT CREW REPORTED DURING SHORT FINAL, SELECTING THE FLAPS FROM 25 DEGREES TO 40 DEGREES, THE ACFT YAWED SEVEREL	Y. VISUAL CHECK OF THE FLAP REVEALED THE LT FLAP AT FULL DOWN AND THE RT FLAP AT APPROX 25 DEGREES. THE ACFT LANDED WITH	OUT FURTHER INCIDENT. MAINT CONFIRMED THE ASYMMETRIC CONDITION AND FOUND THE LT FLAP DRIVING PAST THE "DOWN" LIMIT SWITC	H ACTUATION POINT AND THE LT FLAP L/E ALSO BUCKLED AT THE MID-FLAP TRACK AREA. LT AND RT FLAP TRANSMISSIONS, MOTOR AND D	RIVE CABLES WERE INSPECTED. SUSPECT THE ASYMMETRIC CONDITION DUE TO LT FLAP DRIVING PAST THE DOWN LIMIT AND THE EXCESSIV	E DRIVING TORQUE CAUSED THE INTERNAL DRIVE CABLE SPLINES TO SKIP CAUSING THE SPLIT FLAP CONDITION.  THE FOLLOWING MAINT 	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081118		SO  	2008	11	18	CA080825004      	1	20080820	G	2460	4817102	CLAMP           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  		FAULTY          	W				O				OTHER                   				G			MULTIPLE FAILURE          			IN	INSP/MAINT     	1			CA											(CAN) FLIGHT CREW REPORTED ALL FLIGHT CONTROL TRIM AND BOTH ENGINE COWL FLAP INDICATORS INOP. MAINT INVESTIGATION ISOLAT	ED THE VOLTAGE CLAMPER AT FAULT. AFTER REMOVAL OF FAULTY CLAMPER FOUND THE INTERNAL RESISTOR BADLY BURNED AND PARTIALLY 	MELTED. VOLTAGE CLAMPER P/N 48171-02 REPLACED AND ALL INDICATIONS CHECKED SERVICEABLE.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081201		CE  	2008	12	1	CA080826001      	1	20080812	G	3260	3086070843004	LIGHT           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG INDICATOR	INOPERATIVE     	W				O				OTHER                   				P			NO WARNING INDICATION     			DE	DESCENT        	1			CA											(CAN) LANDING GEAR MOTOR CONTROL CIRCUIT BREAKER FOUND POPPED WHEN THE GEAR WAS SELECTED DOWN FOR LANDING. GEAR WAS LOWE	RED BY EMERGENCY EXTENSION INDICATING (3) GREEN BUT THE IN TRANSIT LIGHT WAS STILL ON.  ACFT EXPERIENCED A NOSE GEAR COL	LAPSE ON LANDING. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THERE WERE NO DIVIDERS IN THE HEAD OF THE GEAR DOWN 	LIGHT BLOCK. THIS ALLOWED LIGHT FROM THE MAIN GEAR DOWN AND LOCK LIGHT TO ILLUMINATE THE NOSE INDICATOR. IT GAVE A FALSE	 INDICATION THAT ALL 3 GEAR WERE IN THE DOWN AND LOCK POSITION.   A NEW INDICATOR WAS INSTALLED SHOWING A POSITIVE INDIC	ATION OF THE NOSE NOT LOCKED.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
	20081118		EA  	2008	11	18	CA080826002      	2	20080824	G	7321	252444057	FCU             			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				2545 							(CAN) WHEN POWER WAS APPLIED TO ENGINE AFTER A TOUCHDOWN, A CONSIDERABLE YAW TO THE LT WAS FELT BY THE PILOTS. ACFT WAS 	MOVED OFF THE RUNWAY AND A MAINT RUN-UP OF ENGINES INDICATED A POWER LOSS IN THE LT ENGINE.  AFTER TROUBLESHOOTING THE E	NGINE A REPLACEMENT FCU WAS INSTALLED. ENG RUNS AND FLIGHTS WERE COMPLETED WITH NO FURTHER PROBLEMS.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
	20081124		EU  	2008	11	24	CA080826003      	1	20080815	G	2440		UNKNOWN         			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					GROUND POWER	UNKNOWN         	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) GPU VOLTAGE SPIKED WHILE PROVIDING POWER FOR ENGINE START.  GROUND POWER WAS SHUT OFF AND ENGINES STARTED USING IN	TERNAL BATTERIES.  BOTH ESSENTIAL DC ELECTRICAL CBS FOUND TRIPPED WHILE PERFORMING TAXI CHECK LIST. RETURNED TO GATE.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6				 
	20081118		EU  	2008	11	18	CA080826004      	1	20080819	G	3213		STRUT           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					LT MLG	CONTAMINATED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF CHECKS COMPLETED AND CONDITION LEVER RETARDED, RESULTING IN CONFIG WARNING AND OAT LIGHT ILLUMINATIN	G. THIRD OCCURANCE. UNSCHEDULED LANDING MADE. (FUEL BURNED OFF TO ACCOMODATE LANDING WEIGHT) THE LT MLG WAS NOT FULLY EX	TENDED DUE TO AIR REMAINING IN THE OLEO. THE LG SERVICING WAS REPEATED USING A POWER SERVICING CART, NO FURTHER FAULTS F	OUND ON SUBSEQUENT GEAR SWINGS.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6				 
	20081120		EU  	2008	11	20	CA080826005      	1	20080818	G	3260		SQUAT SWITCH    			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					LANDING GEAR	OUT OF RIG      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF CHECKS WERE COMPLETED AND CONDITION LEVERS RETARDED, CONFIG WARNING AND OAT LIGHT CAME ON. UNSCHEDUL	ED LANDING COMPLETED, RETURNED TO BASE. GEAR SWING COMPLETED, FAULT NOT DUPLICATED. LANDING GEAR HAD BEEN SERVICED PRIOR	 TO FLIGHT. RE-SERVICED MLG,  GEAR SWING COMPLETED, NO FAULT FOUND. SECOND TAKEOFF COMPLETED WITH THE SAME RESULTS AS TH	E FIRST. SECOND UNSCHEDULED LANDING MADE. FLIGHT CANCELLED. LG POSITION WARNING SYS INSP INDICATED A PROBLEM WITH THE LT	 INBD SQUAT SWITCH RIGGING. SWITCH RE-RIGGED LG SWING COMPLETED, NO FURTHER FAULTS FOUND.		2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6				 
	20081118			2008	11	18	CA080826006      	1	20080825	G	5414	85410587	SKIN            								PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	LT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A WALKAROUND, THE LT NACELLE SKIN PANEL 85410587 DISPLAYS A SMALL CRACK FROM ONE OF THE UPPER AFT FASTENERS	 TO THE SKIN EDGE, AND A LARGE 4 INCH+ CRACK RUNNING ALONG THE LENGTH OF THE SKIN PANEL. AS THE SKIN PANEL IS NOTED AS B	EING BULGED OVER APPROX .6666 OF ITS LENGTH IT IS PROBABLE THAT THE LONG CRACK IS DUE TO THIS SKIN DEFECT. THE SKIN WILL	 BE REMOVED AND THIS SDR WILL BE UPDATED.								4	T			E20NE	6	C	P7NE	 
	20081120		CE  	2008	11	20	CA080826007      	1	20080826	G	7931	26060154RX	INDICATOR       			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	OIL PRESSURE	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				107  							(CAN) OIL PRESSURE NEEDLE INDICATES HIGH OIL PRESSURE WHEN ENGINE IS OPERATING (100- 105 PSI) READS OFF OF ZERO WHEN ENG	INE IS NOT OPERATING (10-15 PSI) 106.5 HRS SINCE OVERHAUL.					1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	6	C	P15EA	 
	20081120		CE  	2008	11	20	CA080826008      	1	20080825	G	3240	6119	CYLINDER        		PN9122      	CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4258 								(CAN) CYLINDER CASTING COMPOSED OF ALUM STEEL ANCHOR BOLTS MOUNTED IN CASTING CAUSED CORROSSION OF ALUM BOSS BORES WHICH	 OVER TIME CAUSED THE BOSS CASTING TO CRACK DUE TO THE (SWELLING) ACTION OF THE CORROSION NEXT TO THE STEEL PINS. DUE TO	 THE NORMAL DIRT CREATED BY BRAKING VISUAL INSP DIFFICULT WITHOUT REMOVAL FOR CLEANING. BOTH ANCHOR BOLT BOSSES CRACKED 	ON BOTH CALIPERS (4 CRACKS).			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081120		SO  	2008	11	20	CA080827001      	1	20080827	G	5210	12030027001	SHIM            		1454101760  	EMB   	145   	EMB145LR    	3260212	SO  										PAX DOOR	CORRODED        	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			20785								(CAN) DURING 4Y, 8Y CHECK, BOTH SHIM P/N: 120-30027-001 LOCATED BETWEEN BRACKET P/N:145-25211-601, 145-25211-602 WAS FOU	ND HEAVELY CORRODED. DUE TO THE EXPENSION PRODUCE BY THE CORROSION, SOME BRACKET FASTENER WAS BROKEN AND THE ATTACHED FR	AME P/N: 145-25299-001 WAS DEFORMED. (TC NR 20080827001)				2	L	7	2 	4T			RT	T00011AT					 
	20081120		NM  	2008	11	20	CA080828001      	1	20080826	G	7920	AE7077093	FLEX LINE       			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) AN ACFT EXPERIENCED AN IN-FLIGHT ENGINE INCIDENT.  THE CREW OBSERVED SUDDENLY THE OIL PRESSURE INDICATOR DROPPED T	O "0" ASSOCIATED WITH THE ENG NR 2 LOW PRESS CAUTION LIGHT AND MASTER WARNING LIGHT. FLIGHT CREW SHUT DOWN THE ENGINE NR	2 IAW QRH PROCEDURES, ACFT MADE A SATISFACTORY SINGLE ENGINE LANDING.  ON GROUND, MAINT PERFORMED EXTERNAL VISUAL INSP A	ROUND ENG AND WAS FOUND CONSIDERABLE EVIDENCE OF OIL LEAKAGE, DETAILED INSP TO ENG DISCOVERED THE HOSE ASSY FLEXIBLE RT 	P/N DSC391-3 WITH ABNORMAL DAMAGE IN THE JOIN ZONE (BETWEEN FLEXIBLE HOSE AND RIGID TUBE). THE RT FLEXIBLE HOSE ASSY WAS	 REPLACED IAW EMM AND BUILD UP MANUAL, PERFORMED RUN TEST FOR OIL LEAKS AND THE ACFT WAS RETURNED TO SERVICE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081120		EA  	2008	11	20	CA080828002      	1	20080818	G	5610	NP13932112	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			10871								(CAN) BEGIN QUOTE  "DISC - WINDOW SHATTERED INFLIGHT WHEN FLYING C/A - RAR FOS WINDOW"  END QUOTE.						2	L	7	2 	4F			RT	A21EA   					 
	20081120		EA  	2008	11	20	CA080828003      	1	20080820	G	2910	601R752863	HYDRAULIC LINE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  										HYDRAULIC SYS	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF IN ROUTE, THE MESSAGE HYD NR1 LOW PRESS CAUTION CAME ON EICAS . CREW COMPLIED WITH QRH AND RETURNED	.  AFT EQUIPMENT WAS SOAKED WITH SKYDROL.  A LEAK WAS FOUND ON A RETURN LINE ON THE HYD NR1 MANIFOLD.  THE LINE AND ELBO	W WERE REPLACED , ACFT BACK TO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
	20081124		EU  	2008	11	24	CA080828004      	1	20080828	G	2720	137312E401	FITTING         			BAG   	JETSTM	JETSTM3112  	1500220	EU  	GARRTT	TPE331	TPE33110UGR 	29069	NE  					RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAPER PINS PN SP28N14 FOUND SLIGHTLY LOOSE AT SPRING END FITTING ASSY.						2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE				 
	20081120		NE  	2008	11	20	CA080828005      	2	20080827	G	7260	31070371	SPUR GEAR       								GARRTT	TPE331	TPE33110UGR 	29069	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FRONT GEAR CASE ON ENG REMOVED FOR TORQUE RING REPLACEMENT. PITTING FOUND ON SPUR AND HELICAL GEAR ASSY.  CONSULTA	TION WITH ENGINE OVERHAUL FACILITY IS ON GOING.										4	T			E4WE	6	C	3PNE	 
	20081120		CE  	2008	11	20	CA080828006      	1	20080827	G	7197		WIRE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  		OUT OF POSITION 	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) WHEN DESCENDING THROUGH FL 180, CREW NOTICED RT ENG WOULD NOT GO BELOW 1600 FT/LBS TORQUE WITH PWR LEVER AT FLIGHT	 IDLE. CREW CHECKED REMAINING RT INSTRUMENTS AND CONFIRMED IT WAS NOT AN INDICATION ISSUE.  RT PROP LEVER WAS OPERATED W	ITH TORQUE INCREASE ON FWD MOVEMENT, NORMAL OPERATION. PWR LEVER WAS MOVED FWD TO HIGHER POWER SETTING AND  ENG RESPONDE	D. STILL, WHEN RETARDING PWR LEVER TO FLIGHT IDLE, TORQUE REMAINED AT 1600 FT/LBS. CREW THEN DETERMINED THAT IT WAS CONS	IDERED A RUNAWAY TORQUE SITUATION, DECLARED AN EMERGENCY, THEN SHUTDOWN AND SECURED THE RT ENG. A SAFE LANDING WAS CARRI	ED OUT AT THE DESTINATION AIRPORT STOPPING 3/4 DOWN THE RUNWAY. EMERGENCY CREWS MET THE ACFT AND ALL PASSENGERS AND CREW	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
	20081120		NE  	2008	11	20	CA080829001      	2	20080827	G	7421	REM40E	SPARK PLUG      			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	DEFECTIVE       	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA											(CAN) ON TROUBLESHOOTING LT MAG DROP (100 RPM), REAR SPARK PLUGS WERE REPLACED WITH NEW SPARK PLUGS OBTAINED FROM RELIAB	LE SOURCE WITH CERTIFICATION. ENG WAS GROUND RUN AND MAG CHECK CONDUCTED AND RPM DROP ON LT MAG WAS 150RPM. AFTER INSPEC	TING LT MAG AND IGNITION LEADS IT WAS DISCOVERED THAT THE NEW SPARK PLUG IN NR 7 CYL REAR WAS NOT FIRING. THE SPARK PLUG	 WAS REPLACED AND ENG RUN WITH SATISFACTORY RPM DROP ON LT MAG.			1	H	7	1 	3R	3	R	RC	A806    	5E1				 
	20081120		NM  	2008	11	20	CA080829002      	1	20080805	G	2497	91252ZC7C4001	CONTACTOR       			BOEING	737   	737232      	1384475	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ELECTRICAL SYS	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA											(CAN) AFTER LIFTOFF, SEVERAL FAILURES OCCURED. ANTISKID INOP, F/O PITOT INOP, NR2 EPR GUAGE INOP, NR2 AFT FUEL PUMP INOP	, PINNED ASSOCIATED LIGHTS TO TRANSFER BUS PROBLEMS. LANDING BOTH 115V AND 28V AC TRANSFER BUS INOP. NR2 TRANSFER BUS CO	NTACTOR WAS FOUND TO HAVE A VOLTAGE DROP ACROSS THE C1 AND C2 CONTACTS. ALSO HEARD LOOSE PARTS RATTLING WITHIN THE SELF 	CONTAINED RELAY. RELAY WAS REPLACED. (TC NR 20080829002)			2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
	20081120		EU  	2008	11	20	CA080829003      	1	20080829	G	2841	SIC6734	MODULE          	GE          	SIC505911   	AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM56 	CFM565B6P   	13018	NE  					FUEL SYSTEM	IMPROPER PART   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DISCOVERED DURING THE SHOP`S PRELIMINARY INSP OF A FQIC UNIT, THAT THIS DASH 11 UNIT HAD INSTALLED (2) CPU MODULES	 (P/N SIC6734, S/N`S 545 AND 575) THAT WOULD NORMALLY BE FOUND ON A SIC5059-04 UNIT. IN OTHER WORDS, A -11 UNIT WAS RECE	IVED WITH -04 CPU BOARDS, WHICH IS NOT CONSIDERED A PROPER CONFIGURATION. ACFT WAS UNDER A "N" (USA) REGISTRATION WHEN T	HE COMPUTER WAS FITTED TO THE ACFT.			2	L	7	2 	4F	4	F	RT	A28NM   					 
	20081120		EA  	2008	11	20	CA080829004      	2	20080826	G	7314	200F5002R	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					FUEL SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				402  							(CAN) THE FUEL WAS FOUND DURING REGULAR INSP LEAKING, FUEL PUMP WAS REPLACED WITH SIMILAR ONE. THE PROBLEM DIDNT AFFECT	 THE ENG PERFORMANCE. FUEL TRACE WAS LOCATED BETWEEN BODY STAGE OF THE PUMP. THIS IS THE FIRST PROBLEM OF LEAK WITH THIS	 TYPE.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20081126		EA  	2008	11	26	CA080829005      	2	20080829	G	7414	6350	MAGNETO         			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE	FAILED          	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA			7    	7    							(CAN) ACFT FLOWN ON LOCAL FLIGHT TRAINING SORTIE WITH INSTRUCTOR AND STUDENT ON BOARD. INSTRUCTOR REPORTED NO NOTICEABLE	 ENGINE ROUGHNESS OR PWR LOSS DURING FLIGHT.  AFTER TAXI TO PARKING POSITION, INSTRUCTOR EGRESSED A/C AND ADVISED STUDEN	T TO CARRY-OUT SHUTDOWN CHECKLIST. AS INSTRUCTOR WALKED CLEAR OF ACFT HE NOTICED ENGINE CUT-OUT DURING THE STUDENTS DEAD	 MAG TEST PRE SHUTDOWN. POST BRIEFING INTERVIEW WITH STUDENT CONFIRMED THAT ENG WOULD NOT CONTINUE TO OPERATE ON RT MAGN	ETO ALONE. DISCREPANCY WAS REPORTED TO MAINT AND ENTERED AS SUCH IN JOURNEY LOG. MAINT CONFIRMED DEAD MAG ON ENG RUN-UP.	 TIMING CHECK IN HANGAR SHOWED NO FAULTS. REMOVAL/DISASSEMBLY OF MAGNETO SHOWED EVIDENCE OF OVERHEATING/ELECTRICAL SHORT	1	L	7	1 	3O	3	O	RT	A49CE   	1E4	5	C	P25EA	 
	20081120		SO  	2008	11	20	CA080829006      	1	20080829	G	2720	4004009	TORQUE TUBE     		4004638     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			*    								(CAN) DUE FOR INSP IAW SB 1105A, AWD 2003-24-07, EXTERNAL RUST FOUND.  HOLE DRILLED IN TOP OF TUBE, SEVERE CORROSION FOU	ND ON LOWER INTERNAL SURFACES. PART REMOVED FROM SERVICE UNSERVICEABLEV.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081120		CE  	2008	11	20	CA080829007      	1	20080828	G	3240	420001263	VALVE           		99123682    	CESSNA	525   	525B        	2076616	CE  										RESERVOIR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			361  								(CAN) DURING DAILY INSP, THE PRESSURE WAS FOUND LOW ON THE EMERGENCY GEAR/BRAKE RESERVOIR.  BOTTLE WAS REMOVED, VALVE AN	D FITTINGS WERE LEAK CHECKED WITH SNOOP AND CRACK WAS FOUND IN BOTTOM OF VALVE NEAR GAUGE BOSS.					1	L	7	2 	4F			RT	A1WI    					 
	20081120		CE  	2008	11	20	CA080902001      	1	20080806	G	2710	0510105364	CONTROL CABLE   			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	AILERON	FRAYED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			2197 								(CAN) DURING IMPORT INSP, THE LT AFT AILERON CABLE WAS CHAFING ON THE PHANOLIC RUB STRIP ATTACHED TO THE RIB EXTENSION A	T WS 71.125 RESULTING IN SEVERE DAMAGE TO THE CABLE. CABLE REPLACED. UNFORTUNATELY THE CABLE HAD BEEN REMOVED BEFORE PIC	TURES WERE TAKEN OF THE WORN CABLE.  UWN1 AND 3 SIMULATE THE CABLE OVER THE CHAFE STRIP USING THE NEW CABLE, AND UWN2 SH	OWS THE DAMAGED OLD CABLE.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
	20081120		CE  	2008	11	20	CA080902002      	1	20080827	G	2432	4076	BATTERY         			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	29053	NE  	HARTZL	HCB4T	HCB4TN5     	GL  		THERMAL RUNAWAY 	W				H				DEACTIVATE SYST/CIRCUITS				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA				11   							(CAN) DURING DAILY INSP OF ACFT, GPU USED. ACFT KEY TURNED (ON) TO CHARGE BATTERIES. APPROX. 2.5 HRS LATER, VENTING OF B	ATTERY NOTICED FROM ACFT. SMELL OF BURNING PLASTIC. GPU DISCONNECTED, KEY (OFF).  ACFT MOVED OUTSIDE. AIRPORT FIRE DEPT.	 REMOVED NR 1 BATTERY AND ALLOWED TO COOL. THERMAL RUNAWAY ALONG WITH GPU PRODUCING 30 VOLTS NOT 28.8 V.				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
	20081124		EU  	2008	11	24	CA080902003      	1	20080826	G	2750	978732000	CONTROL SYSTEM  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FLAP SYS	MALFUNCTIONED   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA			6586 								(CAN) CREW REPORTED FLAPS MOVED ONLY A FEW DEGREES UP AFTER SELECTING "0" FROM TAKEOFF POSITION "15" IN THE INITIAL CLIM	B PHASE.  "FLAP" CAUTION ILLUMINATED.  ACFT RETURNED TO BASE, TROUBLESHOOTING REVEALED POWER DRIVE UNIT AT FAULT.  PDU R	EPLACED, FUNCTION CHECKS SATISFACTORY.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081120		CE  	2008	11	20	CA080902004      	1	20080816	G	3233	1FA1004323	BARREL          		1143800411  	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG ACTUATOR	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED INSP THE LT MLG ACTUATOR (FRISBY) WAS SEEN TO BE LEAKING. THE ACTUATOR WAS REPLACED ON THE ACFT. 	WHILE IN REPAIR THE BARREL OF THE ATUATOR FAILED NDT FOR A CRACK IN THE THREADED AREA. THIS AREA IS NOT INCLUDED IN SB 3	2-3870 WHICH CALLS FOR NDT OF THE END CAP.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
	20081120		SO  	2008	11	20	CA080902005      	1	20080831	G	3213	15200	HOUSING         	ERAM        	110P241021  	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG STRUT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1888 							(CAN) WHEN LANDING AT THE AIRPORT ON A TRAINING FLIGHT THE NLG PARTIALLY RETRACTED TOWARDS THE REAR OF THE ACFT. THE ACF	T PITCHED RT AND FULL LT BRAKE WAS USED TO KEEP THE ACFT ON THE RUNWAY. THE ACFT MOMENTARILY LT THE RT SIDE OF THE RUNWA	Y AND STRUCK A RUNWAY LIGHT WITH THE RT PROPELLER. THE AFT THEN CAME TO A COMPLETE STOP ON THE RUNWAY. UPON INSP OF THE 	ACFT IT WAS FOUND THAT THE NLG STRUT HSG WAS BROKEN AT THE RT  TRUNNION LINK. THIS ALLOWED THE GEAR LEG TO TURN AND MOVE	 REARWARD UNDER THE ACFT.		1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
	20081120		EU  	2008	11	20	CA080902006      	1	20080813	G	6123		AUTOFEATHER SYS 			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA			11   								(CAN) THE TAKEOFF WAS ABORTED DUE TO THE NR 2 ENGINE ANALOGUE TORQUE INDICATION BEING STUCK AT 120 PERCENT. THE NR 2 ENG	INE AFU WAS REPLACED AND THE ACFT RELEASED FOR SERVICE.					2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20081120		NE  	2008	11	20	CA080902007      	2	20080815	G	7250		TURBINE         			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT 10000 FEET, THE OIL PRESSURE DROPPED TO THE RED BAND ACCOMPANIED BY A LOW OIL PRESSURE WARNING. T	HE ENGINE WAS SHUT DOWN. POST EVENT EXAMINATION OF THE ENG SHOWED DAMAGE IN THE POWER TURBINES. THE ENGINE WILL BE REMOV	ED AND SENT FOR REPAIR. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20081120		NE  	2008	11	20	CA080902008      	2	20080819	G	7200		ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWC   	545   	PW545B      		NE  						FLAMED OUT      	W				D				RETURN TO BLOCK         				X			ENGINE FLAMEOUT           			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING FOR TAKEOFF, THE PILOT RETARDED THE POWER LEVER FROM MID POSITION TO IDLE AND THE ENGINE FLAMED OUT.	 POST EVENT TROUBLESHOOTING SHOWED THAT THE ENGINE WOULD NOT START. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE	 OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20081120		EU  	2008	11	20	CA080902009      	1	20080809	G	6123		AUTOFEATHER SYS 			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					RT ENGINE	UNKNOWN         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			F	R		FLT CONT AFFECTED         	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE RT ENGINE PROPELLER FEATHERED UNCOMMANDED. PILOT SHUTDOWN THE ENGINE AND RETURNED TO AIRPORT, WHE	RE AN UNEVENTFUL SINGLE ENGINE LANDING TOOK PLACE. THE AFU IS SUSPECT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADV	ISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20081120		NE  	2008	11	20	CA080902010      	2	20080805	G	7321		FUEL CONTROL    			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					LT ENGINE	UNKNOWN         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE LT ENGINE EXPERIENCED A SUDDEN TORQUE AND ITT INCREASE. THE CREW RETARDED THE POWER LEVER BUT TH	E TORQUE OSCILLATED BETWEEN 0 AND 60 PERCENT WITH ELEVATED ITT. THE ENGINE WAS SHUTDOWN. THE MFCU AND PUMP WERE REMOVED 	AND SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
	20081126		NE  	2008	11	26	CA080902011      	2	20080902	G	7414	BL600646201	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						CONTAMINATED    	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				498  							(CAN) MAG WAS RECEIVED FOR 500 HR INSP. END PLAY WAS NOTICED BEFORE DISASSEMBLY (0.003", 0.0015" IS MAX ALLOWABLE). WHEN	 MAG WAS DISASSEMBLED A COATING OF ENGINE OIL WAS FOUND ON ALL MAG COMPONENTS. THE COIL TAB WAS NOT LEVEL AND WAS PROTRU	DING ABOVE MAG HSG PARTING SURFACE. THE COIL TAB SHOULD BE LEVEL + OR - 5 DEGREES, THIS TAB WAS BENT APPROXIMATELY 10 DE	GREES UP. TAB HAD CONTACTED THE METAL WASHER ON THE DISTRIBUTOR GEAR AND HAD STARTED TO WEAR THE TAB AND WASHER. THE COI	L TAB WAS BENT BACK TO LEVEL, THE OIL SEAL WAS REPLACED AND THE ROTATING MAGNET BRGS WERE INSPECTED AND RESHIMMED TO MFG	 SPECS. THE MAG WAS THEN RETURNED TO SERVICE.	1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081120		CE  	2008	11	20	CA080903001      	1	20080902	G	8011	149NL	STARTER         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1222 								(CAN) DURING FIRST START OF THE DAY THE PILOT NOTED A GRINDING NOISE WHEN THE STARTER WAS ENGAGED. THE BENDIX WAS SUSPEC	TED TO NOT COMPLETELY ENGAGE RING GEAR. STARTER WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
	20081120		SO  	2008	11	20	CA080903004      	1	20080801	G	7920	SA00402SE	HOUSING         		SA00402SE   	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	OIL FILTER	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			350  								(CAN) RT ENGINE OIL FILTER SEPARATED FROM HSG SHORTLY AFTER TAKEOFF. ENGINE SHUTDOWN IN-FLIGHT. ACFT LANDED SAFELY. ACD 	REMOTE OIL FILTER HSG THREADED STUD FOUND CRACKED. ONE PORTION OF THREADED STUD REMAINED IN FILTER AND THE OTHER HALF RE	MAINED IN THE FILTER HSG.  RT REMOTE FILTER HSG THREADED STUD FOUND TO HAVE 0.020" WALL THICKNESS AT THE NON-THREADED PO	RTION.  LT ENGINE ACD REMOTE FILTER HSG INSPECTED AND THREADED STUD FOUND TO HAVE ONLY 0.017" WALL THICKNESS AT THE NON-	THREADED PORTION.  SUSPECT THAT BOTH PARTS WERE INCORRECTLY MACHINED.  A REPLACEMENT PART FROM MFG HAD 0.060" WALL THICK	NESS.	1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
	20081120		WP  	2008	11	20	CA080903005      	1	20080813	G	2435	14924HT	MOUNT           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STARTER MOUNT PAD CRACKED THROUGH BY FRONT MOUNTING HOLES.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081120		EA  	2008	11	20	CA080903006      	1	20080831	G	3230	NAS16128	O-RING          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					LANDING GEAR	DETERIORATED    	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			5135 								(CAN) DEPARTING, EN ROUTE, NR3 HYDR SYS LO PRESS. LIGHT CAME (ON) AND QTY READ 2 PERCENT. ACFT RETURNED TO BASE. INVESTI	GATION SHOWED A (BLOWN) SEAL ON PRIORITY VALVE IN  THE LANDING GEAR WHEEL WELL. O-RING FOUND DETERIORATED.  REPLACED O-R	ING, FUNCTION TESTED AND RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081120		NM  	2008	11	20	CA080903007      	1	20080208	G	5320	HL10878	COLLAR          			BOEING	777   	777222      	1385219	NM  										FASTENER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			40041								(CAN) FOUND DURING INSP, SEVERAL  HI-LOCK COLLARS CRACKED. ALL HI-LOCK COLLARS REPLACED IAW SRM 51-40-02.						2	L	7	2 	4F			RT	T0001SE 					 
	20081120		SW  	2008	11	20	CA080903008      	1	20080828	G	5610	2719442003	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	CRACKED         	W				I				CABIN DEPRESSURIZATION  				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) CAPTAINS WINDOW SHATTERED ON DECENT DURING FINAL LEG INTO BASE. SHORTLY AFTER ENTERING CLOUD WITH ICING. W/S HEAT 	WAS ON LOW. MAINT REPLACED THE WINDSHEILD. NO EXTERNAL DAMAGE COULD BE FOUND ON THE WINDOW WHICH MAY HAVE CAUSED THE FAI	LURE. THE TREND OF PREMATURE FAILURES OF THESE WINDOWS FOR THIS OPERATOR CONTINUES AS IS LIKEY CAUSED DUE TO SUBSTANDARD	 PARTS.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081120			2008	11	20	CA080903009      	1	20080903	G	3411		FITTING         								GARRTT	TFE731	TFE73140    	29001	NE  					PITOT/STATIC SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT AN AUTO SLAT CHECK, DURING AN A-CHECK, THE STATIC SYS WAS REQUIRED TO SIMULATE 25,000 FT AGL. A	N EXCESSIVE LEAK RATE WAS NOTICED ON THE NR1 SIDE AND ISOLATED TO THE FLEX LINE AT THE NR1 ADC STATIC FITTING. UPON FIND	ING THE NR1 SYS PROBLEM THE NR2 SYS WAS ALSO CHECKED AND THE SAME LINE ON THE NR2 SIDE WAS ALSO FOUND DEFECTIVE.									4	F			E1NM				 
	20081120		SW  	2008	11	20	CA080903010      	1	20080828	G	5610	2719442003	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	CRACKED         	W				I				CABIN DEPRESSURIZATION  				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) ON DESCENT AT APPROX 13000FT THE LT HEATED WINDSHIELD CRACKED. MAINT REPLACED THE WINDSHEILD AND NO PREXISTING DAM	AGE WAS FOUND WHICH WOULD HAVE CONTRIBUTED TO THE WINDOW CRACKING. PREMATURE FAILURE OF THESE WINDOWS IS NOT UNCOMMON.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081120		NM  	2008	11	20	CA080903011      	1	20080903	G	2913	6617303	SHAFT           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYDRAULIC PUMP	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) DURING DESCENT ENGINE THE NR2 HYDR PUMP CAUTION LIGHT CAME ON ACFT CONTINUE NORMAL LANDING. NR2 HYDR PRESS BEING M	AINTAINED BY PTU MAINT. FOUND EDP SHAFT SHEARED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081120		EA  	2008	11	20	CA080903012      	1	20080827	G	2810	215640014	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	LT WING	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1744 								(CAN) FUEL LEAKING FROM LT WING.  FUEL CELLS REMOVED LEAK CHECKED.  FUEL CELL NR1 FAILED LEAK CHECK.  CELL REINSTALLED, 	SYS LEAK CHECKED FOUND SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
	20081118		EA  	2008	11	18	CA080903013      	1	20080827	G	2810	215640024	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  					LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1744 								(CAN) FUEL LEAKING FROM LT WING. FUEL CELLS REMOVED LEAK CHECKED. FUEL CELL NR 3 FAILED LEAK CHECK. NEW CELL INSTALLED S	YSTEM LEAK CHECKED AND FOUND SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
	20081118		EA  	2008	11	18	CA080903014      	1	20080827	G	2810	K215T6400212	FUEL CELL       			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  					LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAKING FROM LT WING. FUEL CELLS REMOVED LEAK CHECKED. FUEL CELL NR 4 FAILED LEAK CHECK. NEW CELL INSTALLED S	YSTEM LEAK CHECKED AND FOUND SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
	20081118		WP  	2008	11	18	CA080903015      	1	20080816	G	2435		GEAR            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			277  								(CAN) STARTER TEETH FOUND WORN, REPLACED WITH A SERVICEABLE STARTER.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118			2008	11	18	CA080903016      	2	20080903	G	7414		ROTOR           	SLICK       																MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			135  								(CAN) CUSTOMER RETURNED MAG FOR WARRANTY PURPOSES. MAG ROTOR SHAFT WAS BROKEN BETWEEN THE DRIVE END BEARING AND THE MAGN	ET PORTION. THE BREAK STILL ALLOWED THE ROTOR TO SPIN BUT THE ROTOR STARTED TO CONTACT THE HOUSING. THE CUSTOMER CLAIMS 	THAT THIS IS THE SECOND MAG THEY HAVE SEEN WITH THIS TYPE OF FAILURE. THIS MAG HAD THE NAS1149CO632R WASHER INSTALLED UN	DER THE DRIVE GEAR AS PER TCM SB03-7. THE HUB WAS INSPECTED AS PER SLICK SB1-07 AND NO CRACKING WAS FOUND. MAG WAS RETUR	NED TO MANUFACTURER FOR FURTHER INVESTIGATION.															 
	20081118			2008	11	18	CA080904001      	4	20080902	G	2562		BATTERY         																	ELT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ELT WAS FUNCTION TESTED DURING ROUTINE SCHEDULED INSPECTION AND WOULD NOT TRANSMIT. SUBSEQUENT INSPECTION AT AVION	ICS SHOP REVEALED LEAKING BATTERY.																		 
	20081118		CE  	2008	11	18	CA080904002      	1	20080826	G	3060		BOOT            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	MCAULY	3D36C	B3D36C432   	GL  	PROP DEICE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			523  								(CAN) DEICE BOOT RETAINING STRAP SEPARATING FROM NR 3 BLADE, DISCOVERED DURING ANNUAL INSP. (AT ELECTRICAL LEAD AREA). N	R 3 DEICE BOOT REPLACED.  MCCAULEY SL2006-5 PERFORMED ON ALL 3 BOOTS.					1	H	7	1 	3O	3	O	RT	A4CE    	E14EA	5	C	P58GL	 
	20081219		WP  	2008	12	19	CA080904003      	1	20080901	G	6310	C1883	SPRAG CLUTCH    			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	DAMAGED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			3773 	1921 							(CAN) UNTIL THE OFFICIAL REPORT ARRIVES, THIS IS WHAT IS DETERMINED HAPPENED. DURING TAKEOFF THE PILOT EXPERIENCED A LOU	D NOISE AND THEN ACFT YAWED SLIGHTLY.  THE ACFT LANDED WITHOUT INCIDENT.  THE CLUTCH WAS REPLACED AND ACFT RETURNED TO S	ERVICE.  DETAILS WILL BE BROUGHT FORWARD ONCE THE CLUTCH IS DISASSEMBLED AND A TEAR DOWN REPORT IS AVAILABLE.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081118		EU  	2008	11	18	CA080904004      	1	20080903	G	3210	9321921210	BOLT            	PILATS      		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PIVOT PIN	BROKEN          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			322  								(CAN) ON TAKE OFF THE PILOTS NOTED AN AIR/GROUND LIGHT ON AND THE GEAR WAS UNABLE TO RETRACT. THE PILOTS RETURNED TO THE	 AIRPORT AND MX LOOKED AT THE PROBLEM. THE ACFT WAS PLACED UP ON JACKS AND UPON INSPECTION IT WAS NOTED THAT 1 OF THE WE	IGHT ON WHEEL SWITCHES WAS MAKING CONTACT WITH THE TARGET. THE WOW SWITCH WHICH WAS MAKING CONTACT WAS INSPECTED CLOSER 	AND FOUND THAT THE PIVOT PIN HAD TWISTED. THE PIVOT PIN IS HELD IN PLACE WITH A BOLT AND THE BOLT WAS FOUND SHEARED INTO	 3 PIECES. THE BOLT HEAD AND NUT WAS HELD IN PLACE BY THE SEALANT THAT PREVENTS WATER ENTERING ALONG THE BOLT. THE PIVOT	 PIN WAS REMOVED AND THE SHANK OF THE BOLT WAS REMOVED AND THE GEAR WAS VISUALLY INSPECTED AND FOUND SERVICEABLE. A NEW 	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081118		EA  	2008	11	18	CA080904006      	2	20080904	G	7414		COIL            	BENDIX      		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MAGNETO	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				463  							(CAN) MAG WAS RECEIVED FOR 500 HOUR INSPECTION. WHEN DISASSEMBLED THE COIL TAB WAS FOUND TO BE BENT DOWN AND ALMOST TOUC	HING THE INSULATION COVERING THE COIL (APPROX. 10 DEGREES). THE CARBON BRUSH HAD WORN THE EXTERNAL EDGE ONLY. THIS TAB I	S SUPPOSED TO BE LEVEL + OR - 5 DEGREES. THE TAB WAS BENT BACK UP DURING THE 500 HOUR INSPECTION AND RETURNED TO SERVICE	.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20081119			2008	11	19	CA080905001      	1	20080903	G	3246	9595601143	GROMMET         	BFGOODRICH  																MLG WHEEL	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) VALVE STEM GROMMET SEAL PN TRRG30 WAS CROSS REFERENCED THEN ORDERED FROM AN ACFT MANUFACTURE SUPPLIER USING THE CR	OSS REFERENCE NR OF 959.56.01.143. A BAG OF 10 SEALS WERE RECEIVED AS LABELED 959.56.01.143 ON THE OUTER PACKAGING. A VI	SUAL CONFIRMATION AT A LATER DATE DETERMINED THAT THE PACKAGING RECEIVED FROM THE SUPPLIER ACTUALLY CONTAINED VENDOR PN 	TRRG6 SEALS. THE REMAINDER OF THE STOCK WAS PULLED AND THE SUPPLIER NOTIFIED. 1 SEAL HAD BEEN ISSUED TO A WHEEL REPAIR. 	THE WHEEL WAS PULLED FROM STOCK AND THE SEAL WAS REPLACED WITH THE CORRECT SEAL. THE TRRG6 SEAL AND THE CORRECT PN TRRG3	0 (959.56.01.143) SEAL WERE NOTED VERY SIMILAR IN SIZE AND APPEARANCE. THE SUPPLIER WAS NOTIFIED, AN INVESTIGATION REVEA														 
	20081119		EA  	2008	11	19	CA080905002      	1	20080902	G	2497	M275008SP3U00	WIRE HARNESS    	HAMFLU      	761339D     	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					ADG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19543								(CAN) FOLLOWING THE COMPLETION OF AD CF2008-09, WHILE PERFORMING A FUNCTION CHECK OF THE AIR DRIVEN GENERATOR, 2 OF THE 	3 MAIN FEED WIRES WERE FOUND BROKEN AFT OF THE CONNECTOR P1XC.   CLOSER INSPECTION OF THE WIRES REVEALED PITTING CORROSI	ON AND BREAK IN SEVERAL STRANDS OF THE WIRES. ALL 3 WIRES WERE REPLACED AS AN ASSEMBLY P/N M27500-8SP3U00.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081119		NE  	2008	11	19	CA080905003      	2	20080903	G	7530	658385	CONTROLLER      			BOEING	727   	727260      	138408K	NM  	PWA   	JT8   	JT8D17      	52049	NE  					BLEED SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AT FL300, TOP OF DESCENT, AS THRUST REDUCTION COMMENCED, LARGE BANG WAS EXPERIENCED BY THE FLIGHT CREW WITH FLUCTU	ATIONS IN NR 2 ENGINE PARAMETERS. ENGINE WAS IDLED FOR THE REMAINDER OF THE FLIGHT AND SHUT DOWN UPON LANDING.  MX PERSO	NNEL CARRIED OUT TROUBLESHOOTING AND THE PRESSURE RATIO BLEED CONTROLLER WAS REPLACED.  THE PRBC HAS BEEN SENT TO AN OVE	RHAUL FACILITY AND AWAITING COMPLETE STRIP REPORT TO VERIFY DEFECTIVE PRBC.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
	20081119		SW  	2008	11	19	CA080905004      	1	20080904	G	2497		WIRE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	29081	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	MASTER SWITCH	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) RT AVIONICS AUX MASTER SWITCH WAS SELECTED ON AND SMOKE WAS NOTICED WITHIN 5 SECONDS. SWITCH WAS SELECTED OFF AND 	SMOKE STOPPED. NO OTHER ABNORMALITIES WERE NOTICED EXCEPT VISUAL BLACK DISCOLORATION ON F/O PHONE JACK OF HEADSET. THIS 	OCCURRED ON THE GROUND IN BETWEEN FLIGHTS. MX WAS DISPATCHED AND FOUND THAT THE WIRING FROM THE AUX AVIONICS SWITCH WAS 	BURNT AND ALSO 1 WIRE FROM THE 50AMP CB WAS BURNT. ALL AFFECTED WIRING WAS REPLACED AND ALL SYSTEMS AFFECTED TESTED AND 	NO FURTHER FAULTS FOUND. SUSPECT WIRE FROM AUX SWITCH CHAFED AGAINST 50AMP CB WIRE.		2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081119		NE  	2008	11	19	CA080905005      	2	20080824	G	7250		TURBINE BLADES  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	FRACTURED       	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y	A		ENGINE STOPPAGE           	FLAME/FIRE                		CR	CRUISE         	1			CA											(CAN) APPROX 45 MINUTES INTO THE FLIGHT PILOT REPORTED ENGINE TROUBLE AND WAS ATTEMPTING AN EMERGENCY LANDING. CONTROL O	F THE ACFT WAS LOST DURING LANDING AND THERE WAS A POST CRASH FIRE. EXAMINATION OF THE ENGINE REVEALED FRACTURED COMPRES	SOR TURBINE (CT) BLADES. CT BLADES ARE ORIGINAL TO ENGINE MFG. MFG HAS REQUESTED COMPRESSOR TURBINE DISK AND BLADES TO B	E RETURNED FOR ANALYSIS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081222		NE  	2008	12	22	CA080905006      	2	20080904	G	7323	B2475	GOVERNOR        			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			1557 								(CAN) PILOT WAS LANDING THE ACFT AND THE RPM DROPPED DUE TO THE GOVERNOR NOT HOLDING THE REQUIRED RPM, GOVERNOR REPLACED	.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081119		CE  	2008	11	19	CA080905007      	1	20080904	G	5220		TAB             			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					EMERGENCY EXIT	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1206 	1206 							(CAN)  EMERGENCY EXIT DOOR LATCH APPEARS AS THOUGH THE LATCH TAB HAD BEEN BENT SO THAT IT COULD BE INSTALLED IN THIS MAN	NER. IN THIS MODE, THE LATCH CAN ALWAYS (EVEN WHEN PRESSURIZED) BE OPENED AS THE TAB PASSES OVER THE SAFETY PLUNGER. THE	 TAB SHOULD CONTACT THE PLUNGER WHEN PRESSURIZED AND ENTER THE SLOT FURTHER DOWN THE PLUNGER SHAFT WHEN THE PLUNGER IS P	ROTRUDING IN THE UNPRESSURIZED MODE.  REMOVING THE LATCH ASSEMBLY AND REPOSITIONING THE STEEL TAB TO CORRECTLY INTERFACE	 WITH THE PLUNGER HAS FIXED THE PROBLEM AND THE ASSEMBLY IS NOW SERVICEABLE. WE OPINED THAT THIS CONDITION LIKELY EXISTE	D SINCE MANUFACTURE. AN INSPECTION OF THE REMAINDER OF OUR FLEET FOR THIS CONDITION REVEALED NO OTHER FAULTS.	1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
	20081119		SW  	2008	11	19	CA080905008      	1	20080902	G	2150	20475546	A/C PACK        			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	29073	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	LT	DAMAGED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE PILOT NOTICED SMOKE COMING OUT OF FRESH AIR VENTS AND MOMENTS LATER LT WING OVERHEAT LIGHT CAME O	N. ACFT LANDED WITHOUT INCIDENT. MX WENT TO LOOK AND FOUND THAT THE LT COOLING TURBINE HAD A CATASTROPHIC FAILURE. THE L	T BLEED SYSTEM WAS MEL`D AND DISABLED. NUMEROUS RUNS WERE COMPLETED WITH NO FURTHER SMOKE COMING INTO CABIN.				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081119		SO  	2008	11	19	CA080908001      	1	20080829	G	7120	6666200	MOUNT           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7948 								(CAN) CRACKS WHERE TUBES ARE WELDED TO NOSE STRUT. CHAFING WHERE AERO DUCT HOSE TOUCHED MOUNT.						1	L	7	1 	3O	3	O		2A13    	E274				 
	20081119		EA  	2008	11	19	CA080908002      	2	20080827	G	7414	K3975	COIL            	SLICK       		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					MAGNETO	OPEN            	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			1895 								(CAN) PILOTS NOTED A DEAD LT MAGNETO WHEN PERFORMING PRE FLIGHT RUNUP. MAGNETO WAS REMOVED AND DISASSEMBLED AND FOUND TH	AT THE COIL SECONDARY WINDING WAS OPEN CIRCUIT (SHOULD BE BETWEEN 1500-20,000) - MANGETO WAS REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081119		CE  	2008	11	19	CA080908003      	1	20080902	G	2810	1183810021	FLOAT VALVE     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  					FUEL CELL	DISLODGED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			757  								(CAN) ATTACH PIN MIGRATED OFF ALLOWING FLOAT TO BECOME DISLODGED FROM FLOAT VALVE PIN 118-381002-1. ATTACH PIN MIGRATED 	TO ORIGINAL POSITION AFTER FLOAT BECAME DISLODGED. THE FLOAT WAS LOCATED AT THE RT FUEL FILLER. THE NEW VALVE WAS DATED 	IN 2000 WHILE THE DEFECTIVE VALVE WAS DATED JULY, 2005. THE NEW VALVE WAS OF A DIFFERENT CONSTRUCTION IN THE ATTACH PIN 	AREA LESS CONDUCIVE TO ALLOWING DISLODGING OF THE FLOAT.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081119		NM  	2008	11	19	CA080908004      	1	20080902	G	2722	2334003001	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RUDDER	BYPASSING       	W				O				OTHER                   				F	G		FLT CONT AFFECTED         	MULTIPLE FAILURE          		NR	NOT REPORTED   	1			CA			41801	41801							(CAN) FLT CREW REPORTED RUDDER TRIM INDICATOR SHOWS 40% RT DEFLECTION TO CENTRE BALL ON HSI. MX REPLACED THE RUDDER TRIM	 ACTUATOR AND CHECKED SYSTEM SERVICEABLE. ON THE NEXT FLIGHT THE CREW REPORTED NO APPRECIABLE CHANGE AND THAT IT APPEARE	D THEY WERE CROSS CONTROLLING THE ACFT WITH THE TRIMS.  MX DISCOVERED THAT BOTH THE NR 1 AND 2 SYSTEM RUDDER ACTUATORS W	ERE INTERNALLY BYPASSING FLUID. MX WAS ABLE TO MOVE RUDDER BY HAND EVEN WITH FULL HYDRAULIC SYSTEM PRESSURE. BOTH RUDDER	 ACTUATORS PN 233400-3001, SN 0575 (NR 1), SN 0580 (NR 2), IPC 27-20-00 FIG 5, ITEM 618 WERE REPLACED AND OPS, FUNCTIONA	L AND LEAK CHECKS COMPLETED. RUDDER CABLES TENSIONED. ACFT TEST FLOWN SATISFACTORILY AND RETURNED TO SERVICE. NOTE:MX TA	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081119		EU  	2008	11	19	CA080908005      	1	20080908	G	5753	Z4243300014	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					FLAP SPRING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP SPRING LOCK WAS DISCOVERED CRACKED DURING SCHEDULED MX. SPRING BROKE COMPLETELY DURING REMOVAL.						1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
	20081119		SW  	2008	11	19	CA080908006      	1	20080507	G	6320	430040003	TRANSMISSION    			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	DAMAGED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			C	J		F.O.D.                    	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE FROM AN OIL RIG , THE PILOT HEARD A LOUD BANG AND THE ACFT YAWED LT AND RT AND WAS FOLLOWED BY A L	OUD RUMBLING SOUND. THE COCKPIT INDICATION SHOWED THAT THE ACFT HAS A TRANSMISSION CHIP AND A CHIP SUMP CAUTION. THE PIL	OT DESCENDED DOWN TO APPROXIMATELY 400 FEET READY TO PREPARE FOR DITCHING. AFTER APPROXIMATELY 1 1/2 TO 2 MINUTES, THE R	UMBLING STOPPED AND THE ACFT NOISE WENT BACK TO NORMAL. THE PILOT PROCEEDED TO LAND WITHOUT EVENT AND SHUT DOWN THE HELI	COPTER. AFTER INSPECTION, NUMEROUS CHIPS AND FLAKES OF METAL ON THE SUMP PUMP CHIP DETECTOR, COLLECTOR GEAR DETECTOR AND	 THE MAGNETIC DRAIN PLUG. SOME METAL FOUND ON THE LT INPUT QUILL CHIP DETECTOR AND IN THE OIL FILTER. TRANSMISSION WILL 	1	G	7	2 	3U			RT	H9SW    					 
	20081119		SO  	2008	11	19	CA080908007      	2	20080828	G	8530	07502385AWL	RISER           			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 5 CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			680  								(CAN) DURING 100 HOUR INSPECTION AME FOUND RT EXHAUST STACK CRACKED AT NR 5 CYLINDER, PART WAS REPLACED WITH PART NR 075	0161-31.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
	20081119		EA  	2008	11	19	CA080908008      	2	20080906	G	8530	AEL85099	CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	NR 1	SEPARATED       	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			2577 	2577 							(CAN) ACFT WAS CLIMBING OUT ON A TRAINING FLIGHT. SHORTLY AFTER HEARD A LOUD BANG AND RPM DROPPED TO APPROX 1200. TURNED	 BACK AND LANDED SAFELY FOUND THE NR1 CYL HEAD SEPARATED FROM THE BARREL WITH APPROX 1 INCH OF BARREL EXPOSED PAST THE C	YLINDER FINS. NR1 INTAKE LIFTER WAS DAMAGED AS WELL AS THE ENG CRANKCASE, ENG REMOVED FOR OVERHAUL. ENG WAS OPERATING ON	 AN ON-CONDITION PROGRAM. (@2567 HOURS, TBO IS 2000) FIRST FAILURE OF THIS TYPE. CYL WAS NOT AFFECTED BY AD 2006-12-07 A	ND WAS IN FACT NOTED AS AN ACCEPTABLE REPLACEMENT CYLINDER FOR THE PN MENTIONED IN THE AD. ENGINE WAS INSTALLED IN THIS 	AIRFRAME. REPLACED ORIGINAL ENGINE.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081124		CE  	2008	11	24	CA080908009      	1	20080908	G	5511	12326212	SPAR            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION AN AME FOUND THAT THE RT AND LT REAR SPAR WAS HEAVILY CORRODED (LEVEL 3) AND CRACKED 	UNDER THE OTBD HINGE BRACKET.					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
	20081124		CE  	2008	11	24	CA080908010      	1	20080808	G	5312	071111229	BULKHEAD        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING NON-ROUTINE MX REPAIRS AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER RT CORNER AT REAR FLOAT FITTING. CUSTOMER	 WAS NOTIFIED.					1	H	7	1 	3O	3	O		3A24    	E3SO				 
	20081124		CE  	2008	11	24	CA080909001      	1	20080907	G	2435		COOLING FAN     	TRW         		BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					STARTER GEN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1581 	662  							(CAN) WHILE PERFORMING AN INSPECTION, THE ENGINEER PULLED THE STARTER-GENERATOR AND NOTICED THE COOLING FAN BROKEN. UPON	 FURTHER INVESTIGATION, THE ENGINEER NOTICED THAT 1 OF THE BROKEN FAN BLADES WAS PROVIDING A GROUND PATH INTERNALLY BETW	EEN THE GENERATOR AND THE CASE.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
	20081124			2008	11	24	CA080909003      	2	20080909	G	7414	M3611	CAM             	SLICK       																MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAG WAS INSTALLED ON AN OVERHAULED ENGINE APPROX. 1 YEAR AGO, CUSTOMER HAS YET TO INFORM US AS TO HOURS ON UNIT. T	HE MAG WAS DISASSEMBLED FOR INSPECTION AND THE CAM THAT OPENS THE CONTACT POINTS WAS FOUND TO BE EXCESSIVELY WORN. THIS 	IS COVERED BY SLICK BULLETIN SB2-08. THE CAM WAS WORN TO THE EXTENT THAT IT WAS BARELY OPENING THE POINTS. THE MAG WAS R	ETURNED TO UNISON/SLICK FOR INSPECTION.																 
	20081124			2008	11	24	CA080909004      	2	20080909	G	7414	M3611	CAM             	SLICK       																LOBES	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) (2ND MAG) MAG WAS INSTALLED ON AN OVERHAULED ENGINE APPROX. 1 YEAR AGO. CUSTOMER HAS YET TO INFORM US AS TO HOURS 	ON UNIT. THE MAG WAS DISASSEMBLED FOR INSPECTION AND THE CAM THAT OPENS THE POINTS WAS FOUND TO BE EXCESSIVELY WORN. THI	S IS COVERED BY SLICK BULLETIN SB2-08. THE CAM WAS WORN TO THE EXTENT THAT IT WAS BARELY OPENING THE POINTS. THE MAG WAS	 RETURNED TO UNISON/SLICK FOR INSPECTION.																 
	20081124		EA  	2008	11	24	CA080909005      	1	20080819	G	2750	1104SD1201	SHAFT           			CNDAIR	CL600 	CL6002B19   	1900309	EA  										TE FLAPS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			20680								(CAN) AFTER LANDING AND ON RETRACTION OF THE FLAPS, THE CREW RECEIVED A FLAP FAIL CAUTION MSG.  PIREP: FLAP FAIL CAUTION	. WHEN FLAP SELECTOR MOVED FROM 45 DEG TO 8 DEG, FLAPS STOPPED AT THE 22 DEG POSITION.  MX EXAMINED THE FLAPS AT THE GAT	E AND DETERMINED THAT THERE WAS EVIDENCE OF OIL CANNING ON THE TOP SURFACE SKIN OF THE RT INBD FLAP. THE ACFT WAS TAKEN 	OUT OF SERVICE AND PROCESSED TO THE HANGAR FOR FURTHER INVESTIGATION.  LOCATED A BROKEN FLEX SHAFT TIP AT THE INBD SIDE 	OF THE OTBD ACTUATOR FOR THE INBD FLAP. ALL DAMAGED PARTS INCLUDING THE FLAP SURFACE WERE REPLACED.		2	L	7	2 	4F			RT	A21EA   					 
	20081124		CE  	2008	11	24	CA080910001      	1	20080903	G	7160	155212914	INTAKE DUCT     			CESSNA	337   	337F        	2075725	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  		CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA			2712 								(CAN) DURING A ROUTINE PATROL FLIGHT THE PILOT EXPERIENCED A VIBRATION IN THE AREA OF THE REAR ENGINE. HE ELECTED TO RET	URN TO THE AIRPORT AND MADE AN UNSCHEDULED LANDING WITHOUT INCIDENT. UPON INSPECTION BY THE MX CREW, IT WAS DISCOVERED T	HAT THE FWD EDGE OF THE INNER & OUTER SECTIONS OF THE AIR COOLING DUCT HAD PARTIALLY SEPARATED FROM THE NOSE CAP. THIS A	LLOWED ROM AIR TO FLOW BETWEEN THE INNER & OUTER SECTIONS AND CAUSED THE INNER DUCT TO VIBRATE AND SUBSEQUENTLY CRACK & 	BREAK.		1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
	20081124		WP  	2008	11	24	CA080910002      	1	20080818	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			345  								(CAN) THE STARTER WAS NOT CRANKING OVER ENGINE, STARTER REPLACED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081124		SO  	2008	11	24	CA080910003      	2	20080715	G	8520		COTTER PIN      	CONT        							CONT  	O200  	O200A       	17020	SO  					CONNECTING ROD	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NO COTTER PINS IN ANY OF THE 8 CON-ROD BOLTS DISCOVERED UPON DISMANTLE FOR PROPELLER STRIKE INSPECTION.											3	O			E252				 
	20081119		NE  	2008	11	19	CA080910004      	2	20080909	G	7530		SWITCH          			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					NR 2	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING THE DEPARTURE, THE FLIGHT HAD A NR2 BLEED VALVE FAILURE INDICATION WHICH WAS RESET. AND THEN FAILED AGAIN, 	FOLLOWED WITHIN 2 MINUTES WITH A BLEED NR1 FAILURE. QRH PROCEEDURES WERE FOLLOWED AND THE FLIGHT RETURNED TO LAND. THE F	LIGHT WAS NOT OVERWEIGHT FOR LANDING AND THERE WAS NO EMERGENCY DECLARED.   BLEED NR1 FAULT CODE HAS BEEN TROUBLESHOT. B	LEED O/P SWITCH NR2 REPLACED IAW AMM. TORQUE MOTOR LINES TO VALVE CHECKED OK.			2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081119		SW  	2008	11	19	CA080910005      	1	20080709	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					T/R DRIVESHAFT	CRACKED         	W				O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			CA											(CAN) FOUND (3) DISCS CRACKED AND ALL DISCS CORRODED ON THE FWD NR 1 POSITION.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20081119		NE  	2008	11	19	CA080910006      	2	20080820	G	7314	C8187B	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			993  								(CAN) FUEL PUMP ELECTRICALLY MALFUNCTIONING, REPLACED FUEL PUMP.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081126		SO  	2008	11	26	CA080911001      	1	20080908	G	8120	89682002	SHROUD          			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					AIR PUMP	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			2626 								(CAN) THE LWR AIRPUMP COOLING SHROUD ASSY, ALTHOUGH NOT LOOSE TO THE TOUCH, WAS ABLE TO ROTATE WITH A LIGHT TO MODERATE 	PUSH.   THIS ROTATION ALLOWED THE AIR INLET DUCT AND CLAMP TO CONTACT THE LINKAGE ON THE TURBO CONTROLLER. THE SHROUD RO	TATION OCCURRED DURING FULL POWER, THIS TRAPPED THE LINKAGE ON THE TURBO CONTROLLER IN THE CLIMB POWER POSITION.  THE LO	WER AIRPUMP COOLING SHROUD ASSEMBLY(P/N 89682-002), ROD(P/N 89682-008), HOSE (P/N 89684-002), AND CLAMP(P/N 5544-896) WE	RE REPLACED WITH NEW. THE NEW SHROUD AND CLAMP WERE POSITIONED TO PROVIDE MAXIMUM CLEARANCE TO THE TURBO CONTROLLER. THE	 NEW SHROUD AND ROD FIT IS MORE SECURE TO PREVENT FURTHER ROTATION.  AN ENGINE GROUND RUN WAS CARRIED OUT SATISFACTORILY	1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
	20081119		EA  	2008	11	19	CA080911002      	1	20080909	G	5610	601R330339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				K				NONE                    				Z			SIGNIFICANT FAILURE REPORT			DE	DESCENT        	1			CA			18238	18238							(CAN) ON DESCENT THE LT WINDSHIELD CRACKED AT FL370 AND THE LT WINDSCREEN HEAT CAUTION CAME ON. AN EMERGENCY WAS DECLARE	D, BUT THE A/C LANDED WITHOUT INCIDENT. THIS WINDSHIELD HAD OVER 18,000 HRS AND WAS WELL ABOVE THE AVERAGE FOR NORMAL FA	ILURE RATES.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081119		NM  	2008	11	19	CA080911003      	1	20080905	G	2782	1U1110	ACTUATOR        			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					KRUEGER FLAP	FAILED          	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THROUGH APPROX 2,000 FT NR1 ENGINE LOW HYDR PRESSURE LIGHT ILLUMINATED, SYS `A` HYDRAULIC OIL AND PRE	SSURE LOSS. ACFT RETURNED TO DEPARTURE. NR5 KRUGER FLAP ACTUATOR FOUND FAILED AND ATTACH BRACKET DAMAGED. REPLACED ACTUA	TOR AND TESTED IAW AMM 29-11-00 AND 27-81-22. KRUEGER FLAP ATTACH BRACKET REPAIRED IAW SRM 51-10-2. ACFT RETURNED TO SER	VICE.			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081119		EU  	2008	11	19	CA080911004      	1	20080908	G	3220	5322012165	BARREL NUT      	PILATS      	532001203   	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NLG OLEO WAS STICKING AND NOT EXTENDING WHEN GEAR UP WAS SELECTED. WITH THE TIRE FALLING SHORT OF THE BACK OF THE 	WHEEL WELL IT MAKE CONTACT WITH THE NOSE GEAR DOOR RODS. BOTH LT AND RT RODS BUSTED OFF LEAVING THE DOORS FLOATING. THE 	NOSE WHEEL BEING SHORT CONTACTED AND RUBBED THE GEAR UP BUMPER AND LIGHTLY TOUCHED THE RT GEARDOOR LEAVING A BLACK RUBBE	R MARK. UPON INSP, IT WAS FOUND THAT THE BARREL NUT STARTED TO CORRODE INTERNALLY UNDER THE PHENOLIC BUSHING FORCING THE	 PHENOLIC BUSHING AGAINST THE OLEO. BARREL NUT AND SEALS REPLACED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081126		NM  	2008	11	26	CA080911005      	1	20080911	G	7920	443330	O-RING          			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					GEARBOX OIL	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) WHILE CLIMBING OUT, NOTICED ENG NR 1 OIL QUANTITY INDICATOR SLOWLY DECREASING, QUANTITY  WAS 1 GALLON AT TOP OF CL	IMB. AT MID POINT, QUANTITY DECREASED TOWARD ZERO. ENGINE SHUTDOWN DRILL AND CHECK LIST COMPLETED.  ENGINE  WINDMILLING 	SUPPLEMENT COMPLETED PRIOR TO DESCENT.  ALL OTHER ENGINE INDICATIONS NORMAL PRIOR TO SHUTDOWN.  OPENED COWLING ON NR 1 E	NG, CHECKED FOR OIL LEAK, NOTHING OBVIOUS, ADDED 12 QUARTS OF OIL IAW MM  12-13-001-2.  NR 1 ENG RUN AT IDLE TO LEAK CHE	CK,  SIGNIFICANT OIL LEAK FROM GEARBOX TO OIL  COOLER TUBE. FOUND OIL LINE HAD TENSION ON IT WHEN REMOVING TUBE. SEAL SP	LIT AND REAR PIECE MISSING.  PROCURED SEAL P/N 443330 (REV.A).  CPN 0043234 INSTALLED SEAL AND REPOSITIONED TUBE, REMOVE	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081119		NE  	2008	11	19	CA080911006      	2	20080904	G	7200	JT8D9A	ENGINE          			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2	FAILED          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			54469	1313 							(CAN) AFTER T/O AND CLIMB OUT, NR2 ENGINE LOST OIL QTY AND OIL TEMP ROSE RAPIDLY INTO RED INDICATION. INFLIGHT SHUTDOWN 	COMPLIED WITH AND ACFT RETURNED TO DEPARTURE. NR2 ENGINE REPLACED IAW AMM AND KFL TASK CARDS, ACFT RETURNED TO SERVICE. 	ENGINE TO BE EVALUATED IN ENGINE SHOP FOR CAUSE.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081119		NE  	2008	11	19	CA080912001      	2	20080825	G	7321		ECU             								PWA   	PW121 	PW121       	52124	NE  					NR 1 ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J	X		WARNING INDICATION        	ENGINE FLAMEOUT           		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE PILOT NOTICED FLUCTUATION OF NR1 ENGINE PARAMETERS. WHILE ATTEMPTING TO ADJUST PROPELLER SPEED,	 ENGINE FLAMED OUT. AN ATTEMPT TO RESTART ENGINE IN-FLIGHT WAS NOT SUCCESSFUL. DURING GROUND INSP, ALL ENGINE PARAMETERS	 FLUCTUATED WITH ECU "ON" AND ALL PARAMETERS STABLIZED WITH ECU "OFF". THE ECU WAS REPLACED.									4	T			E20NE				 
	20081119		NE  	2008	11	19	CA080912002      	2	20080826	G	7320		HMU             			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN) ACFT EXPERIENCED LOSS OF POWER TO FLIGHT IDLE (FI) ON LT ENGINE DURING FLIGHT WHICH LEAD TO A COMMANDED ENGINE IN-	FLIGHT SHUTDOWN + RESTART WITH INABILITY TO GO ABOVE FI. FLIGHT WAS DIVERTED WHERE THE A/C LANDED WITH THE LT ENGINE AT 	FI POWER. EXTENSIVE TROUBLESHOOTING LED TO HMU REPLACEMENT. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT	 CAUSE ONCE ESTABLISHED.			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
	20081119		EA  	2008	11	19	CA080912003      	2	20080902	G	8530	SL11625	PLUG            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1300 								(CAN) THE PISTON PIN PLUGS IN TWO CYLINDERS ON THE ENGINE WORE UNUSUALLY AND CAUSED ALUMINUM METAL CONTAMINATION THROUGH	OUT THE ENGINE.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081119		CE  	2008	11	19	CA080912004      	1	20080912	G	5753	3516505030	HINGE BRACKET   			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	TE FLAP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE REPLACEMENT OF THE REAR SPAR LT BRACKET, THE LT OTBD FLAP WAS REMOVED FOR ACCESS AND FOUND THE INBD HIN	GE OTBD BRACKET WITH DAMAGE CAUSED BY THE ROLLER BEARING FLANGE APROX 0.025 DEEP.  DECIDED TO PERFORM DVI OF ALL REMAINI	NG FLAP ROLLER ASSY AND REMOVE THE RT OTBD FLAP. FOUND THE SAME DAMAGE ON THE RT OTBD FLAP INBD HINGE OTBD BRACKET. INVE	STIGATION SHOWED THAT THE BEARINGS AND FLAPS WERE INSTALLED CORRECTLY. BRACKETS ARE BEING REPLACED.			2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
	20081120		CE  	2008	11	20	CA080912005      	1	20080911	G	2497	10936102247	WIRE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	LT NACELLE	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) LT ENGINE FAILED TO ROTATE ON START UP. MAINT DISCOVERED LT STARTER GEN WIRE FEED THRU ASSY (CONSISTS OF 3 PARALLE	L HEAVY GUAGE WIRES) TERMINAL ENDS BURNED OFF AT START CONTROL PANEL TERMINAL. NEW WIRE FEED THRU ASSY ON ORDER. START C	ONTROL PANEL ON ORDER. WILL CARRY OUT A FLEET WIDE INSP OF LT AND RT NACELLES FOR WIRE FEED THRU TERMINAL ENDS FOR CONDI	TION.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
	20081120		SW  	2008	11	20	CA080912006      	1	20080908	G	7920	991930811	TUBE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	29073	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	OIL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING THE PREFLIGHT WALKAROUND, THE FLIGHT CREW NOTICED OIL DRIPPING FROM THE RT ENGINE. MX WAS DISPATCHED TO THE	 LOCATION WHERE THE STAINLESS STEEL TUBE ASSY FROM THE ENGINE PROP GOVERNOR TO THE NEGATIVE TORQUE SENSING (NTS)MANIFOLD	 WAS FOUND LEAKING. DURING REMOVAL, 1 FLARED END OF THE TUBE WAS FOUND CRACKED 3/4 OF THE WAY AROUND THE CIRCUMFERENCE O	F THE TUBE. TOSL TIME ON THE TUBE COULD NOT BE DETERMINED. THIS SAME PN TUBE HAS BEEN FOUND CRACKED PREVIOUSLY ON OTHER 	ACFT. THE CRACK WAS LIKELY DUE TO IMPROPER ALIGNMENT OF THE TUBE ASSY DURING INSTALLATION ON THE PROP GOVERNOR.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081120			2008	11	20	CA080912007      	1	20080817	G	5210		ATTACH FITTING  	BRAERO      	1371008C409 						GARRTT	TPE331	TPE33110UGR 	29069	NE  					PAX DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SEVERE CORROSION NOTED AT MAIN CABIN DOOR ATTACH FITTINGS. CORROSION ALSO NOTED UNDER SEVERAL DOOR SEAL CLIPS. DOO	R DEEMED BEYOND ECOMONICAL REPAIR AND REPLACED WITH SERVICEABLE UNIT.										4	T			E4WE				 
	20081120			2008	11	20	CA080912008      	1	20080912	G	5210		FITTING         	BRAERO      	1371008C409 						GARRTT	TPE331	TPE33110UGR 	29069	NE  					PAX DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS DOOR WAS INSTALLED AS A REPLACEMENT DUE TO SEVERE CORROSION FOUND ON ORIGINAL DOOR. REPLACEMENT DOOR INSPECTE	D AND CORROSION DISCOVERED UNDER SEVERAL DOOR INFLATION SEAL CLIPS. CLIPS REMOVED AND CORROSION REMOVED AND SURFACES TRE	ATED. CLIPS REINSTALLED.									4	T			E4WE				 
	20081126		GL  	2008	11	26	CA080915006      	1	20080826	G	3260		WARNING LIGHT   			BOMBDR	BD700 	BD7001A10   	1390006	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					MLG	ILLUMINATED     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING FLT, "GEAR SYS FAIL" CAUTION MESSAGE POSTED.  CREW VERIFIED ACTIVE FAULTS IN CAIMS TO FIND LGECU CHANNEL B 	FAILED. CREW PROCEEDED TO PREPARE FOR LANDING FOLLOWING ACFT FLT MANUAL PROCEDURE FOR GEAR SYS FAIL MESSAGE. MANUAL LAND	ING GEAR EXTENSION PROCEDURE WAS CARRIED OUT IAW AFM.  ON APPROACH, ACFT DESCENDED TO AN ALTITUDE OF 500 FEET WHEN ENHAN	CED GROUND PROXIMITY WARNING SYSTEM "TOO LOW GEAR" UN-MUTABLE AURAL WARNING SOUNDED, WHICH PROMPTED PILOT TO GO AROUND A	ND VERIFY THE REASON FOR THIS WARNING. AFTER VERIFICATION CREW MADE A SECOND ATTEMPT ON APPROACH AND THE "TOO LOW GEAR" 	AURAL WARNING SOUNDED AGAIN DISREGARDED BY CREW TO FINALIZE LANDING.  ON TOUCH DOWN, THE PILOT NOTICED THAT THE LT ENGIN	2	L	7	2 	4F	4	F	RT	T00003NY	E00010LA				 
	20081120		WP  	2008	11	20	CA080915007      	1	20080816	G	2822	D7431	PUMP            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					FUEL SYSTEM	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			267  								(CAN) THE AUX FUEL PUMP LIGHT WOULD NOT EXTINGUISH, AUX PUMP REPLACED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081120		EU  	2008	11	20	CA080916001      	1	20080911	G	3233	72MEF20151	SWIVEL FITTING  			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	RT MLG	SHEARED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF, DURING GEAR RETRACTION, THE RT MLG DOWNLOCK ACTUATOR SWIVEL FITTING LOCATED ON THE DRAG BRAC, FAIL	ED. THIS CAUSED A SUBSTANTIAL LOSS OF FLUID.  AN EMERGENCY GEAR EXTENSION WAS CARRIED OUT AND THE ACFT RETURNED TO BASE 	WITH NO FURTHER PROBLEMS.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
	20081120		CE  	2008	11	20	CA080916002      	1	20080806	G	2752		ROLL PIN        	CESSNA      	C1450046RX  	CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TE FLAP	SHEARED         	W				O				OTHER                   				F	P		FLT CONT AFFECTED         	NO WARNING INDICATION     		IN	INSP/MAINT     	1			CA			2998 								(CAN) DURING ROUTINE INSPECTION, STANDBY FLAP SYSTEM OPS DISCOVERED INOPERATIVE (MOTOR TURNING - NO FLAP MOVEMENT). UPON	 FURTHER INVESTIGATION, ROLL PIN SECURING STANDBY DRIVE TO WARM GEAR WAS FOUND TO BE SHEARED RENDERING STAND BY FLAP OPS	 U/S. SUSPECT FAILURE WAS DUE TO AGE OF PART. RECOMMEND TESTING OF STAND BY FLAP SYSTEM PER A/C MAN. N.M. AT EACH INSPEC	TION. IN THIS INSTANCE PRIMARY FLAP OPS WERE NOT AFFECTED.			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
	20081120		EU  	2008	11	20	CA080916004      	1	20080915	G	4940		CONTROL BOX     			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					COCKPIT	DEFECTIVE       	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			12101								(CAN) PILOTS HAVE BEEN REPORTING INTERMITTENT SULPHUR SMELL IN THE ACFT. WHILE TROUBLESHOOTING, THE MECHANIC NOTICED THA	T THE APU DOOR WAS OPEN AND APU MASTER AS OFF. WHEN THE APU SWITCH WAS CYCLED TO CLOSE THE DOOR, SPARKS STARTED TO APPEA	R NEXT TO START SWITCH IN THE COCKPIT. UPON REMOVAL OF THE CONTROL BOX, IT WAS NOTICED THAT THE RUBBER SLEEVE AROUND THE	 START SWITCH WAS MELTED AND THERE WERE SIGNS OF BURNING ON THE WIRES COMING OUT OF THE SWITCH.			2	L	7	3 	4F	4	F		A46EU   	E6WE				 
	20081126			2008	11	26	CA080916005      	4	20080830	G	3457	GNS530430W	GPS             																		MALFUNCTIONED   	W				O				OTHER                   				G	H		MULTIPLE FAILURE          	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA											(CAN) GNS530W AND GNS430W SIMULTANEOUSLY LOOSE SATELLITE RECEPTION. SATELLITES ARE REAQUIRED BETWEEN 2 AND 20 MINUTES LA	TER. EXTENSIVE TROUBLESHOOTING FOUND NO FAULT WITH THE INSTALLATION. MFG PRODUCT SUPPORT INDICATED THAT SIMILAR REPORTS 	HAVE BEEN RECEIVED FROM OPERTORS IN ALASKA AND THE ANOMOLY APPEARS AT AROUND THE LATITUDE OF FAIRBANKS. THERE IS A PROBL	EM WITH THE GNS SOFTWARE AND THE ALASKA WAAS GROUND STATION. THE WAAS ENGINE IN THE GNS NAVIGATOR MUST BE SHUT OFF IN TH	AT AUXILLARY MENU SETUP PAGE TO PREVENT SATELLITE LOSS IN NORTHERN LATTITUDES. THIS INFORMATION IS NOT READILLY AVAILABL	E TO OPERATORS AND OWNERS.														 
	20081222		CE  	2008	12	22	CA080916006      	1	20080912	G	5551	04320049	ATTACH BRACKET  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CARRIED OUT SEB 03-6 ON VERTICAL TAIL ATTACH BRKT AND STAB SPAR. SPAR WAS NOT CRACKED BUT THE STEEL ATTACH BRKT WA	S CRACKED AROUND A RIVET HOLE FOR THE PREVIOUSLY INSTALLED NUT PLATES. AD PREVIOUSLY ALLOWED REMOVAL OF NUT PLATES.  THI	S OPERATOR HAS SEEN AT LEAST TWO OTHER FAILURES OF THIS PART. A/C TT IS ~22,950 HOURS OPERATING IN AN FTU.  REPLACED PAR	T WITH A USED, INSPECTED SERVICEABLE PART DUE TO NO PARTS SUPPORT FROM MFG.   NOTE: NO PICTURE, NOT ABLE TO TAKE A PICTU	RE FROM THE INSIDE OF THE BRACKET.		1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
	20081120		CE  	2008	11	20	CA080916007      	1	20080728	G	2436	C6110040101	VOLT REGULATOR  			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ELECTRICAL SYS	SHORTED         	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) ACFT WAS IN CRUISE FLIGHT WHEN THE PILOT NOTICED THE ELECTRICAL SYSTEM WAS DRAINING THE BATTERY. THE ACFT LANDED A	ND WSA INVESTIGATED BY MX. IT WAS FOUND THAT THE BATTERY WAS DISCHARGED AND THE ELECTROLYTE HAD BOILED FROM THE BATTERY.	 FURTHER INVESTIGATION REVEALED THE VOLTAGE REGULATOR WAS AT FAULT, ALLOWING THE ALTERNATOR TO OVERVOLT THE BATTERY AND 	DESTROY IT. THE BATTERY COMPARTMENT WAS CLEANED AND A NEW BATTERY WAS INSTALLED, A NEW VOLTAGE REGULATOR WAS INSTALLED A	ND A NEW ALTERNATOR WAS ALSO INSTALLED AS A PRECAUTIONARY MEASURE. THE ACFT WAS GROUND RUN & ELECTRICAL SYSTEM CHECKED S	ERVICEABLE.	1	H	7	1 	3O	3	O		A4CE    	E5CE				 
	20081120			2008	11	20	CA080916008      	1	20080913	G	3040		MOTOR           								GARRTT	TPE331	TPE3312201A 	 	WP  					WINDSHIELD	MALFUNCTIONED   	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) SKYVAN EN ROUTE WITH 2 CREW ,1 PASSENGER ON BOARD ADVISED ARCTIC RADIO THEY HAD SMOKE IN COCKPIT, CREW REQUESTED E	MERGENCY VEHICLES, ACFT LANDED SAFELY, CREW AND PASSENGER WERE CHECKED AT LOCAL NURSING STATION AND RELEASED. FURTHER IN	VESTIGATING PROBLEM, IT WAS FOUND THAT THE WINDSHIELD WIPER MOTOR HAD BURNT OUT. WIPER MOTOR WAS REPLACED WITH A SERVICE	ABLE UNIT , FUNCTION CHECKED AND RELEASED BACK TO SERVICE. TOTAL TIME ON WIPER MOTOR UNKNOWN.								4	T			E3WE				 
	20081120			2008	11	20	CA080917001      	1	20080826	G	2820	3014884	TUBE            								PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3219 								(CAN) FUEL FOUND LEAKING ONTO ENGINE DECK FROM AT BRAZE ON BOTTOM "B" NUT FITTING ON TUBE. TUBE LOCATED ON FORWARD FACE 	OF ENGINE ACCESSORY GEARBOX. ACFT WAS GROUNDED UNTIL PART WAS REPLACED.										4	U			E22EA				 
	20081120		EA  	2008	11	20	CA080917002      	1	20080911	G	3213	8A04000021	SUPPORT         		8000FLOATS  	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					MLG AXLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEEL ASSEMBLIES AND BRAKES REMOVED FOR INSPECTION AND REBUILD. IT WAS DISCOVERED THAT THE AXLE SUPPORT BODIES ON 	BOTH MAIN GEAR ASSEMBLIES HAD CRACKS AND REQUIRED REPLACEMENT. THIS WAS FOUND ON A 200 HR. INSPECTION.					1	H	7	1 	3R	4	T		A815    	E4EA				 
	20081126		NM  	2008	11	26	CA080917003      	1	20080916	G	2133	3964401	SHUTOFF VALVE   			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					A/C PACK	FAILED          	W				J	A			DUMP FUEL               	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMBOUT, SEPT 16 2008, PRESSURIZATION FAILED TO OPERATE NORMALLY. WHEN CLIMBING THROUGH 23,000 FT, CABIN A	LTITUDE EXCEEDED 10000 FT. FUEL DUMP CARRIED OUT IN ORDER FOR ACFT TO RETURN TO DEPARTURE.  CABIN PRESSURIZATION LEAK CH	ECK CARRIED OUT, NO FAULTS. PRESSURIZATION CONTROLLER AND PRESSURIZATION CONTROL PANEL REPLACED. GROUND PRESSURIZATION C	HECKS CARRIED OUT WITH NO FAULTS DETECTED. ON SEPT 17, 2008, ACFT WAS DEPARTED. AS THE ACFT CLIMBED THROUGH 25000 FT, CA	BIN PRESSURIZATION FAILED TO OPERATE NORMALLY WITH MINIMAL CONTROL. ACFT RETURNED TO DEPARTURE FOR FURTHER TROUBLESHOOTI	NG. TROUBLESHOOTING REVEALED NO PROBLEMS WITH THE PRESSURIZATION SYS BUT HAS REVEALED THAT THE RT PACK FLOW CONTROL AND 	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081120		CE  	2008	11	20	CA080917004      	1	20080907	G	2750	C3010010211	COUPLING        			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TE FLAP	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) FLAP COUPLING FAILED DURING NORMAL LANDING PROCEDURES. UPON FAILING, THE PART BROKE INTO 2 PIECES, DISCONNECTING T	HE FLAP MOTOR FROM THE ACTUATOR ASSEMBLY. THIS RESULTED IN THE FLAPS STOPPING WHILE PARTIALLY EXTENDED. THE FLAPS WERE L	EFT PARTIALLY EXTENDED FOR LANDING. THE CREW ELECTED NOT TO USE THE STANDBY FLAP MOTOR TO AVOID THE POTENTIAL FOR FURTHE	R DAMAGE TO THE FLAP ACTUATOR ASSEMBLY.			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
	20081124		NE  	2008	11	24	CA080917005      	2	20080910	G	7200	90623	ENGINE          			BOEING	777   	777*        	UTILUSE	NM  	GE    	GE90  	GE90115B    	30048	NE  					NR 1	VIBRATION       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			889  								(CAN) IN CRUISE, THE FLIGHT EXPERIENCED A NR 1 ENGINE VIBRATION.  THE ENGINE CONTINUED OPERATING NORMALLY BUT WITH VIBRA	TION.  THE FLIGHT DIVERTED TO FAIRBANKS, ALASKA.  AN ENGINE HAS BEEN SCHEDULED AND TOOLS, PARTS AND MANPOWER ARE CURRENT	LY BEING SHIPPED TO ALASKA. ACFT IS OUT OF SERVICE.  \ETQ INVESTIGATION NR 2917 INITIATED.				2	L	7	2 	4F	4	F	RT	T00001SE	E00049EN				 
	20081120			2008	11	20	CA080917006      	4	20080902	G	6122		GOVERNOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					PROPELLER	OUT OF ADJUST   	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI ROLL IN PREPARATION FOR TAKE-OFF, THE COMPRESSOR TURBINE SPEED (NG) DROPPED BY APPROX 2%. PILOT ADVANC	ED POWER LEVER AND ITT ROSE TO 740 DEG C WITH NO INCREASE IN NG. THE LOW OIL PRESSURE ANNUNCIATED AND PILOT OBSERVED ZER	O OIL PRESSURE. THE PROPELLER FEATHERED UNCOMMANDED AND THE PILOT SHUT THE ENGINE DOWN. THE PROP GOVERNOR WAS ADJUSTED A	ND THE ACFT RETURNED TO SERVICE.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081120		EA  	2008	11	20	CA080917007      	2	20080823	G	7200		ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  						MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB PASSING THRU FL15, THE LOW OIL PRESSURE WARNING WAS ACTIVATED AND THE COCKPIT INDICATION WAS SEEN FAL	LING.  THE CREW SHUT THE ENGINE DOWN AND THE ACFT RETURNED TO THE POINT OF DEPARTURE.  NO TROUBLESHOOTING WAS DONE BY TH	E OPERATOR AND THE ENGINE WAS REPLACED. THIS WAS THE 2ND EVENT IN 7 DAYS.  THE FIRST EVENT LED TO THE REPLACEMENT OF THE	 OIL PUMPS.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081120		CE  	2008	11	20	CA080917008      	1	20080808	G	5312	071111210	BULKHEAD        			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION AN AME FOUND CRACKS IN LOWER LT AND RT CORNER AT REAR FRONT ATTACH, WHICH HAD BEEN PR	EVIOUSLY REPAIRED AND HAS CRACKED AGAIN.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
	20081120		NE  	2008	11	20	CA080917009      	2	20080904	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						SHUTDOWN        	W				D				RETURN TO BLOCK         				R	X		PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           		TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REPORTED THAT DURING TAXI THE ENGINE EXPERIENCED UNCOMMANDED ROLL BACK AND SHUTDOWN.  TROUBLESHOOTING INDICA	TED THAT THE ENGINE MAY HAVE ALSO EXPERIENCED AN OVERTEMP CONDITION AND WAS REMOVED FROM SERVICE FOR INSPECTION.  P&WC W	ILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
	20081120		CE  	2008	11	20	CA080917010      	1	20080808	G	5312	071111229	BULKHEAD        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT CORNER AT REAR FLOAT FITTING.  CUSTOMER	 WAS NOTIFIED.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
	20081120		CE  	2008	11	20	CA080917011      	1	20080808	G	5312	071111229	BULKHEAD        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A NON-ROUTINE INSPECTION AN AME FOUND CRACKS IN BULKHEAD ASSY LOWER LT AND RT CORNERS AT REAR FLOAT FITTING	S.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
	20081120		NE  	2008	11	20	CA080917012      	2	20080907	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						MALFUNCTIONED   	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) DURING A 5 MIN. RE-POSITIONING FLIGHT, THE ENGINE LOST POWER AND AN EMERGENCY LANDING WAS ATTEMPTED.  THE ENGINE W	ILL BE RETURNED TO P&WC FOR INVESTIGATION.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE EST	ABLISHED.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081120		NE  	2008	11	20	CA080917013      	2	20080908	G	7200		ENGINE          			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					RIGHT	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				K	J	B	FLUID LOSS                	WARNING INDICATION        	SMOKE/FUMES/ODORS/SPARKS  	CR	CRUISE         	1			CA											(CAN) A YAW OF THE ACFT CAUGHT THE ATTENTION OF THE PILOT AND A QUICK REVIEW OF THE COCKPIT GAGES REVEALED THAT THE RT E	NGINE TORQUE WAS FLUCTUATING BETWEEN APPROXIMATELY 20% TO 40% WITH THE TEMPERATURE INDICATION RISING TO APPROXIMATELY 82	0 DEGREES.  THE PILOT VISUALLY CONFIRMED THAT LARGE AND SMALL SPARKS WERE EMANATING FROM THE ENGINE EXHAUST.  THE PILOT 	PROCEEDED TO SHUT THE ENGINE DOWN BEFORE MAKING AN UNEVENTFUL SINGLE ENGINE LANDING.  GROUND INSPECTION FOUND FUEL LEAKI	NG FROM THE COWLING. THE ENGINE WILL BE REMOVED.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20081120		NE  	2008	11	20	CA080917014      	2	20080901	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						DEFECTIVE       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, THE ENGINE LOST OIL PRESSURE.  AN AIR TURNBACK WAS INITIATED AND THE ACFT LANDED AT THE POINT OF DE	PARTURE WITH THE ENGINE RUNNING.  POST FLIGHT INSPECTION FOUND OIL LEAKING AROUND THE ENGINE INTAKE AREA.  THE ENGINE WI	LL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR.  P&WC WILL CLOSELY MONITOR THE INVESTIGATION RESULTS AND ISSUE	 UPDATES TO TC.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081120		NE  	2008	11	20	CA080917015      	2	20080905	G	7250		TURBINE BLADES  			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					ENGINE	DISTRESSED      	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE PILOT OBSERVED AN ENGINE OIL PRESSURE DROP TO THE RED ZONE.  HE ELECTED TO SHUTDOWN AND SECURE 	THE ENGINE BEFORE MAKING A SINGLE ENGINE LANDING AT DESTINATION.  GROUND INSPECTION FOUND LOW PRESSURE TURBINE BLADE DIS	TRESS.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
	20081120		NE  	2008	11	20	CA080917016      	2	20080908	G	7200		ENGINE          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING A RE-POSITIONING FLIGHT, THE PILOT NOTED LOW AND FLUCTUATING OIL PRESSURE.  THE ENGINE WAS SHUT DOWN AND SE	CURED AND A SINGLE ENGINE LANDING WAS PERFORMED.  GROUND INSPECTION FOUND CONTAMINATION IN THE OIL FILTER AND FILTER BOW	L.  THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTIGATION AND REPAIR.  P&WC WILL CONTINUE INVESTIGATING THE EVENT A	ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
	20081126		SW  	2008	11	26	CA080917017      	1	20080911	G	2597		CONNECTOR       	ARTEX       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ELT	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSTALLATION OF NEW 406 ELT ON INSTALLATION OF CONNECTOR FOR REMOTE SWITCH THE ELT WAS SET OFF. THE ELT WAS NOT FU	LLY INSTALLED SO THE ELT ACTIVATION WAS NOT NOTICED. HAVE SINCE SPOKE WITH THE MFG AND FOUND THAT THIS IS A COMMON PROBL	EM WITH THE INSTALLATION OF THE CONNECTOR NOT BEING INSERTED EXACTLY STRAIGHT, CAUSING THE PINS TO GROUND AND ACTIVATE E	LT. POSSIBLE PROBLEM EVERY TIME YOU INSTALL OR REMOVE THIS ELT. THERE IS NO OFF SWITCH TO PREVENT THIS REOCCURRENCE JUST	 POSSIBILITY OF MONITORING 121.5 FOR ACCIDENTAL ACTIVATION AND RESET OF ELT IF IT GOES OFF.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081124			2008	11	24	CA080917018      	4	20080911	G	8300		GEARBOX         								PWC   	PW610 	PW610FA     	52267	NE  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE, THE PILOT NOTICED A LOW OIL PRESSURE WARNING AND ELECTED TO SHUT THE ENGINE DOWN.  WHILE DESCENDING THE	 CREW DECIDED TO RESTART THE ENGINE AND COMPLETE THE FLIGHT WITH THE LOW OIL PRESSURE INDICATION.  ON THE GROUND, THE PI	LOT COULD NOT RESTART THE ENGINE.  INITIAL TROUBLESHOOTING MAY HAVE INDICATED DAMAGE TO THE ACCESSORY GEARBOX AND THE EN	GINE HAS BEEN REPLACED.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.								4	F			E00074EN				 
	20081120		NE  	2008	11	20	CA080917019      	2	20080913	G	7220		INLET GUIDE VANE			AMD   	FALC50	FALCON2000  	2730170	NM  	PWC   	PW308 	PW308C      	52182	NE  					NR 1 ENGINE	MALFUNCTIONED   	W				K				NONE                    				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) IT IS REPORTED THAT 10 MINUTES BEFORE LANDING, ENGINE NR 1 SHUTDOWN BY ITSELF FOLLOWED BY A "NO DISPATCH" MSG ON T	HE COCKPIT DISPLAY.  TROUBLESHOOTING SHOWED THAT THE IGV POSITION DID NOT MATCH THE REQUESTED VALUE.  THE VIGV WAS REPLA	CED AND THE FAULT CLEARED.  P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4F	4	F	RT	A50NM   	E00065EN				 
	20081120		EU  	2008	11	20	CA080918002      	1	20080912	G	5753	S5751202320	A/C PACK        	SNIAS       	S57512007004	AEROSP	ATR72 	ATR72212    	8680945	EU  										TE FLAP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C-CHECK INSPECTION (1C, 2C, 4C, CPCP2, A8), WHILE PERFORMING A DVI INSPECTION ON THE L INBD FLAP, THE INSPE	CTION REVEALED THAT THE FWD PICK-UP FITTING INBD LOG AT RIB 5 WAS BROKEN IN HALF. THE FITTING LOT NR IS P4110. THE BROKE	N OFF PIECE WAS FOUND IN THE FLAP FAIRINGS.				2	H	7	2 	4T			RT	A53EU   					 
	20081120		CE  	2008	11	20	CA080918003      	1	20080917	G	2434	00317	ALTERNATOR      			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	FWD ENGINE	DAMAGED         	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA				577  							(CAN) THE ACFT, A CESSNA 337G WAS ON A RETURN FLIGHT TO MAIN BASE WHEN THE PILOT NOTICED A INDICATION OF A FAILED FRONT 	ENGINE ALTERNATOR.  THE ACFT LANDED WITHOUT INCIDENT AND MX INVESTIGATED THE PROBLEM.  DURING REMOVAL OF THE FRONT ALTER	NATOR, IT WAS DISCOVERED THAT THE DRIVE SHAFT HAD BEEN SHEARED OFF.  THE DRIVE GEAR IN THE ENGINE WAS INSPECTED AND FOUN	D SERVICEABLE. A SERVICEABLE ALTERNATOR WAS INSTALLED AND THE ACFT RELEASED FOR SERVICE.  THE U/S ALTERNATOR HAD A TOTAL	 OF 577 HRS SINCE O/H.  WE HAVE HAD REPORTS OF SIMILAR PROBLEMS WITH THESE ALTERNATORS IN THE PAST.		1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
	20081125		SW  	2008	11	25	CA080918004      	1	20080914	G	2913		HOUSING         	VICKERS     		SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					HYDRAULIC PUMP	SEPARATED       	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA				3    							(CAN) DURING ENGINE START THE NR 2 ENGINE HYDRAULIC PUMP BEGAN TO LEAK SIGNIFICANTLY CAUSING A LOSS OF SYSTEM PRESSURE A	ND FLUID.  UPON INSPECTION BY MX THE PUMP WHICH WAS JUST INSTALLED 2.5 HRS PRIOR WAS FOUND TO HAVE SEPARATED AT THE PUMP	 HOUSING HALVES AND THE O RING SEAL WAS EXTRUDED. THE INTERNAL WRENCHING BOLTS WHICH HOLD THE HALVES TOGETHER APPEARED T	O HAVE PULLED OUT OF THE THREADS ALLOWING THE PUMP HALVES TO SEPARATE TO THE POINT OF PUMP FAILURE.  THE COMPANY WILL SE	ND THE PUMP FOR WARRANTY REPAIR.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20081125		SW  	2008	11	25	CA080918005      	1	20080914	G	7603	2543161	SPRING          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					THROTTLE RETURN	BROKEN          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA				101  							(CAN) DURING TAKEOFF THE LOW ROTOR HORN SOUNDED.  THE PILOT ABORTED THE TAKEOFF, SHUT DOWN THE ENGINE AND CALLED MX.  WH	EN THE ENGINE COWL WAS OPENED THE FCU THROTTLE RETURN SPRING WAS FOUND IN THE BOTTOM OF THE ENGINE PAN.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081125		CE  	2008	11	25	CA080918006      	1	20080909	G	2731	12601491	ACTUATOR        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ELEVATOR TRIM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION A AME FOUND HEAVY CORROSION (LEVEL 3) ON THE ACTUATOR.  HE R&R THE PART.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
	20081126			2008	11	26	CA080919001      	4	20080917	G	2562		MOUNT BRACKET   			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					ELT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE EXISTING ELT MOUNTING BRACKET WAS INSPECTED PRIOR TO REPLACEMENT OF THE VHF ELT WITH A 406 MHZ ELT.  UPON REMO	VING THE NARCO ELT10 MOUNTING TRAY, IT WAS DISCOVERED THAT ACFT ELT MOUNTING BRACKET WAS CRACKED AT EACH MOUNTING TRAY S	CREW HOLE LOCATION.  THE NARCO ELT TRAY WAS FOUND TO BE MOUNTED TO THE BRACKET USING ACCEPTABLE AN SCREWS AND SELF-CAPTI	VE NUTS.  THERE WERE NO WASHERS USED BETWEEN THE SELF-CAPTIVE NUTS AND THE BOTTOM SIDE OF THE ACFT MOUNTING BRACKET.  AS	 PART OF THE 406MHZ ELT UPGRADE AND MODIFICATION REPORT, THE OLD BRACKET WAS REMOVED, A NEW BRACKET WAS FABRICATED AND I	NSTALLED.	1	L	7	1 	3O	3	O		2A13    	E286				 
	20081125		WP  	2008	11	25	CA080919002      	1	20080916	G	2421	ALX8521RS	ALTERNATOR      			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  						DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				128  							(CAN) ALTERNATOR HAS STRIPPED HOUSING						1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081125		WP  	2008	11	25	CA080919003      	1	20080910	G	6310	C0512	ACTUATOR        			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					CLUTCH	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			712  								(CAN) CLUTCH ACTUATOR FOUND U/S DURING INSPECTION, SERVICEABLE ACTUATOR INSTALLED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081126		EA  	2008	11	26	CA080919004      	2	20080916	G	7261		NUT             		766859C     	BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	OIL PUMP	LOOSE           	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) DURING DESCENT NR 2 ENGINE INDICATED LOW OIL PRESSURE.  ENGINE WAS SHUTDOWN AND UNEVENFUL LANDING WAS CARRIED OUT.	   MX BORESCOPE INSP FOUND THE OIL PUMP DRIVE SHAFT NUT BECAME LOOSE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081125		WP  	2008	11	25	CA080919005      	1	20080908	G	6310	C0183	CLUTCH          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1920 							(CAN) LOUD BANGING NOISE IN ACFT.  CLUTCH REMOVED FOR TEARDOWN INSPECTION, SERVICEABLE CLUTCH INSTALLED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081125		WP  	2008	11	25	CA080919006      	1	20080826	G	6310	C0512	CLUTCH ACTUATOR 			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1747 							(CAN) DRIVE BELTS SLIPPING, SERVICEABLE ACTUATOR INSTALLED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081126		EU  	2008	11	26	CA080919007      	1	20080917	G	2110	139312	SUPERCHARGER    			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	CABIN PRESSURE	INOPERATIVE     	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			3982 								(CAN) WHILE IN CRUISE FLIGHT, ENROUTE, CREW NOTICED A STRANGE ODOR COMING FROM THE CABIN.  CREWMAN ONBOARD WENT TO LOOK 	IN THE CABIN AND NOTICED TEMPERATURE IN THE CABIN WAS VERY HOT AND THERE WAS LIGHT HAZE OR SMOKE IN SAFELY.  MX INSPECTE	D THE ACFT AND FOUND THAT BOTH CABIN SUPERCHARGER INTAKE FILTERS WERE NEARLY COMPLETELY CLOGGED.  FURTHER INSP REVEALED 	SOME SCORING ON THE INSIDE WALLS AND ROTORS OF THE CABIN SUPERCHARGERS.  INLET FILTERS WERE CLEANED AND BOTH LT AND RT C	ABIN SUPERCHARGERS REPLACED.  GROUND RUNS AND FLIGHT TEST WERE COMPLETED, THE ACFT WAS FOUND SERVICEABLE AND RELEASED FO	R SERVICE.	2	L	7	2 	3T	4	T		A24EU   	A196	6	C	P899	 
	20081125		CE  	2008	11	25	CA080919008      	1	20080825	G	8011	149NL	STARTER         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  						FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			98   								(CAN) STARTER FAILS TO ENGAGE, SERVICEABLE STARTER INSTALLED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081125			2008	11	25	CA080919009      	2	20080918	G	7414		ROTOR           																	MAGNETO	BROKEN          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											(CAN) CUSTOMER COMPLAINED ABOUT DEAD MAG.  TIME IN SERVICE IS UNKNOWN. MAG WAS OPENED AND INSPECTED.  THE ROTOR GEAR VAN	E SHOWED INDICATIONS OF RUBBING ON THE HALL EFFECT SENSOR AND HAD CONTACTED THE SENSOR.  THIS STOPPED THE ROTOR GEAR WHI	CH IS INSTALLED IN THE SLOT AND BROKE THE ROTOR SHAFT AT THE BASE OF THE SLOT.  THIS INFORMATION IS BEING SENT TO SLICK 	FOR EXAMINATION.																 
	20081125		EA  	2008	11	25	CA080919010      	2	20080908	G	7414	10600646201	MAGNETO         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			331  								(CAN) REMOVED DUE TO ERRATIC ENGINE RPM.						1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081126		NE  	2008	11	26	CA080919011      	2	20080918	G	7414		BEARING         		BL6006163   	ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	EXCESS PLAY     	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				458  							(CAN) MAG WAS RECEIVED FOR 500 HR INSP.  BEFORE MAG WAS DISASSEMBLED THE BEARINGS WERE CHECKED BY SPINNING THE ROTATING 	MAGNET.  THE END PLAY WAS MEASURED AT 0.004", MFG LIMIT IS 0.0015" MAX.  THE BEARINGS WERE RESHIMMED, THE REST OF THE 50	0 HR INSP WAS CARRIED OUT AND THE MAG WAS RETURNED TO SERVICE.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081201		CE  	2008	12	1	CA080921001      	1	20080919	G	3220	AN17621A	BOLT            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MX AND ENGINE CHANGE, NLG WAS REMOVED FOR ACCESS TO REPLACE LOOSE RIVETS IN ENG NACELLE AREA.  INSP	 OF NLG ATTACH BOLTS SHOWED SIGNS OF CRACKS JUST UNDER THE HEAD OF THE BOLT.  LPI INSP OF THE BOLT SHANKS CONFIRMED CRAC	KS.  BOLTS WERE BOTH REPLACED.  AFTT 12484.6 HOURS, A REVIEW OF ACFT HISTORY FOUND NO RECORD OF THESE BOLTS HAVING BEEN 	REPLACED.  A REVIEW OF THE MFG SERIES CAP, CONTINUED AIRWORTHINESS PROGRAM, SHOWED NO INITIAL INSP OR REPLACEMENT REQUIR	EMENTS.		1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P36EA	 
	20081201		NM  	2008	12	1	CA080922001      	1	20080917	G	3244	DR0231T	TIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 3	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			255  								(CAN) PASSENGER REPORTED NR 3 TIRE BURST DURING TAKE OFF.  CREW EXTENDED GEAR AND FA CONFIRMED TIRE WAS BLOWN.  ACFT RET	URNED TO BASE FOR LANDING. OPERATOR REPORTED TIRE WAS ON SECOND RETREAD WITH 238 CYCLES 255 HOURS. AXLE WAS NOT DAMAGED 	AND IS NOT BEING REPLACED.  THE RUNWAY WAS SWEPT AFTER THE INCIDENT AND NO DEBRIS OTHER THAN BITS OF TIRE WERE FOUND.  I	NSPECTION COMPLETED AND TIRE REPLACED,			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081201		EA  	2008	12	1	CA080922002      	2	20080822	G	7414		IMPULSE COUPLING			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	MAGNETO	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA		CGGPE									(CAN) ENGINE WAS OVERHAULED AND STORED UNTIL AUGUST 2008.  DURING INSTALLATION ON AUG. 22, 2008, IT WAS NOTICED THAT THE	RE WAS NOT :CLICKING: OF THE MAGNETO IMPULSE COUPLINGS AS THE PROPELLER WAS ROTATED A NR OF TIMES. BOTH MAGNETO (UNISON 	4381`S, S/N 07031616 AND 07031617) WERE REMOVED FROM THE ENG AND INSPECTED, THE PAWLS ON THE IMPULSE COUPLINGS ON BOTH M	AGNETOS WOULD NOT ENGAGE PROPERLY OR AT ALL.  IT APPEARED THAT THE IMPULSE COUPLINGS HAD BEEN ASSEMBLED INCORRECTLY.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081125		NE  	2008	11	25	CA080922003      	2	20080915	G	7313	301114521	ADAPTER         			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	REAR FUEL NOZZLE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				400  							(CAN) DURING LEAK TEST AFTER CLEANING LEAKAGE NOTED AT THE HEAD FUEL NOZZLE ADAPTER.						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
	20081128		SW  	2008	11	28	CA080922005      	1	20080909	G	2910	2781032273	LINE            			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	29073	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED HYD FLUID LEAKING IN LT WW.   SMALL PINHOLE WAS FOUND IN LINE.  LINE REPLACED AND ACFT RETURNED TO 	SERVICE.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081128		EA  	2008	11	28	CA080922006      	1	20080915	G	2150	78279015	ACM             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					LEFT	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA			13244	13244							(CAN) ON FINAL APPROACH, SMOKE SMELL IN FLIGHT DECK.  AT THE SAME TIME UNABLE TO CONTROL LT PACK IN AUTO OR MANUAL MODE.	  ALSO DISPLAY FAN OR AIR IN FAN MAKING GRINDING NOISE.  BOTH FANS PLACED IN FLT ALTN MODE AND SMOKE STOPPED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081128		EA  	2008	11	28	CA080923002      	1	20080922	G	5610	6003303021	WINDOW          			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			4341 								(CAN) WHILE IN CRUISE, CREW EXPERIENCED THE FAILURE OF THE COCKPIT LT SIDE WINDOW OUTER MAIN PLY.  A CRACK SPANNED FROM 	THE LOWER FWD FRAME, TO THE FWD SECTION OF THE UPPER FRAME OF THE WINDSHIELD.  THE ACFT HAD DEPARTED AND WAS ENROUTE SOU	THBOUND WHEN THE FAILURE OCCURRED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081128		EU  	2008	11	28	CA080923003      	1	20080912	G	5397	52802800	WIRE            			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					CARGO HOOK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACFT OVERHAULED, CAME BACK TO BASE LAST WEEK OF AUGUST, NO SLING LOAD OPERATION HAS BEEN LOGGED.  ELECTRICAL WIRE 	FOUND BROKEN AT HOOK CONNECTOR LOCATION.  ELECTRICAL WIRE ATTACHED WITH CLAMPS (4X) ALONG THE SWING CABLE SUPPORT.  THE 	ROUTING SEEMED TO BE TOO TIGHT.				1	G	7	2 	3U	3	U		H3EU    	E4CE				 
	20081125		SW  	2008	11	25	CA080923004      	1	20080922	G	7933		OIL SYSTEM      			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	OVERTEMP        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) ENGINE OIL TEMPERATURE INCREASED TO 100 DEG. C.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081128		NE  	2008	11	28	CA080923006      	2	20080806	G	7250	3022312	TURBINE WHEEL   			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	DISINTEGRATED   	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA			10566								(CAN) WHILE HOVERING DURING TAKEOFF, NR1 PWR SECTION LOST POWER (PILOT REPORTED HEARING LOUD BANG).  ACFT PUT DOWN WITHO	UT FURTHER INCIDENT, NR2 POWER SECTION SHUTDOWN.  POWER SECTION REPLACED.  ACFT RETURNED TO SERVICE.  PRELIMINARY INSP R	EVEALED FAILURE OF THE PT DISK.  PARTIAL BLADE SEPARATION AND FOD TO EXHAUST DUCT.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081128		NM  	2008	11	28	CA080924001      	1	20080920	G	3240	900005831PR	BRAKE ASSY      			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					NR 3	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA				2416 							(CAN) 100 M FROM STOPPING AT THE GATE, THE RT BRAKE STARTED TO GRAB.  BRAKE TEMPS ALL NORMAL RANGE.  AFTER SHUTDOWN, INS	PECTED RT MAIN BRAKE ASSY AND APPEARS THAT BRAKE PAN AND ASSY CAME APART.  NR3 MLG WHEEL AND BRAKE ASSY REMOVED.  LG AND	 ACFT INSPECTED, NO ADDITIONAL DEFECTS NOTED.  NEW BRAKE AND WHEEL ASSYS INSTALLED AND TESTED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081125		SW  	2008	11	25	CA080924002      	1	20080924	G	5302	205001731101	SUPPORT         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR SERVO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2322 								(CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
	20081125		SW  	2008	11	25	CA080924003      	1	20080924	G	5302	205001731101	SUPPORT         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR SERVO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2322 								(CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
	20081125		SW  	2008	11	25	CA080924004      	1	20080924	G	5302	205001731001	SUPPORT         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR SERVO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2322 								(CAN) TAIL ROTOR SERVO SUPPORT FOUND CRACKED NEAR UPPER ATTACHMENT FLANGES.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
	20081128		SW  	2008	11	28	CA080924005      	1	20080918	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			1118 								(CAN) ACFT WAS ON A MEDEVAC FLIGHT AT NIGHT AT CRUISE ALTITUDE OF 16000 FT WHEN THE FLIGHT CREW HEARD A NOISE LIKE A SLA	P.  THEY COULD SEE THEN THAT THE RT WINDSHIELD WAS CRACKED.  ACFT RETURNED WITHOUT FURTHER INCIDENT. INSP FOUND THE WIND	SHIELD OUTER PANEL HAD SHATTERED.  WINDSHIELD IS BEING RETURNED FOR INSP AND WARRANTY CONSIDERATION.  WINDSHIELD REMOVED	 FROM ACFT AND STRUCTURE INSPECTED.  NO DEFECTS FOUND.			1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU	 
	20081128			2008	11	28	CA080924007      	1	20080924	G	2820		LINE            								GARRTT	TFE731	TFE73140    	29001	NE  					FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSP IN THE RT WW THE MAIN FUEL LINE TO THE RT ENGINE WAS FOUND TO BE CHAFING ON THE LAV SINK HEATED DRAIN 	LINE. THE DAMAGE WAS BEYOND LIMITS AND THE FUEL LINE WAS REPLACED.										4	F			E1NM				 
	20081128			2008	11	28	CA080924008      	1	20080924	G	2820	25W653120634	LINE            								GARRTT	TFE731	TFE73140    	29001	NE  					FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) IT WAS REPORTED THAT FUEL WAS SLOWLY TRANSFERRING FROM THE RT WING INTO THE CENTER TANK WHEN THE ACFT WAS STATIC. 	 THE MOTIVE FLOW LINE PN 25W653120-634 AT THE CENTRAL TANK LOWER TRANSFER JET PUMP WAS FOUND TO BE CHAFING ON THE FUEL Q	TY PROBE MOUNTING BRACKET.  THE LINE WAS REPLACED.									4	F			E1NM				 
	20081128		EA  	2008	11	28	CA080924009      	1	20080924	G	3210	C6UM11104	ATTACH FITTING  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE 12 MONTH INSP OF THE MLG WHICH CONSISTS OF INSPECTING THE WELDS FOR CRACKS, A CRACK WAS DETECTED ON THE	 BOTTOM OF THE AFT ATTACH TUBE APPROX 5 INCHES FROM THE AFT GEAR ATTACH FITTING.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081128		NE  	2008	11	28	CA080924011      	2	20080922	G	7200		TORQUE SHAFT    			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					NR 1 ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE TORQUE WAS LOST ON NR 1 ENGINE, SUBSEQUENTLY THE ENGINE WAS SHUTDOWN BY THE CREW.  POST FLIGHT INSPE	CTION REVEALED A CRACKED TORQUE SHAFT AT THE WELD JOINT.  ENGINE IS BEING REMOVED FOR INVESTIGATION.  MFG WILL CONTINUE 	INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20081128		NE  	2008	11	28	CA080924012      	2	20080815	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					LEFT	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN) ACFT WAS IN HOVER AND WAS TRANSITIONING TO FWD FLIGHT WHEN THE LT ENGINE ROLLED BACK IN POWER AND SHUTDOWN.  PILOT	 LANDED THE ACFT SUCCESSFULLY ON 1 ENGINE.  LT ENGINE WAS REMOVED AND SENT TO MFG FOR INVESTIGATION.  MFG WILL CONTINUE 	INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081128		NE  	2008	11	28	CA080924013      	2	20080922	G	7200		ENGINE          			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  						FLUCTUATES      	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) AT ABOUT 50 METERS FROM THE ARRIVAL GATE, THE ENG PARAMETERS STARTED FLUCTUATING.  PILOT SHUTDOWN THE ENG.  NO REP	ORTED DAMAGE. TROUBLESHOOTING IN PROGRESS.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTA	BLISHED.				2	H	7	2 	4T	4	T	RT	A45NM   	E20NE				 
	20081128		NM  	2008	11	28	CA080925001      	1	20080914	G	5610	80260008	WINDOW          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			371  								(CAN) RT WINDSHIELD CRACKED DURING CRUISE.  REDUCED SPEED TO 180 KTS AND DESCENDED TO FL100 AND LANDED AT DESTINATION.  	 MX REPLACED WINDSHIELD.  ACFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081128		CE  	2008	11	28	CA080925002      	1	20080924	G	5511	053200198	SPAR            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					HORIZONTAL STAB	CRACKED         	W				A				UNSCHED LANDING         				C	A		F.O.D.                    	FLAME/FIRE                		NR	NOT REPORTED   	1			CA			9629 								(CAN) DURING THE 100 HRS/ANNUAL INSP, IT WAS DISCOVERED THAT THE HORIZONTAL STABILIZER FRONT SPAR ASSY (PN 0532001-98) A	ND THE RE-INFORCEMENT SPAR (PN 0531037-1) HAVE CRACKS AT 2 PLACES, ABOUT .5 INCH IN LENGTH, RADIATING FROM THE CENTER LI	GHTENING HOLE BETWEEN BOLT ATTACHMENT AREA.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081128		EA  	2008	11	28	CA080925003      	2	20080919	G	7414	BL600646201	MAGNETO         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				O				OTHER                   				X			ENGINE FLAMEOUT           			DE	DESCENT        	1			CA			151  								(CAN) PILOT SNAGGED THERE WAS A HIGH ENGINE RPM RISE.  MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.						1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081128		EA  	2008	11	28	CA080925004      	2	20080919	G	7414	BL600646201	MAGNETO         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				O				OTHER                   				X			ENGINE FLAMEOUT           			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED THERE WAS A HIGH ENGINE RPM RISE.  MAGNETO WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.  THIS IS 	DUPLICATED ON REPORT 20080925003.					1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081201		NE  	2008	12	1	CA080925006      	2	20080908	G	7200		ENGINE          			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					NR 2	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN)  WHILE DEPARTING AREA WITH AN AIRSPEED OF 30 TO 40 KNOTS AND A 500 FT PER MINUTE RATE OF DESCENT, NR 2 ENGINE N1 L	OW RPM AUDIO HORN SOUNDED ALONG WITH ILLUMINATION OF NR 2 ENGINE LOW OIL PRESSURE LIGHT. A SCAN OF THE ENGINE GAUGES REV	EALED THE NR 2 ENGINE HAD LOW N1 RPM WITH A CLIMBING T5 TEMP. THE FLIGHT CREW IDENTIFIED THE PROBLEM AS AN ENG ROLL BACK	 AND ONCE THE LOAD WAS SAFELY JETTISONED, A SHUTDOWN OF THE NR 2 ENGINE WAS CARRIED OUT. THE ACFT THEN RETURNED TO ITS S	ERVICE LANDING AND MADE AN SINGLE ENGINE LANDING.  A POST FLIGHT INSPECTION OF THE T5 RECORDING SYS REVEALED THE ENGINE 	TEMP HAD REACHED 798 DEGREES C. THE ENGINE, FREE TURBINE ASSY AND FCU WERE REPLACED AND AFTER A COMPLETE GROUND CHECK TH	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
	20081202		NE  	2008	12	2	CA080925007      	2	20080908	G	7321		FUEL CONTROL    			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  						FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	M	J	PARTIAL RPM/PWR LOSS      	OVER TEMP                 	WARNING INDICATION        	NR	NOT REPORTED   	1			CA											(CAN) LIGHT  A SCAN OF THE ENG GAUGES REVEALED THE NR 2 ENGINE HAD LOW N1 RPM WITH A CLIMBING T5 TEMP.  FLIGHT CREW IDEN	TIFIED THE PROBLEM AS AN ENG ROLL BACK AND ONCE THE LOAD WAS SAFELY JETTISONED A SHUTDOWN OF THE NR (2) ENGINE WAS CARRI	ED OUT. THE ACFT THEN RETURNED TO IT`S SERVICE LANDING AND MADE AN SINGLE ENGINE LANDING.  A POST FLIGHT INSP OF THE T5 	RECORDING SYS REVEALED THE ENGINE TEMP HAD REACHED 798 DEGREES C. THE ENG, FREE TURBINE ASSY AND FCU WERE REPLACED AND A	FTER A COMPLETE GROUND CHECK ACFT WAS RETURNED TO SERVICE.  THE ENG, FREE TURBINE AND FCU WERE RETURNED TO MFG FOR AN OV	ER TEMP INSP AND EVALUATION AS TO A POSSIBLE CAUSE OF THE ROLL BACK.	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
	20081128		SW  	2008	11	28	CA080925009      	1	20080804	G	2435	23032027	STARTER GEN     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STARTER WAS SNAGGED BY PILOT WHICH MOTORED UNDER ITS OWN POWER. EXCESSIVE ROTATION CAUSED INTERNAL DAMAGE.  STARTE	R WAS REPLACED AND NO ISSUES WERE NOTED.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081128		WP  	2008	11	28	CA080925012      	1	20080924	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			1781 								(CAN) CLUTCH WAS REMOVED FROM ACFT FOR VISUAL INSP DUE TO ISSUES WITH CLUTCH ASSY`S.  TEARDOWN REVEALED THE FOLLOWING: C	AGE CRACKED AT 1 CROSSBAR, SHAFT C166-4 WORN UNDERSIZE, HSG C167-3 WORN OVERSIZE AND OIL WAS VERY BLACK.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081202		GL  	2008	12	2	CA080925013      	1	20080918	G	2421	ALU8521LS	ALTERNATOR      			DIAMON	DA40  	DA40        	2990002	GL  											INTERMITTENT    	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA			6    								(CAN) INSUFFICIENT CLEARANCE BETWEEN THE HEAD OF THE FIELD TERMINAL STUD AND HSG.  BRUSH HOLDER ASSY WHEN FLEXED INWARD,	 CAUSES THE HSG AND HEAD OF THE STUD TO TOUCH.  IF YOU REMOVED THE BRUSH HOLDER ASSY YOU WILL NOTICE THAT THE RING TERMI	NAL THAT IS CRIMPED TO THE BRUSH LEAD IS SLIGHTLY LARGER THAN THE HEAD OF THE TERMINAL BOLT.  IT IS ACTUALLY THE RING TE	RMINAL THAT TOUCHES THE HSG.  THIS TRIPS THE VOLTAGE REGULATOR OFF LINE.  THE ALTERNATOR SWITCH NEEDS TO BE CYCLED TO RE	SET THE REGULATOR.		1	L	7	1 	3O			NT	A47CE   					 
	20081128		WP  	2008	11	28	CA080925014      	1	20080923	G	6310	C1883	SPRAG CLUTCH    			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	CHIPPED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			596  								(CAN) PILOT HEARD POSSIBLE NOISE WITH SLIPPAGE OF DRIVE TRAIN.  CLUTCH WAS REMOVED TO VERIFY NO INTERNAL DAMAGE.  THE FO	LLOWING WAS FOUND DURING A TEARDOWN: 1 PEANUT INNER EAR CHIPPED, SHAFT PN C166-4 WORN UNDERSIZE, HSG C167-3 WORN OVERSIZ	E AND OIL VERY BLACK.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081128		NE  	2008	11	28	CA080926001      	2	20080925	G	7414	103571651	COIL            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			235  								(CAN) IT WAS FOUND WHEN THE MAG WAS ASSEMBLED NEW, THE HIGH TENSION TAB OF THE COIL WAS NOT MADE PARALLEL WITHIN THE HOU	SING SPLIT LINE.  THIS CAUSED THE BRUSH TO WEAR A DEEP GROOVE INTO THE TAB.  THE BRUSH (10-160844) ALSO RECEIVED DAMAGE 	IN THE FORM OF A STEP GROUND INTO THE SIDE OF IT FROM THE SIDE LOAD IMPOSED BY THE BENT TAB.				1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081128		NM  	2008	11	28	CA080926002      	1	20080926	G	2910	82920010227	PIPE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	DAMAGED         	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			12782								(CAN) DURING TAXI OUT THE FLIGHT CREW REPORTED A LOSS OF NR 2 HYDR QUANTITY AND HYDR LOW PRESSURE CAUTION LIGHT.  MX DIS	COVERED A HYDR TUBE LOCATED AT APPROX STA X409.00 RT SIDE HAD A (2) CENTIMETER CRACK LONGITUDINALLY ON THE INNER RADIUS 	OF A 90 BEND.  TUBE WAS PART OF THE MLG DOWN SYS, PRESSURE LINE, NR 2 HYDR.  TUBE WAS REPAIRED IAW THE AMM AND ACFT RETU	RNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081128		SW  	2008	11	28	CA080926003      	1	20080914	G	2720	27720065	ARM             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RUDDER PEDAL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND 3 OF 4 RUDDER PEDAL ATTACH ARMS CRACKED ON LWR END, WHERE THE TORQUE TUBE THAT THE PEDAL IS MOUNTED TO ATTAC	HES TO THE CAST ARM. MATERIAL THICKNESS IS APPROX .2500 INCH IN THAT AREA.  ACFT IS 17,800 TOTAL TIME, LOW FOR THIS TYPE	 OF ACFT.  HAVE PREVIOUSLY FOUND 1 OTHER CRACKED ARM.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
	20081128		CE  	2008	11	28	CA080926004      	1	20080922	G	2840	S38521	RESISTOR        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	FUEL INDICATOR	WORN            	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) DURING GROUND RUN, NOTICED THAT THE LOW FUEL WARNING LIGHT FOR THE LT SIDE WOULD FLICK ON.  IF YOU WERE QUICK ENOU	GH TO CATCH IT THE LT FUEL QUANTITY NEEDLE WOULD TWITCH AT THE SAME TIME.  WITH THE SENDER REMOVED THE RESISTANCE IN THE	 SENDER WAS CHECKED WITH A DIGITAL MULTI METER. NORMAL OPERATION FROM THE EMPTY TO FULL IS 2 OHMS TO 90 OHMS. THE SENDER	 WAS FINE AT THE EMPTY POSITION AT 2 ISH OHMS UP TO 63 OHMS. PAST 63 UP TO FULL THE RESISTANCE COULD SPIKE UPWARDS AROUN	D 350 OHNS WHEN THE FLOAT ARM WAS WIGGLED. UNIT WAS REPLACED AND NO FURTHER ISSUES WERE NOTED.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
	20081201		EU  	2008	12	1	CA080926005      	1	20080925	G	2597	E0111241057	CONNECTOR       			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680       	30025	NE  					GALLEY POWER	DAMAGED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING STATION TRANSIT, CABIN CREW REPORTED SMOKE COMING FROM AFT GALLEY, WITH SMOKE WARNING, WHEN GALLEY ELECTRIC	AL PWR WAS PUT ON.  GALLEY POWER WAS REMOVED FROM THE AFT GALLEY.  DURING MX INVESTIGATION, THE GALLEY CONNECTOR 38 MC W	AS FOUND DAMAGED WITH PINS AND SOCKET BURNED. CONNECTOR WAS REPLACED AND CAMPAIGN WAS INITIATED TO INSPECT ACFT EQUIPMEN	T WITH THE SAME TYPE OF INSTALLATION.			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
	20081202		EA  	2008	12	2	CA080927001      	2	20080926	G	8520	130L119	PISTON RING     			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				1547 							(CAN) PILOT REPORTED ENGINE ROUGH AT 80 PERCENT RPM.  ACFT WAS GROUNDED AND A COMPRESSION CHECK WAS CONDUCTED.  CYLINDER	 1 WAS FOUND TO HAVE 58/80 PSI.  CYLINDER AND PISTON REMOVED AND COMPRESSION RING WAS FOUND CRACKED. PISTON/CYLINDER REP	LACED.  ACFT RETURNED TO SERVICE.				1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081202		NE  	2008	12	2	CA080929003      	2	20080918	G	7321	8237002	FUEL CONTROL    			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					ENGINE	FAILED          	W				L				ABORTED APPROACH        				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA			3308 	3308 							(CAN) ON DESCENT THROUGH 12000 FT, THE ENGINE EEC WARNING ACTIVATED, OIL PRESSURE DROPPED AND ENGINE SPOOLED DOWN TO 0. 	 APPROACH REJECTED AND EMERGENCY DECLARED, ACFT DIVERTED.  TROUBLESHOOTING CARRIED OUT, AS REQUESTED BY MFG, FUEL IS NOT	 PASSING THROUGH THE FCU, UNIT REMOVED FOR REPAIR/OVERHAUL, A REPLACEMENT UNIT HAS BEEN ORDERED.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20081209		SW  	2008	12	9	CA080929005      	1	20080924	G	6720	369X2172313	PITCH LINK      			DOUG  	500N  	MD500N      	3030001	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			219  								(CAN) THE PITCH CHANGE ROD END BEARING BALL WAS FOUND SEPARATED FROM THE PITCH LINK.  THE PILOT REPORTED THAT THE TAIL R	OTOR FELT DIFFERENT UPON LANDING.  IT WAS FOUND BY THE PILOT WHEN DOING A POST FLIGHT INSPECTION.  AN AME WAS DISPATCHED	 TO ATTEND THE PROBLEM.  BOTH PITCH CHANGE RODS WERE REPLACED AND THE HELICOPTER WAS RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
	20081202		WP  	2008	12	2	CA080929006      	1	20080929	G	6310	C0183	CLUTCH          			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAIN ROTOR	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			955  								(CAN) THE C188-3 SPRAG S/N S164 REV G HAS 2 PEANUTS WITH 5 BROKEN EARS. C166-4 SHAFT SPRAG JOURNAL WORN UNDERSIZE, C167-	3 HOUSING SPRAG JOURNAL WORN OVERSIZE.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081202		CE  	2008	12	2	CA080929007      	1	20080920	G	2843	38522	INDICATOR       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	FUEL QTY	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FUEL QUANTITY SENDER FOUND ELECTRICALLY UNSERVICEABLE, READING EMPTY WHEN TANKS WERE FULL.  SERVICEABLE FUEL SENDE	R INSTALLED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
	20081202		EA  	2008	12	2	CA080930001      	1	20080928	G	5280	CC670105202003	DOOR            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     	30049	NE  					LT MLG	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) DURING THE WALKAROUND THE CREW NOTICED THE LT MLG DOOR WAS MISSING.  THE DOOR SEPARATED FROM ACFT DURING THE FLIG	HT.  THE PRELIMINARY ASSESSMENT FROM PICTURES SHOWS THE HINGE FITTINGS CRACKED AND THE ROD END SNAPPED ON THE DOOR ATTAC	HMENT POINT.  LAST STRUCTURAL INSPECTION IAW AD CF2003-23 DONE 12 SEPT 2008.				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081202		GL  	2008	12	2	CA080930002      	3	20080914	G	6110		PROPELLER       			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	O540A1C5    	41532	EA  	HARTZL	HC92Z	HC92ZK1     	GL  		VIBRATION       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PROPELLER REMOVED FOR EVALUATION DUE TO SMALL VIBRATION.  NOT CONSIDERED SERIOUS.						1	H	7	1 	3O	3	O		A7EA    	E295	5	C	P892	 
	20081202		NE  	2008	12	2	CA080930003      	2	20080831	G	7261		SEAL            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE OIL	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE OIL PRESSURE STARTED TO FLUCTUATE FOLLOWED BY A DROP TO ZERO, WHICH WAS ACCOMPANIED BY A GEARBO	X CHIP DETECTOR WARNING FOR NR 2 POWER SECTION.  A SINGLE ENGINE LANDING WAS PERFORMED. TROUBLESHOOTING FOUND LITTLE OIL	 LEFT IN THE ENGINE AND A LEAK AT NR 2 PT GOVERNOR SEAL.  THE CHIP DETECTOR WAS FOUND CONTAMINATED.  THE POWER SECTION A	ND GEARBOX TC2523 WILL BE REMOVED AND FORWARDED FOR REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROO	T CAUSE ONCE ESTABLISHED.		1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081202		CE  	2008	12	2	CA080930004      	1	20080929	G	2730	05117821	YOKE            			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	ELEV CONTROL	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN)  ASSEMBLY WAS FOUND CORRODED WHEN INSPECTED IAW SEB01-3.						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
	20081202		CE  	2008	12	2	CA080930005      	1	20080929	G	5340	0512128	BRACKET         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					FLAP PULLEY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT FLAPS HAVE EXCESSIVE PLAY WHEN DEPLOYED.  SYSTEM INVESTIGATED AND LT SIDE FLAP PULLEY BRACKET FOUND BROKEN.						1	H	7	1 	3O	3	O		3A24    	E5CE				 
	20081202		CE  	2008	12	2	CA080930006      	1	20080723	G	3246	4040A	WHEEL           			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT MAIN WHEEL ASSY BEAD AREA FOUND CRACKED.  WHEEL REPLACED WITH SERVICEABLE UNIT.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
	20081202		CE  	2008	12	2	CA080930007      	1	20080930	G	3210	24410071	SPACER          			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					LT MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REMOVAL OF LT GEAR ACTUATOR DUE TO HYDR BYPASS, CONICAL SPACER, P/N 2441007-1, ITEM NR 32 IN IPC 32-32-20, WA	S FOUND CRACKED. RT ACTUATOR REMOVED, SPACER VISUALLY INSPECTED. NO CRACK INDICATIONS. BOTH ACTUATOR PILLARS REMOVED, CL	EANED AND MAGNETIC PARTICLE INSPECTED IAW NDT MANUAL. NO DEFECTS NOTED. SURROUNDING AREA VISUALLY INSPECTED, NO DEFECTS 	NOTED. ACTUATORS INSTALLED WITH NEW SPACERS ON BOTH SIDES IAW ACFT MM. F/C OF GEAR C/O SERVICEABLE.			2	L	7	2 	4F	4	F		A10CE   	E6WE				 
	20081202		SO  	2008	12	2	CA080930008      	1	20080929	G	8120		SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) PILOT SAW THICK BLUE SMOKE FROM LT ENG JUST AFTER LANDING AT HOME BASE.  OIL PRESSURE INDICATIONS APPEARED NORMAL.	  DURING INVESTIGATION FOUND LT TO BE 5 QUARTS LOW ON OIL, WITH NO VISIBLE EXTERNAL LEAKS.  CYL COMPRESSION CHECK SHOWED	 NO FAULTS.  TURBO CHARGER EXHAUST PIPE SHOWED WET OIL ON INSIDE OF EXIT PIPE.  PIPE REMOVED FROM TURBOCHARGER AND FOUND	 OIL STAIN IN EXHAUST TURBINE.  REPLACED TURBO AND GROUND CHECKED SERVICEABLE.  NO FAULTS REPORTED AFTER SUBSEQUENT FLIG	HTS.		1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20081202		CE  	2008	12	2	CA080930009      	1	20080920	G	2910	1013880175	LINE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	HYDRAULIC SYS	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER LANDING A HYDR LEAK WAS DISCOVERED BY THE MX CREW.  IT TURNED OUT TO BE THE RT MLG "REGULAR EXTEND" HYDR LIN	E.  THE LINE HAD RUPTURED ABOUT 1 INCH FROM THE END FITTING RESULTING IN A SUBSTANTIAL FLUID LOSS.  THE LINE WAS REPLACE	D WITH NO FURTHER ISSUES.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
	20081202		NM  	2008	12	2	CA081001001      	1	20080916	G	7920		PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE OIL	LOW PRESSURE    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, THE LOW OIL PRESSURE WARNING FOR THE NR 2 ENGINE SOUNDED.  THE PILOT ELECTED TO SHUTDOWN AND SECUR	E THE ENGINE AND AN UNEVENTFUL SINGLE ENGINE LANDING WAS PERFORMED AT DESTINATION.  GROUND INSPECTION REVEALED NO SIGNS 	OF EXTERNAL OIL LEAKAGE, HOWEVER THE OIL TANK SHOWED "EMPTY".  INITIAL TROUBLESHOOTING REVEALED INTERNAL DISTRESS OF THE	 OIL PUMP ASSY.  THE ENGINE HAS BEEN REMOVED AND WILL BE RETURNED FOR INVESTIGATION.  MFG WILL CONTINUE INVESTIGATING TH	E EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081202		EU  	2008	12	2	CA081001002      	1	20080930	G	2440		TERMINAL        			SAAB  	SF340 	340B        	7860101	EU  										EXTERNAL POWER	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACFT ARRIVED FROM CUSTOMER WITH EXTERNAL POWER INOP (MEL).  AFTER INVESTIGATION, FOUND THE + TERMINAL MELTED AT TH	EN EXT PWR CONNECTOR.  SHEET METAL REPAIR WAS PREVIOUSLY DONE AT THE EXT PWR CONNECTOR ATTACHMENT.  BOTH TERMINALS WERE 	CRACKED HALF WAY.				2	L	7	2 	4T			RT	A52EU   					 
	20081202		CE  	2008	12	2	CA081001003      	1	20080919	G	5751	122005211	SKIN            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT INSPECTION THE LT AILERON OTBD HINGE ASSY WAS FOUND CRACKED.  THE CRACKS WERE LOCATED AT THE BEND RADIUS OF THE	 LOWER AFT ATTACH ANGLES.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
	20081202		SW  	2008	12	2	CA081001004      	1	20080927	G	5302	206031329103S	FITTING         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPPER LT TAILBOOM ATTACHMENT FITTING ON THE FUSELAGE SIDE FOUND CRACKED FROM THE RIVET HOLES.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081202			2008	12	2	CA081001006      	4	20080924	G	2397	GNS430	WIRE            			UROCOP	EC130 	EC130B4     	8680989	EU  	TMECA 	ARRIEL	ARRIEL2B1   	60056	NE  					COMM 1	SHORTED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA			31   								(CAN) NO PILOT OR COPILOT SIDE TONE ON COMM 1.  TECH FOUND THE AUDIO PHONE WIRE SHORTED BY THE SHIELDING.  REPAIRED AND 	SIDE TONES WERE RETURNED TO NORMAL.					1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
	20081202		SW  	2008	12	2	CA081001007      	1	20081001	G	2821	ZT2CV06A08B	CHECK VALVE     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					FUEL SYSTEM	DIRTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13135								(CAN) AFTER A FUEL FILTER REPLACEMENT A 2 MINUTE RUN IS REQUIRED WITH BOOST PUMPS OFF TO ENSURE THERE ARE NO AIR LEAKS I	N THE FUEL SYS.  DURING THIS 2 MINUTE GROUND RUN THE ENG FLAMED OUT AFTER APP 90 SECONDS INDICATING AN AIR LEAK.  FUEL S	YS INSPECTED AND THE INLINE FUEL/CHECK VALVE WAS FOUND STUCK IN THE OPEN POSITION.  WHEN THIS VALVE IS STUCK OPEN AIR CA	N BE SUCKED FROM THE FRONT FUEL TANKS IF THEY ARE EMPTY.  CHECK VALVES CLEANED AND HELICOPTER WAS GROUND RUN SATISFACTOR	ILY.  THIS WAS POSSIBLY CAUSED BY FUELING FROM DRUMS FOR AN EXTENDED PERIOD OF TIME AND A SMALL QUANTITY OF DIRT ENTERED	 THE FUEL SYS.	1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081202		NM  	2008	12	2	CA081001008      	1	20080814	G	3000	XD4N	RELAY           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	DEICE SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			40935	40935							(CAN) DURING DESCENT FROM FL250, AS POWER WAS REDUCED BELOW 30 PERCENT TORQUE.  WHEN DESCENDING THROUGH 23000` CABIN STA	RTED TO CLIMB RAPIDLY. DE-ICE PRESSURE CAUTION LIGHT ILLUMINATED.  NO LOUD NOISES OR SQUEALS.  MX INVESTIGATION FOUND RE	LAY 2121-K6 AT FAULT.  RELAY REPLACED, ACFT RETURNED TO SERVICE. (NOTE: PART IS CONSIDERED AN EXPENDABLE AND TIMES NOT T	RACKED, TIMES PROVIDED ARE AIRFRAME TIMES)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081202		CE  	2008	12	2	CA081002001      	1	20081002	G	3260	SA24SDX111	SWITCH          			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	MLG	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LANDING GEAR INTERMITTENTLY WOULD NOT RETRACT.  FOUND ANNUNCIATOR PRESS TO TEST SWITCH INTERMITTENT.						1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
	20081202		CE  	2008	12	2	CA081002002      	1	20081002	G	3230	1002573	PISTON          			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  	HARTZL	HCF3Y	HCF3YR1     	GL  	MLG	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			51   								(CAN) RT MLG FAILED TO RETRACT.  FOUND HYDRAULIC CYLINDER PISTON HAD SEPARATED FROM CYLINDER RAM.						1	H	7	1 	3O	3	O	RT	A4CE    	E14EA	5	C	P31EA	 
	20081202		CE  	2008	12	2	CA081002003      	1	20080929	G	8120	407809001	TURBINE WHEEL   			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520C    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	TURBOCHARGER	SEIZED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				774  							(CAN) TURBINE WHEEL SEIZED.  TURBOCHARGER REMOVED, OVERHAULED TURBOCHARGER INSTALLED.						1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
	20081202		NM  	2008	12	2	CA081002004      	1	20081001	G	2432		BATTERY         			BOEING	737   	737275C     	13844AS	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MASTER	OVERHEATED      	W				O				OTHER                   				B	M		SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 		TX	TAXI/GRND HDL  	1			CA											(CAN) PASSENGERS WERE ON THE ACFT, ACFT WAS ON EXTERNAL GROUND POWER AT THE TIME.  WHEN THE PILOTS WENT TO START THE APU	, THEY NOTICED THE START WAS NOT NORMAL, AND THE APU ALSO DID NOT START.  APU OVERSPEED CAUTION LIGHT ILLUMINATED.  CAPT	AIN WENT TO THE E&E BAY TO RESET THE APU BOX.  APU START ATTEMPTED AGAIN, SAME RESULT.  PILOT AGAIN RESET THE APU CONTRO	L BOX, AND THAT WAS WHEN HE NOTICED THE BATTERY SMOKING/VENTING.  IT WAS HOT TO THE TOUCH.  PEOPLE WERE REMOVED FROM THE	 ACFT.  MX CONFIRMED THE BATTERY WAS STILL HOT, AND IT WAS REMOVED.  A NEW OVERHAULED BATTERY WAS INSTALLED, AND THE BAT	TERY CHARGING CIRCUIT WAS TESTED IAW WORKCARD.  NO FAULTS WERE NOTICED, ACFT WAS RELEASED BACK INTO SERVICE.	2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
	20081126		CE  	2008	11	26	CA081002005      	1	20080929	G	2820	10192000015	LINE            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING DAILY INSP, WITH POWER ON A FEW MOMENTS, NOTICED FUEL LEAKING FROM LT GEAR WELL. POWER TURNED OFF, NOTED FU	EL LEAKING FROM SUPPLY LINE WHICH IS LOCATED BETWEEN AUX FUEL TANK AND NACELLE FUEL TANK. ON CLOSER INSP NOTICED  WHERE 	FUEL LINE PASSED THROUGH OPENING IN A BULKHEAD,  LINE RUBBING AGAINST B-NUT OF A HYD LINE. AFTER REMOVAL OF LINE, A WORN	 AREA & CRACK IN THE MIDDLE OF IT WAS FOUND TO BE THE CAUSE OF THE FUEL LEAK. THIS FUEL LINE WOULD ONLY LEAK IF FUEL WAS	 BEING TRANSFERRED FROM THE AUX TANK TO THE NACELLE FUEL TANK, OTHERWISE THE MOTIVE CHECK VALVE WOULD HAVE CLOSED AND NO	T ALLOWED FUEL TO FLOW BACK FROM THE NACELLE TANK. PILOT HAD LEFT THE AUX FUEL TRANSFER OVERRIDE SWITCH IN THE MANUAL PO	1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
	20081120			2008	11	20	CA081002006      	1	20080926	G	5200		ACTUATOR        	CNDAIR      	215T752204  						PWA   	PW120 	PW123       	 	NE  					DOOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			129  	129  							(CAN) FOUND LEAKING AT THE PREES LINE CONNECTION, TSO129HRS, TOTAL DROPS 398 FOUND LEAKING DURING AN INSPECTION BY THE T	ECHNICAL ENGINEER.										4	T			E20NE				 
	20081120		CE  	2008	11	20	CA081002007      	1	20080924	G	5553	04311481	FITTING         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					VERTICAL STAB	FRACTURED       	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) ACFT BROUGHT TO MX DUE TO ACFT NOT RESPONDING CORRECTLY, VERTICAL STABILATOR WAS INSPECTED AND A FRACTURE WAS FOUN	D IN THE BRACKET.  IT APPEARED TO BE A STRESS FRACTURE IN THE FITTING.  WE WOULD LIKE ALL CESSNA OWNERS TO UNDERSTAND TH	AT IF THE TAIL HITS THE GROUND OR IT RUBS THE GROUND IN ANY WAY THAT IT SHOULD BE INSPECTED.  THIS ACFT HAD BEEN INSPECT	ED APPROX 50 HOURS PRIOR AND THERE WAS NO FRACTURE AT THAT TIME.  ALL OF THE FITTINGS AND BOLTS RELATED TO THE ATTACH PO	INT OF THE VERTICAL FIN WERE REPLACED AND THE FIN WAS INSPECTED FOR ANY DAMAGE.  WE ARE GOING TO CONTINUE TO MONITOR THE	SE FITTINGS ON ALL 152`S AND IF FURTHER INFORMATION ABOUT THIS ISSUE BECOMES APPARENT TO US WE WILL UP DATE.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
	20081120			2008	11	20	CA081002008      	2	20080925	G	7414	10357584	DISTRIBUTOR GEAR	CONT        	106006141   															MAGNETO	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAGNETO RECEIVED WITH TEETH BROKEN OFF THE DISTRIBUTOR GEAR.																			 
	20081120		EA  	2008	11	20	CA081003001      	1	20080926	G	5610	NP13932211	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CAPTAINS SIDE WINDOW CENTER PANE SHATTERED ENROUTE.  MX CHANGED THE WINDOW.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081120		NE  	2008	11	20	CA081003002      	2	20081001	G	7397	1710101	WIRE HARNESS    			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					FADEC	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6526 								(CAN) FADEC WIRING HARNESS DAMAGED (WHICH REQUIRED REPLACEMENT) DUE TO THE LOWER SEAL ON THE PYLON PRE-COOLER LEAKING (N	O LEAK/HEAT DETECTION IN THIS AREA). ATTACHED ARE PICTURES. BELOW ARE THE FIN`S AFFECTED WITH TIMES AND CYCLES. ACFT IND	UCTED FOR THE FREEZE PROTECTION MOD.				2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081120			2008	11	20	CA081003003      	1	20080925	G	8011	149NL	HOUSING         																	STARTER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			43   								(CAN) REAR HOUSING DISCOVERED LOOSE DURING SCHEDULED MX.																			 
	20081120			2008	11	20	CA081003004      	1	20080912	G	8011	149NL	HOUSING         																	STARTER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			207  								(CAN) REAR HOUSING DISCOVERED LOOSE DURING SCHEDULED MX.																			 
	20081120			2008	11	20	CA081003005      	1	20080924	G	8011		ATTACH BOLT     		149NL       															STARTER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			655  								(CAN) MOTOR TO HOUSING ATTACH BOLTS LOOSE.																			 
	20081124		NE  	2008	11	24	CA081003006      	2	20080930	G	7322		FLOAT           	BENDIX      		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  					CARBURETOR	DAMAGED         	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) FLIGHT CREW REPORTS THAT THE ENGINE FALTERED ON SHORT FINAL AND QUIT COMPLETELY AS THE FLOATPLANE CAME OFF THE STE	P.  AFTER BEING TOWED TO THE DOCK, FUEL WAS OBSERVED POURING OUT OF THE CARBURETOR.  THE FLOAT VALVE APPEARED TO BE STUC	K IN THE FULL OPEN POSITION. CARBURETOR WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE.  THE CARBURETOR HAD BEEN INST	ALLED 2 HOURS PREVIOUS FROM OVERHAUL.			1	H	7	1 	3R	3	R	RC	A806    	5E1				 
	20081124		SW  	2008	11	24	CA081003007      	1	20080925	G	3233	LA11C2110	ACTUATOR        			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360LYC*   	41514	EA  					MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) LANDING GEAR FAILED TO EXTEND ELECTRICALLY. ACTUATOR TEAR DOWN REVEALED THE MOTOR HAD FAILED.						1	L	7	1 	3O	3	O		2A3     	1E10				 
	20081124		SO  	2008	11	24	CA081003009      	2	20081001	G	8530	652420902	THRU BOLT       								CONT  	O360  	IO360KB     	17025	SO  					NR 6 CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				855  							(CAN) ON A PRE-FLIGHT INSPECTION, THE PILOT NOTICED A LOOSE WASHER ON THE FRONT OF THE ENGINE.  AFTER FURTHER INSPECTION	 IT WAS DISCOVERED THAT THE TOP FWD ENGINE THROUGH BOLT FOR NR 6 CYLINDER WAS BROKEN ON THE CYLINDER SIDE.  THE LOOSE WA	SHER WAS BECAUSE THE BOLT SNAPPED AND THERE WAS NO TORQUE ON THE OTHER SIDE AND THE NUT HAD WORKED ITS WAY LOOSE (IT WAS	 NEVER FOUND).  THE BROKEN PIECE OF BOLT AND NUT FROM THAT SIDE WERE FOUND ON TOP OF THE FWD ENGINE BAFFLE.  ALL OTHER B	OLTS IN THE AREA WERE TORQUE CHECKED AND FOUND SERVICEABLE.  NO OTHER DEFECTS WERE NOTED.							3	O			E1CE				 
	20081124		CE  	2008	11	24	CA081004001      	1	20081001	G	3245	302247400	TUBE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	NLG	FOD             	W				O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			CA											(CAN) TUBE HAD A HOLE CHAFED IN IT - NO EVIDENCE OF FOD INSIDE TIRE FROM INITIAL ASSY TO CAUSE WEAR HOLE.						1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20081126		CE  	2008	11	26	CA081006001      	1	20081002	G	3250	05430223	STEERING SYS    			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  						INOPERATIVE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) INSTRUCTOR WITH A STUDENT PILOT ON BOARD REPORTED THAT ALTHOUGH RUDDER PEDAL TRAVEL APPEARED TO BE NORMAL DURING T	AXI, AT THE POINT OF LIFT OFF RUDDER PEDAL MOVEMENT WAS RESTRICTED TO RT RUDDER ONLY. RUDDER COULD NOT BE MOVED TO THE L	T. THE ACFT CONTINUED WITH A NORMAL CIRCUIT AND LANDED WITHOUT INCIDENT WHEREUPON THE RUDDER PEDAL MOVEMENT APPEARED TO 	RETURN TO NORMAL OPERATION. MAINT INSP WAS REQUESTED FOR THE ACFT. IT WAS DISCOVERED THAT THE LT STEERING TUBE ASSY, P/N	 0543022-3 HAD LOST THE CUSHIONING EFFECT OF THE INTERNAL SPRING. THIS IN EFFECT HAD LEFT THE TUBE ASSY TO ACT AS A SOLI	D ROD, WHERE AFTER LIFT OFF WITH THE NOSE OLEO EXTENDED AND THE NOSE WHEEL LOCKED IN THE CENTER POSITION, IT WOULD HAVE 	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
	20081124		GL  	2008	11	24	CA081006002      	1	20080929	G	2420	1707580A	CONVERTER       			BOMBDR	BD700 	BD7001A10   	1390006	GL  											DAMAGED         	W				O				OTHER                   				M	B	G	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	MULTIPLE FAILURE          	TX	TAXI/GRND HDL  	1			CA											(CAN) ON GROUND, DURING GROOMING THE ACFT, THE AC POWER DROPPED OFF.  WHEN IT WAS RE-APPLIED, COCKPIT DISPLAYS SHOWED AC	 SYSTEM IN MAGENTA (NO COMMUNICATION).  FOUND THE EXTERNAL AC/DC CONVERTOR CARD LOCATED IN THE AC POWER CENTER HAD A BUR	NED TRACE.  THE MICROPROCESSOR CARD LOCATED ABOVE THE AC/DC CONVERTER CARD HAD A SMALL AMOUNT OF SOOT BUT NO VISIBLE DAM	AGE.  THE PRIMARY LOGIC CARD WAS SOOTY AND , WHEN THE SOOT WAS WASHED OFF, A SMALL AREA ABOUT 3 SQUARE INCHES WAS DISCOL	ORED.  AC POWER CENTER  REPLACED TO DISPATCH THE ACFT.		2	L	7	2 	4F			RT	T00003NY					 
	20081124		NM  	2008	11	24	CA081006003      	1	20081001	G	3231		CONTROL ROD     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					NLG DOOR	BROKEN          	W				A				UNSCHED LANDING         				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT, THE CREW NOTED A VIBRATION AND BANGING NOISE FROM THE NOSE OF THE ACFT.  THE ACFT RETURNED AND THE G	ROUND CREW NOTED THAT THE RT NLG DOOR WAS OPEN AND THAT THE DOOR CONTROL ROD AND TENSION SPRING (PN 83232010-105) FOR TH	E RT DOOR WAS BROKEN.  THERE WAS NO DAMAGE TO THE SURROUNDING STRUCTURE.  THE CONTROL ROD WAS SHEARED AT THE UPPER PERMA	SWAGE ON THE ROD.  GEAR INDICATION WAS NORMAL TO THE CREW.  THE BARTS WHERE REPLACED AND THE ACFT RELEASED BACK TO SERVI	CE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20081120		SO  	2008	11	20	CA081006004      	1	20081003	G	7160	434179	GROMMET         		86245041    	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6D   	42305	EA  					CARB HEAT BOX	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			406  								(CAN) DURING A DEFECT RECTIFICATION ON OUR OTHER ACFT, IT WAS FOUND THAT THE LWR GROMMET AND BUSHING P/N 453-991 WAS MIS	SING ON THE LT ENGINE CARB HEAT BOX. THIS GROMMET SUPPORTS THE SHAFT IN THE CARB HEAT BOX. THIS PROMPTED THE INSP OF THI	S ACFT, WHICH FOUND THE BOTTOM GROMMET AND BUSHING MISSING FROM ITS LT ENGINE.				1	L	7	2 	3O	3	O		A19S0   	E286				 
	20081124		EA  	2008	11	24	CA081007001      	2	20081003	G	7320	312240015	FADEC           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 2 ENGINE	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			115  								(CAN) DURING PUSH-BACK FROM THE GATE WITH BOTH ENGINES RUNNING (PROPS FEATHERED), THE NR 2 ENGINE HAD AN UN-COMMANDED SH	UTDOWN WITH AN ASSOCIATED NR 2 ENG FADEC FAIL WARNING LIGHT AND POWERPLANT MSG.  INTERROGATION OF THE CDS REVEALED THE F	OLLOWING FAULT CODES: 705, 707, 734, MPT, 737, 740, 748 & 749. FIM TASKS ARE CURRENTLY IN WORK, BUT AS FAULT CODES 705 &	 707 ARE INDICATING AN INTERNAL FAULT IN THE FADEC.  FADEC REPLACED IAW AMM TASK 73-21-01-400-801, FAULT CODES CLEARED, 	PLA TRIM AND ENGINE RUNS CARRIED OUT SUCCESSFULLY.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081124		NE  	2008	11	24	CA081007002      	2	20080906	G	7200		ENGINE          			SKRSKY	S92   	S92A        	       	NE  	GE    	CT7TS 	CT78A       	30136	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) POST LANDING AND TAXI.  ACFT WAS STATIONARY WITH BOTH ENGINES IN THE GROUND IDLE POSITION WITH ROTORS TURNING.  PI	LOT OBSERVED ROTOR SPEED WAS NEARING A KNOWN "AVOID RANGE" AND ELECTED TO NUDGE THE NR 1 ENGINE CONTROL LEVER FORWARD TO	 INCREASE ROTOR SPEED SLIGHTLY ABOVE THE AVOID RANGE.  DURING THE EXECUTION OF THIS MARGINAL CONTROL LEVER MOVEMENT, THE	 RELATED ENGINE THEN UNEXPECTEDLY SHUTDOWN.  NO OTHER INDICATIONS OF A PROBLEM WERE OBSERVED BY EITHER PILOT.  THE HUMS 	DATA WAS DOWNLOADED AND DURING REVIEW IT WAS DISCOVERED THAT DURING THE CONTROL LEVER INCREASE, THE NR 1 ENGINE TGT SPIK	ED TO 1100 DEGREES C FOR A PERIOD OF 3 SECONDS BEFORE THE AUTOMATED PROTECTIVE CIRCUITS OF THE FADEC SHUT THE ENGINE DOW	2	G	7	2 	4U	4	U		R00024BO	E8NE				 
	20081124		NM  	2008	11	24	CA081007003      	1	20081006	G	5754	NAS86034NAS86	SCREW           			BOMBDR	CL600 	CL6002D15   	       	NM  	GE    	CF34  	CF348C5     	30050	NE  					SLAT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ALL SCREWS ON TOP OF WING UNDER THE SLATS WERE FOUND LOOSE. 2 SCREWS , 1 ON EACH SIDE, WERE FOUND PROTRUDING BEYON	D THE WING SURFACE CAUSING  MINOR DAMAGE TO THE UNDER SKING SURFACE OF THE SLAT. ALL SCREWS WERE TIGHTENED BACK.					2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081124		NM  	2008	11	24	CA081007004      	1	20080929	G	2130	10010602	CIRCUIT CARD    			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					CABIN PRESSURE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE AT APPROX 1500`, BLEED NR 1 AND NR 2 FAILED EICAS MSGS APPEARED, AND QRH CARRIED OUT (RESET) BUT U	NSUCCESSFUL. ACFT DID NOT PRESSURIZE, AND RETURNED TO BNA FOR MX.  OTHER PNS AND SNS AFFECTED:					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081120			2008	11	20	CA081007005      	4	20081007	G	3160	071015980301	CONTROLLER      			PILATS	PC12  	PC1247      	7090552	EU  	PWA   	PT6   	PT6A67      	52043	NE  					MFD	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			100  	100  							(CAN) THE ABOVE MFD CONTROLLER IS A JOYSTICK TYPE CONTROL THAT ALLOWS THE CREW TO MAKE SELECTIONS ON THE MFD SCREEN IN T	HE MFG APEX SYS. THE JOYSTICK FAILS TO MOVE THE CURSOR TO THE RT AS DISPLAYED ON THE MFD SCREEN. THE CONTROLLER WAS REPL	ACED WITH A NEW ITEM THAT CLEARED THE PROBLEM THIS IS THE SECOND REPLACEMENT ON THIS ACFT SINCE NEW 150 HRS TT.				1	L	7	1 	4T	4	T	RT	A78EU   	E26NE				 
	20081126		EU  	2008	11	26	CA081007006      	1	20081007	G	2910	MS287786	O-RING          			BAG   	JETSTM	JETSTM3112  	1500220	EU  	GARRTT	TPE331	TPE33110    	29053	NE  	ROTOL	R333	R333482F12  	GL  	COUPLING	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING GEAR DOWN LANDING CHECKS, ONLY NOSE GEAR LOCKED, BOTH MLG UNSAFE.  REQUESTED LOW AND OVER-CYMM FSS CONFIRME	D 3 GEAR DOWN. RE-POSITIONED TO A SAFE AREA AND PERFORMED ITEMS LISTED ON QRH. PUMPED GEAR DOWN MANUALLY, GEAR WAS CONFI	RMED 3 DOWN AND LOCKED. LANDED, WITH NO STEERING AND LIMITED BRAKE USE. STOPPED ACFT ON TAXIWAY A.  TOWED TO HANGER WITH	 PAX EMERGENCY SERVICES ON STANDBY FOR THIS INCIDENT. MAINT INSP CONFIRMED LT HYDR PUMP PRESSURE RETURN INLET BANJO COUP	LING BASE O-RING HAD FAILED, CAUSING EXCESSIVE FLUID LOSS.  REMOVED AND REPLACED DEFECTIVE O-RING WITH NEW.  HYD SYS REP	LENISHED GEAR, FLAP, STEERING, BRAKE SYSTEMS BLED, GEAR SWINGS C/O AND SYS F/C C/O SYS SERVICED AND L/C C/W.	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
	20081124		EU  	2008	11	24	CA081007007      	1	20080929	G	5310	350A38101832	CROSSBEAM       			SNIAS 	350   	AS350BA     	8680817	EU  	ALLSN 	250C  	250C30      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4692 	702  							(CAN) A BI DIRECTIONAL CROSS BEAM WAS SENT OUT FOR NDT INSPECTION AND A CRACK INDICATION WAS FOUND INBD RADIUS OF CROSS 	BEAM WHERE THE LAMINATED MOUNT ATTACHES. A SECOND NDT INSPECTION WAS PERFORMED WITH THE SAME RESULTS.					1	G	7	1 	3U	3	U	NC	H9EU    	E1GL				 
	20081124		CE  	2008	11	24	CA081007008      	1	20081007	G	3340	CM358910	SWITCH          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					TAXI LIGHT	INOPERATIVE     	W				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			CA			566  								(CAN) TAXI LIGHT SWITCH FAILED WITH 566 HRS OF ACFT OPS FAULT WAS FOUND WHEN TRYING TO CHECK TAXI LIGHT FOR OPS.  SWITCH	 WAS REPLACED 7 MONTHS AGO AND 566 HRS OF OPS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081124		CE  	2008	11	24	CA081007009      	1	20081001	G	3397	903641241	C/BREAKER PANEL 			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT642A      		NE  					COCKPIT	BURNED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) PILOTS REPORTED FLAMES AND FIRE FROM LOWER RT CORNER OF THE RT CIRCUIT BREAKER PANEL AND MADE AN EMERGENCY LANDING	. THE CIRCUIT BREAKER FOR THE EDGE LIGHTED PANEL LIGHTS OPENED AS A RESULT OF THE SHORT AT 1 BULB BUT NOT BEFORE THE HEA	T HAD BURNED PART WAY THROUGH THE EDGE LIGHTED PANEL AND STARTED TO HEAT THE OVER LYING CIRCUIT BREAKER PANEL. NO FURTHE	R DAMAGE WAS NOTED. THIS EDGE LIGHTED PANEL WAS PREVIOUSLY INSPECTED AS PER THE MM ABOUT 565 HOURS AGO.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081124		SW  	2008	11	24	CA081007010      	1	20081002	G	3240	5011639	DISC            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	29073	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	BRAKE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS BRAKE ASSEMBLY WAS REMOVED FROM ACFT ON THE RT - O/B GEAR FOR BRAKE WEAR BEYOND LIMITS.  UPON TEAR DOWN THE L	UGS WERE FOUND TO HAVE WORN APPROXIMATELY 40% WHILE THE RIM SIDE HAD MINIMAL WEAR AND THE RIM WAS RETURNED TO SERVICE.  	THIS TYPE OF WEAR IS NOT COMMON AS THEY WEAR CONSISTENTLY SIMILAR.  FURTHER INVESTIGATION WILL BE ACCOMPLISHED IN ORDER 	TO POSSIBLY DETERMINE OTHER CAUSES AS TO WHY THE UNEVEN WEAR PATTERN.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081126		CE  	2008	11	26	CA081008001      	1	20080818	G	3220		FORK            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6816 								(CAN) DURING A ROUTINE OPERATION, NR 2 INSP, A SUSPECTED CRACK WAS FOUND ON NLG FORK.  EDDY CURRENT REVEALED A LARGE DEF	LECTION IN THE SUSPECTED AREA. SUBSEQUENTLY THE INSP WAS CONDUCTED ON THE OPPOSITE SIDE OF THE NLG FORK WITH THE SAME RE	SULTS. ADDITIONALLY FPI WAS ALSO DONE TO SHOW VISUALLY UNDER BLACK LIGHT. CRACKS WERE CLEARLY VISIBLE ON BOTH SIDES OF T	HE FORK UNDER THE BLACK LIGHT. THE ACFT WAS REMOVED FROM SERVICE AND A NEW NLG FORK ASSY WAS ORDERED FROM MFG AND INSTAL	LED UPON ARRIVAL.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081124		GL  	2008	11	24	CA081008002      	1	20080923	G	2410	2224121400	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ALTERNATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			715  								(CAN) ON SEPTEMBER 2, 2008, DURING A ROUTINE 100 HOUR INSPECTION THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE CRACKED	 ON THE INSIDE RADIUS OF THE BRACKET RIGHT NEXT TO 1 OF THE 2 MOUNTING BOLT HOLES. THIS WAS THE SECOND CRACKED BRACKET F	OUND ON THIS ACFT AND BOTH CRACKS HAVE BEEN LOCATED IN THE IDENTICAL LOCATIONS.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
	20081124		GL  	2008	11	24	CA081008003      	1	20080923	G	2410	2224121400	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ALTERNATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			448  								(CAN) ON MARCH 14, 2008, DURING A ROUTINE 100 HOUR INSPECTION THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE CRACKED ON	 THE INSIDE RADIUS OF THE BRACKET RIGHT NEXT TO 1 OF THE 2 MOUNTING BOLT HOLES.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
	20081124		SW  	2008	11	24	CA081008006      	1	20081007	G	5210	205D10282	WINDOW FRAME    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					JUMP DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 10 INCH CRACK FOUND AT UPPER LT CORNER OF WINDOW FRAME.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
	20081124		NM  	2008	11	24	CA081008007      	1	20081008	G	5210	SB003T0023	PANEL           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					COCKPIT DOOR	MISALIGNED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLEX IN LAV WALL IS CAUSING SIGNIFICANT IN-SERVICE MISALIGNMENT OF PONS INSTALLED IN LATCH HOUSING USING TTF-SB-03	T002-001.  REFER TO PROTECTED "A" AD CF-2008-26R1 AND STC SA03-70, SB TTF-SB-03T002-001 REV "D".					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20081124		EA  	2008	11	24	CA081009001      	1	20081002	G	3810	5000120701	WATER HEATER    			CNDAIR	CL601 	CL6013A     	8070802	EA  										FWD GALLEY	DAMAGED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT SMOKE WAS OBSERVED COMING OUT OF THE FUEL CONTROL PANEL IN THE FORWARD GALLEY.  THE WATER HEATER INSU	LATION BLANKET IN THE FORWARD GALLEY HAD EVIDENCE OF HEAT DAMAGE.  INSTALLATION OF THIS PART IN THE FORWARD GALLEY OF TH	E ACFT IS A PART OF SUPPLEMENTAL TYPE CERTIFICATE ST09049SC.  THE PART IN QUESTION HAS BEEN FORWARDED TO THE TSB.				2	L	7	2 	4F			RT	A21EA   					 
	20081124		CE  	2008	11	24	CA081009002      	1	20080918	G	5753	S16612	SWITCH          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					TE FLAP	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			5911 								(CAN) THE FLAP SWITCH SHOULD SPRING BACK TO OFF POSITION WHEN PRESSURE IS RELEASED. THE PILOT SELECTED 20 OF FLAP TOOK 	PRESSURE OFF SWITCH BUT THE FLAPS EXTENDED TO 40 NEW SWITCH INSTALLED.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081124		GL  	2008	11	24	CA081009003      	2	20081002	G	7323	23065123	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1234 								(CAN) BENDIX KING GOVERNOR NOT RESPONDING WHEN BEEPED,						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081124		NM  	2008	11	24	CA081009004      	1	20081003	G	2421	ALX8521R	ALTERNATOR      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  						INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				331  							(CAN) ALTERNATOR LIGHT ILLUMINATED IN FLIGHT, ALTERNATOR CHECKED AND NOT CHARGING.						1	G	7	1 	3O	3	O		H10WE   	E286				 
	20081124		NE  	2008	11	24	CA081009005      	2	20080929	G	7414	10600646201	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			90   								(CAN) ENGINE TACH FLUCTUATING, MAGNETO REPLACED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081124		WP  	2008	11	24	CA081009006      	1	20080930	G	2435	BC3151004	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  						MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				359  							(CAN) STARTER NOT ENGAGING.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081124		NM  	2008	11	24	CA081009007      	1	20081009	G	2781	651781823	SWITCH          	DECOTO      		BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15      	52051	NE  					SLAT ACTUATOR	FAILED          	W				J	A			DUMP FUEL               	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA				47   							(CAN) JUST AFTER DEPARTURE FROM YYZ, THE PILOTS NOTICED WHEN SELECTING FLAPS 5 TO FLAPS 2, THE LEADING EDGE FLAP INDICAT	OR ON THE FORWARD PANEL WENT MOMENTARILY GREEN THEN BACK TO AMBER.  THE LEADING EDGE INDICATOR ON THE REAR PANEL INDICAT	ED THE NR 1 LEADING EDGE IN TRANSIT.  FUEL WAS DUMPED IN ORDER TO REDUCE LANDING WEIGHT OF THE ACFT AND THE ACFT RETURNE	D TO YYZ.  MX TROUBLESHOT THE SYSTEM AND INSTALLED A JUMPER CABLE ON THE SLAT ACTUATOR TO ENABLE THE ACFT TO DEPART.			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081124		NM  	2008	11	24	CA081009008      	1	20081008	G	2497		WIRE            			BOMBDR	CL600 	CL6002D15   	       	NM  	GE    	CF34  	CF348C5     	30050	NE  						CHAFED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) FLIGHT ATTENDANT REPORTED A BURNING ODOR IN THE CABIN.  THE ACFT LANDED UNEVENTFULLY.  THE CAUSE OF THE ODOR WAS T	RACED TO CHAFED WIRE ABOVE THE FORWARD LAVATORY.					2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081124		GL  	2008	11	24	CA081009009      	1	20080927	G	2497		WIRE            	KELLY       		DIAMON	DA40  	DA40        	2990002	GL  	CONT  	IO360 	IO360*      	17025	CE  					ALTERNATOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) A+ TERMINAL MELTED OFF ALTERNATOR AND LOOSE. PROBLEM CAUSED BY BROKEN TERMINAL ON A+ WIRE GOING TO ALTERNATOR.  WI	RE WAS ORIGINALLY VERY TIGHT CAUSING THE BREAKAGE, THEN IT ARCED CAUSING HEAT AND EVENTUAL FAILURE.					1	L	7	1 	3O	3	O	NT	A47CE   	E1CE				 
	20081126		NE  	2008	11	26	CA081009010      	2	20080929	G	7532	PN1422010	CLEVIS          			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					BLEED VALVE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) (ENGINE INTAKE VARIABLE BLEED VALVE ACTUATOR) INTERFERENCE HAS OCCURRED BETWEEN THE SUBJECT CLEVIS LUG AND ADJACEN	T HARDWARE.  THE DAMAGE APPEARS TO BE A RESULT OF CONTACT WITH AN ADJACENT BOLT HEAD.  ACTUATOR ASSY: P/N 8100-052, S/N 	WYGB1199 (CLEVIS: P/N 1422-010 [REF CMM 75-30-02, FIGURE 01, ITEM 010)				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081126		GL  	2008	11	26	CA081009011      	1	20081007	G	2720	2227271100	RUDDER PEDAL    			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	COCKPIT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3498 								(CAN) ACFT WAS INSPECTED BY MAINT TO REPLACE A DEFECTIVE RUDDER PEDAL ADJUSTING CABLE. UPON COMPLETION OF THE JOB IT WAS	 NOTICED THAT THE SLIDE ASSY WAS NOT ABLE TO MAKE FULL TRAVEL. CLOSER INSP FOR OTHER SYMPTOMS REVEALED THAT THE RUDDER C	ABLE HAD WORN THROUGH THE S-TUBE THAT IS WELDED TO THE PEDAL ASSY. CABLE WAS EXPOSED THROUGH THE LWR BEND OF THE S-TUBE 	TO A POINT WHERE IT JAMMED IN ITS WEAR HOLE AND RESTRICTING THE SLIDE ACTION. THE PEDAL ASSY AND THE CABLE WERE REMOVED 	FOR CLOSER INSP AND REPLACEMENT PARTS ARE ON ORDER.   WEAR ON THE S-TUBE BECOMES CRITICAL WHEN THE CABLE BECOMES VISIBLE	 FROM THE OUTSIDE OF THE TUBE. IT IS ALSO AN AREA THAT YOU WOULD NOT EXPECT THIS TO HAPPEN THEREFORE IT COULD BE OVERLOO	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081126		NM  	2008	11	26	CA081010001      	1	20080927	G	2820		LINE            			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					FUEL SYSTEM	CRACKED         	W				O				OTHER                   				K	E		FLUID LOSS                	VIBRATION/BUFFET          		AP	APPROACH       	1			CA											(CAN) EXPERIENCED A LT ENG FUEL LEAK DURING APPROACH/LANDING.  MAINT IDENTIFIED AND REPLACED A CRACKED P/N BRH19082 FUEL	 PIPE. ON 28 SEP/08, ACFT WAS FERRIED. WHEN ACFT WAS ON TAXI INTO THE RAMP, ANOTHER ACFT BEHIND REPORTED FUEL POURING FR	OM UNDER THE LT ENGINE.  MAINT FOUND THAT PIPE WAS CRACKED AGAIN. SEVERAL FIRE LOOP BRACKETS WERE ALSO FOUND CRACKED. TH	E LT ENG WAS REPLACED, S/N 13243 OFF, THIS ENG HAD JUST BEEN INSTALLED ON 2 SEP/08, AT TIME OF REMOVAL: TSI 55 HOURS, CS	I 35 CYCLES. HIGH VISIBILITY EVENT BY THE FAA DUE TO FUEL LEAK. ENG 13243 IN FOR INVESTIGATION. TEST BED RUN CONFIRMED H	IGH VIBRATION EMANATING FROM ACCY GEARBOX, WHEN ENGINE POWERED UP AN OIL LEAK EMANATED FROM THE GEARBOX AT FUEL PUMP LOC	2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
	20081124		NE  	2008	11	24	CA081010002      	2	20081009	G	7310	63E951	HOUSING         	GRIMES      		CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					FUEL FILTER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) MX DISCOVERED NR 1 ENGINE FUEL FILTER ASSEMBLY LEAKING FROM THE TOP OF THE FILTER HOUSING.  HOUSING IS EITHER CRAC	KED AROUND TOP FITTING OR IS LEAKING THROUGH PRC AROUND FITTING.  FUEL FILTER ASSEMBLY 4106T62P01 REF IPC 73-11-00 FIG 1	 ITEM 110A INSTALLED.  ENGINE TTSN: 26020 HOURS, CYCLES 21453. AFTT: 31453 HOURS, CYCLES: 26057				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081124		EA  	2008	11	24	CA081010003      	1	20081010	G	2750	855D10011	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					RT WING TE FLAP	UNSERVICEABLE   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA			10100	10100							(CAN) ON APPROACH, AND UPON INITIAL FLAP SELECTION THE CREW RECEIVED FLAP FAILURE CAUTION MSG.  CREW CARRIED OUT A FLAP 	ZERO LANDING.  CREW SAID LANDING WAS UNEVENTFUL.  NO EMERGENCY DECLARED, NO CALL OUT REQUIRED.  WILL UPDATE INFO AS RECE	IVED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081124		SW  	2008	11	24	CA081010004      	1	20081003	G	3040		HEATER          			GULSTM	680   	680         	0141602	SW  	PWC   	PW306 	PW306C      	52169	NE  					WINDSHIELD	SMOKE           	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA			613  								(CAN) SMOKE DETECTED IN COCKPIT ON ENGINE STARTUP. PROBLEM ISOLATED TO LT WINDSHIELD.  RECTIFIED BY REPLACEMENT OF PART.						1	H	7	2 	3O	4	F		2A4     	E35NE				 
	20081124		EA  	2008	11	24	CA081010005      	1	20081002	G	5343	VALTBS112091	ATTACH FITTING  			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					WING/MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE WING GEAR/STRUT ATTACH FITTING TO BE CORRODED (LEVEL 3).						1	H	7	1 	3T	4	T		A806    	E4EA				 
	20081124		EA  	2008	11	24	CA081010006      	1	20081002	G	2731	C2T29A	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ELEVATOR TRIM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE 100 HOUR INSPECTION A AME FOUND THE ELEVATOR TRIM TORQUE TUBE TO BE CRACKED, PART WAS REPLACED AN	D CUSTOMER WAS ADVISED.					1	H	7	1 	3T	4	T		A806    	E4EA				 
	20081124		EA  	2008	11	24	CA081010007      	1	20081002	G	3246	VALBVS12601	FITTING         			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					MLG FLOAT	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION A AME FOUND THE FLOAT FITTING TO HAVE TYPE 3 CORROSION THAT CAUSED FITTING TO SPLIT. 	 FITTING REPLACED WITH NEW PART.					1	H	7	1 	3T	4	T		A806    	E4EA				 
	20081124		EA  	2008	11	24	CA081010008      	2	20081003	G	7414	4371	MAGNETO         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  						MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			156  								(CAN) POOR MAG DROP, TIMING LIGHT FLICKERING BEFORE 25 DEGREES.  MAGNETO REPLACED WITH A SERVICEABLE MAGNETO.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081124		EA  	2008	11	24	CA081010009      	2	20081003	G	7414	4371	MAGNETO         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  						MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			156  								(CAN) POOR MAG DROP.  TIMING LIGHT FLICKERING BEFORE 25 DEGREES.  REPLACED WITH SERVICEABLE MAGNETO.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
	20081124		EA  	2008	11	24	CA081010010      	2	20081002	G	7321		SCREW           			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FCU	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION POST RUN UP THE AME FOUND THE IDLE NEEDED TO BE ADJUSTED.  UPON LOOSENING IDLE SCREW 	JAM NUT IDLE SCREW FAILED DUE TO LEVEL 3 CORROSION. FCU REMOVED AND SENT FOR REPAIR.					1	H	7	1 	3T	4	T		A806    	E4EA				 
	20081124		SW  	2008	11	24	CA081010011      	1	20081010	G	3500	AS4857D01	TEE FITTING     			GULSTM	680   	680         	0141602	SW  	PWC   	PW306 	PW306C      	52169	NE  					OXYGEN SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1251 								(CAN) DURING MX WALK AROUND FOUND LT OXYGEN SYSTEM LEAKING.  UPON INVESTIGATION FOUND TEE FITTING LOCATED AT LT FUSELAGE	 OXYGEN GAUGE CRACKED AT 2 POINTS.  IT APPEARS THAT UPON ORIGINAL INSTALLATION OF FITTING IT WAS OVER TORQUED.  FITTING 	REPLACED WITH NEW.  LEAK CHECKS CARRIED OUT.  SYSTEM FUNCTION CHECKED SERVICEABLE.				1	H	7	2 	3O	4	F		2A4     	E35NE				 
	20081124			2008	11	24	CA081014001      	1	20081010	G	6100		SHAFT           								PWA   	118   	PW118       	 	NE  					PROPELLER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) EIR PW100-0477 CRACKED PROPELLER SHAFT.											4	T			E20NE				 
	20081124		CE  	2008	11	24	CA081014002      	1	20081008	G	2730	07606861	CONTROL TUBE    			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	LT ELEVATOR	GOUGED          	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA			9986 								(CAN) THE BOLT PN AN21-10 ATTACHING THE LT ELEVATOR CONTROL CABLE PN 0510105-90 TO THE LT BELLCRANK CONTROL ARM ASSEMBLY	 PN 0760686-1 IS RUBBING ON THE LT BELLCRANK CONTROL TUBE SUPPORT PN 0760693-1.  THE DAMAGE IS 0.039 DEEP, 1.750 LONG AN	D 0.250 WIDE.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
	20081124		CE  	2008	11	24	CA081014003      	1	20081009	G	2731	071250012	ACTUATOR        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	HORIZ STAB TRIM	SEPARATED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA			100  								(CAN) ACFT HORIZONTAL STAB TRIM JAM ON LANDING. ELEVATOR CONTROLS BECAME LIGHT.  ACFT LANDED WITHOUT INCIDENT.  UPON INS	PECTION AT THE DOCK, THE PILOT FOUND THE HORIZONTAL STAB WAS COMPLETELY LOOSE,  STAB COULD BE MOVED FULL TRAVEL UP AND D	OWN WITH NO RESISTANCE FROM THE TRIM JACKS.  MX FOUND THE TRIM JACK BARREL COULD BE SLID ON TO THE SCREW OF THE SCREW JA	CK WITH HAND PRESSURE, WHEN NORMALLY THEY HAVE TO BE SCREWED ON TO THE ACTUATOR SCREW.  BOTH BARRELS WERE FOUND TO HAVE 	THREADS ONLY ON 1 SIDE OF THE BARREL, INSTEAD OF COMPLETELY AROUND THE INSIDE OF THE BARREL.  THE ACTUATORS WERE REPLACE	D AND CESSNA DISTRIBUTOR CONTACTED DUE TO THE ACTUATORS IN QUESTION WERE ONLY 3 MONTHS OLD AND 100HRS. SINCE NEW TIME IN	1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
	20081124		NM  	2008	11	24	CA081014004      	1	20080917	G	5210	1700375200	SEAL            			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					PAX DOOR	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) T FWD PAX DOOR AFT LATERAL SEAL (PN 170-03752-001) WAS FOUND GOUGED AT 3 LOCATIONS. PLEASE REFER TO THE ATTACHED P	ICTURES FOR DETAILS, TYPICAL DAMAGE SEEN TO THE PAX/SERVICE DOOR CUTOUT SEAL RESTS.  EMB HAS ISSUED A TYPICAL IC APPRO	VAL THAT PERMITS PERMANENT BLENDING OF UP TO 20% THICKNESS.				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081124		NE  	2008	11	24	CA081014005      	2	20081006	G	7322	87327003	ARM             	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360A1H6   	42294	NE  					CARB HEAT	SEPARATED       	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			379  								(CAN) THE ACFT RETURNED TO THE RAMP WITH REPORTED RT CARB HEAT U/S. INVESTIGATION REVEALED THE WELD SECURING THE ACTUATO	R ARM ONTO THE CARB AIR DOOR HAD BROKEN CAUSING THE ARM TO SEPARATE FROM THE SHAFT.  THE WELD APPEARED TOO THIN IN COMPA	RISON TO THE LT ENGINE CARB AIR DOOR ASSY.				1	L	7	2 	3O	3	O		A19S0   	E286				 
	20081124		SO  	2008	11	24	CA081014006      	1	20081006	G	7160	434179	GROMMET         	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360A1H6   	42294	NE  					AIR BOX	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			379  								(CAN) DURING A DEFECT RECTIFICATION ON THE CARB AIR DOOR ON THE RT ENGINE IT WAS DISCOVERED THAT THE LT ENGINE CARB AIR 	DOOR LOWER SHAFT SUPPORT BUSHING PN, 453-991 AND GROMMETT WERE MISSING.					1	L	7	2 	3O	3	O		A19S0   	E286				 
	20081126		CE  	2008	11	26	CA081014007      	1	20081001	G	3246	1368520629	BEARING         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					WHEEL	FAILED          	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											(CAN) LT MLG OTBD MAIN WHEEL ASSY BECAME DETACHED FROM THE AXLE ASSY, ONLY BEING HELD ON BY THE OUTER MAIN WHEEL AXLE NU	T AND BRG CONE.  INITIAL INVESTIGATION CONFIRMED THAT THIS WAS THE RESULT OF AN EXTREME BEARING FAILURE. FAILURE WAS TO 	SUCH EXTENT THAT IT ACTUALLY WELDED THE INNER BRG RACE PERMANENTLY TO THE AXLE AND HEAT TRANSFER TO THE NR2 WHEEL ALSO R	ESULTED IN A BEARING BURN WHICH IS NOT SEVERE IN MATTER BUT IS AN INDICATION OF HOW FAR THE INITIAL FAILURE EXTENDED. DA	MAGE REQUIRED  REMOVAL OF THE LT GEAR LEG AND INSTALLATION OF A SERVICEABLE GEAR LEG. BOTH MAIN WHEEL ASSEMBLIES AFFECTE	D WERE REPLACED. ACFT WAS THEN RETURNED TO SERVICE. ONE WHEEL ASSY WAS DESTROYED AND THE OTHER SENT OUT FOR TESTING. BEA	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
	20081126		SW  	2008	11	26	CA081014009      	1	20080904	G	3397		WIRE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					AT NAV LIGHT	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) PILOT TURNS ON ALL REQUIRED BREAKERS FOR FLIGHT INCLUDING NAV LIGHTS. PRE LIFT-OFF THE PILOT NOTES THE BREAKER FOR	 THE NAV LIGHTS AT MIDPOINT. PILOT RESETS SWITCH AND LIFTS OFF. AS THE ACFT FLIES THROUGH 300 FT,  THE PILOT TURNS ON TH	E HEATER AND IN A FEW SECONDS SEES A MIST COMING FROM OVERHEAD PANEL. HEATER IS SWITCHED OFF THEN PILOT REALIZES ITS SMO	KE FROM HOT WIRES. BATTERY, GENERATOR IS SWITCHED OFF AND ACFT RETURNS UNEVENTFUL TO THE TAKEOFF AREA. UPON INVESTIGATIO	N, AN INITIAL SHORT IN THE NAVIGATIONAL LIGHTS CAUSED THE BREAKER TO TRIP. THE PILOT RESETS THE BREAKER WHICH CAUSES THE	 BREAKER POINTS TO WELD AND MAINTAIN CURRENT TO THE SHORTED NAV LIGHTS. THIS CAUSED THE WIRE FROM THE BUSS TO THE BREAKE	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081124		CE  	2008	11	24	CA081015001      	1	20081006	G	2910	6000100184	LINE            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3249 								(CAN) RETURN LINE FROM HYDRAULIC RETURN FILTER TO HYDRAULIC RESERVOIR 1/2" CRACK AT 90 DEGREE BEND ON LINE. CAUSE, MAIN 	HYDRAULIC SYSTEM RETURN LINE CHATTERING AGAINST A HYDRAULIC LINE WHICH GOES FROM THE AUXILIARY HYDRAULIC PUMP TO AUXILIA	RY PUMP INLINE FILTER.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
	20081124		EA  	2008	11	24	CA081015002      	2	20081006	G	8530	AEL11795	SPRING          			BNORM 	BN2   	BN2B27      	7080227	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	INTAKE VALVE	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			333  								(CAN) DURING INSPECTION OF LYCOMING SB 388C FOUND BROKEN INNER SPRING PART NR AEL11795 ON INTAKE AND EXHAUST VALVE.						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
	20081124		NE  	2008	11	24	CA081015003      	2	20081015	G	7497	BL60064620	WIRE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	MISROUTED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1287 							(CAN) TACH WIRE CHAFING ON TACH POINT CONNECTOR TACH WIRES INCORRECTLY ROUTED.  TCM SB663A NOT COMPLIED WITH FOR WIRE RO	UTING.  LAST MX ON MAGNETO WAS PRO AERO.  MAGNETO WAS REMOVED DUE TO ENGINE/ACFT OVERSPEED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081124		NE  	2008	11	24	CA081015004      	2	20081015	G	7497	10400586	WIRE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					TACH	MISROUTED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			235  								(CAN) TACH WIRES INCORRECTLY ROUTED COIL PRIMARY WIRE INCORRECTLY ROUTED. TCM SB663A NOT COMPLIED WITH FOR WIRE ROUTING.	  MAGNETO WAS REMOVED FOR ENGINE/ACFT OVERSPEED.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081124		NE  	2008	11	24	CA081015005      	2	20081015	G	7497	10400586	WIRE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					TACH	PINCHED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			90   								(CAN) TACH WIRE WAS PINCHED BETWEEN HOUSING AND CAPACITOR TACH WIRES INCORRECTLY ROUTED TCM SB663A NOT COMPLIED WITH FOR	 WIRE ROUTING MAGNETO WAS REMOVED FOR FLUCTUATING ENGINE TACH NEEDLE .					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081124		EA  	2008	11	24	CA081015006      	2	20081015	G	7497	10400586	WIRE            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TACH	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			151  								(CAN) TACH WIRES CHAFED THROUGH AND GROUNDING TO THE COIL PRIMARY CONNECTOR.  TACH WIRES INCORRECTLY ROUTED TCM SB663A N	OT COMPLIED WITH FOR WIRE ROUTING.  VERY HIGH RESISTANCE FOUND BETWEEN THE TERMINALS OF THE TACH POINTS, WHEN CLOSED 120	0-1500 OHMS, PROBLEM IS BLACK COATING ON TACH POINT ARM CAUSING A HIGH RESISTANCE.  MAGNETO REMOVED FROM ACFT BECAUSE IT	 WANTED TO OVERSPEED.			1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081124		NM  	2008	11	24	CA081016001      	1	20081010	G	2781	1702286A	SENSOR          			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					FLAP SKEW	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			1688 								(CAN) FLIGHT WAS INBOUND WHEN THE CREW HAD A FAILURE ON SLAT/FLAP 1 SELECTION.  ALSO SPOILER FAULT, AOA FAIL AND SHAKER 	ANTICIPATED CAS MSGS.  THE ACFT LANDED AND TAXIED TO THE GATE WITH HOT BRAKES.  FOUND OPEN CIRCUIT BETWEEN PINS 2 AND 4 	OF THE LT OB SKEW SENSOR.  REPLACED SENSOR AS PER MM 27-83-01, CHECKED SERVICEABLE. ALL OTHER FAULTS CORRELATED TO SLAT 	FAILURE.			2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081124		NM  	2008	11	24	CA081016002      	1	20081006	G	2781	1702286A	SENSOR          			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					SLAT SKEW	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH, WHEN FLAP 2 SELECTED, EICAS SLAT FAIL MSG.  QRH CARRIED OUT.  UNEVENTFUL LANDING. SKEW SENSOR 2 AND 3	 AFFECTED AND REPLACED PER AMM 27-83-01.  OPS CHECK SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081126		EA  	2008	11	26	CA081016003      	1	20081010	G	4930	MS29513021	O-RING          			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF348E5A1   	30062	NE  					EMI FILTER	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			2790 								(CAN) ACFT, PRIOR TO ENG START APU HAD AN UNCOMMANDED SHUTDOWN. WHILE CARRYING OUT COCKPIT TROUBLESHOOTING PILOTS OBSERV	ED APU BOOST PUMP FAIL LIGHT WAS ILLUMINATED. APU BOOST PUMP WAS SUSPECT BECAUSE IT HAD JUST BEEN CHANGED THE PREVIOUS D	AY FOR SAME SNAG. BOOST PUMP ELECTRICAL CONNECTOR MALE PINS WERE FOUND CHARRED AND MELTED.  FEMALE PORTION OF CONNECTOR 	WAS ALSO FOUND CHARRED AND FUEL SOAKED. SUSPECT O-RING THAT PREVENTS FUEL FROM ENTERING CONNECTOR HAD FAILED ALLOWING FU	EL TO DEGRADE THE INSULATION MATERIAL TO THE POINT WERE THE PINS SHORTED OUT. A NEW EMI FILTER HARNESS AND BOOST PUMP WE	RE INSTALLED AND ACFT RETURNED TO SERVICE.  FYI THE APU BOOST PUMP FUEL IS USED TO COOL.  APU LUBRICATING OIL. WITH NO F	2	L	7	2 	4F	4	F	RT	A21AE   	E00063EN				 
	20081124		NE  	2008	11	24	CA081016004      	2	20081008	G	7310	10608486	HOSE            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUEL SYSTEM	LEAKING         	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING DEPARTURE OF THE ACFT PRIOR TO ENGINE START, FUEL WAS NOTICED LEAKING FROM NR 3 ENGINE.  MX REQUESTED NORMA	L ENGINE START TO VERIFY FUEL LEAK.  ENGINE WAS SHUT DOWN, AND ACFT TOWED BACK TO GATE FOR FURTHER INVESTIGATION.  THE F	UEL HOSE ASSEMBLY WAS R&R WITH A SERVICEABLE ASSEMBLY.  ENGINE GROUND RUN WAS CARRIED OUT AND LEAK CHECKED WITH NO FURTH	ER LEAKS OBSERVED.  THE ACFT WAS RETURNED TO SERVICE.			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081124		EA  	2008	11	24	CA081016005      	1	20081014	G	2751	601R930301	TRANSMITTER     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					FLAP POSITION	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) CLIMBING THROUGH 12000 FT AT 250 KIAS ACFT NOSED OVER AS FLAPS WENT TO AT LEAST 25 DEGREES AND AUTOPILOT KICKED OF	F.  ACFT SLOWED TO 200 KIAS WHILE RETURNING TO DEPARTURE AIRPORT.  FLAPS CONTINUOUSLY CYCLED FROM 0 TO 12 DEGREES.  CIRC	UIT BREAKERS 1F4 AND 2F4 WERE PULLED.  A 0 DEGREE FLAP LANDING WAS PERFORMED.  MX REPLACED THE FLAP POSITION TRANSMITTER	 AND THE SKEW DETECTION HARNESS PN K601R50533-3. AFTT: 27877:46, CYCLES: 23108.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081126		NM  	2008	11	26	CA081016006      	1	20081008	G	2782	1703911	ACTUATOR        			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					NR 4 SLAT	MALFUNCTIONED   	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA			4135 								(CAN) SLAT FAIL ON APPROACH CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. T/S IAW FIM, SLAT INHIBIT CLEARED, O	PS CHECK PASSED. CONSIDERED TRANSITORY CONDITION OF THE SLAT CONTROL SYS. 2 SLAT ACTUATORS REPLACED: LT SLAT ACT POS 04L	 REPLACED, P/N S/N AND TIMES GIVEN ABOVE. ALSO, RT NR 5 SLAT ACTUATOR REPLACED, P/N 1703909, S/N 0174, FH: 8052, FC: 366	5.			2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081126			2008	11	26	CA081016007      	2	20081015	G	7414	D6RN3200	MAGNETO         																	RT ENGINE	INOPERATIVE     	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PREFLIGHT RUN-UP RT ENG, RT MAGNETO EXPERIENCED EXCESSIVE DROP AND WAS RUNNING ROUGH. UPON INVESTIGATION OF	 THE MAGNETO IT WAS FOUND THAT THE DISTRIBUTOR GEAR BUSHING HAD WORN IN THE DISTRIBUTOR BLOCK HSG CAUSING A MISS FIRING 	CONDITION. MAGNETO WAS REPLACED.																	 
	20081126		NM  	2008	11	26	CA081016008      	1	20081003	G	7830	65378786	SWITCH          			BOEING	727   	7272Q6      	138407V	NM  	PWA   	JT8   	JT8D17      	52049	NE  					THRUST REVERSER	INOPERATIVE     	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT, NR 3 ENGINE THRUST REVERSER OPERATING LIGHT ILLUMINATED THROUGH 5000 FT. THE ACFT RETURNED TO THE AI	RPORT. THE NR3 ENG THRUST REVERSER WAS DEACTIVATED AND MEL APPLIED. UPON REACHING THE DESTINATION, THE NR3 ENGINE THRUST	 REVERSER SWITCH WAS REPLACED, ENGINE RUN CARRIED OUT AND THE THRUST REVERSER WAS FUNCTIONALLY CHECKED AS SERVICEABLE. T	HE DEFERRAL WAS CLEARED AND THE ACFT WAS RETURNED TO SERVICE.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
	20081126		NM  	2008	11	26	CA081016009      	1	20081010	G	2797	19019566401	WIRE HARNESS    			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					LE SLAT	DEFECTIVE       	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) SLAT FAIL MESSAGE ON FLAP 5 SELECTION ON APPROACH. CREW CARRIED OUT A MISSED APPROACH, QRH WAS FOLLOWED AND LANDED	 UNEVENTFULLY ON SECOND TRY. SLAT HARNESS REPLACED, OPS TEST CARRIED OUT IAW AMM 27-80-00-710-801A, NO FAULTS NO EICAS M	ESSAGES.				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081126		CE  	2008	11	26	CA081016011      	1	20081010	G	2720	1295240823	TORQUE TUBE     	BEECH       	1295240821  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					RUDDER CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			17702								(CAN) RUDDER PEDALS LINKAGE (UNDER FLOOR) - LT TORQUE TUBE BROKEN JUST INBD OF THE LT RUDDER PEDAL BLOCK. RUDDER TORQUE 	TUBE FAILURE STARTED AT TAPER PIN HOLE USED TO SECURE THE RUDDER PEDAL ASSY BLOCK TO THE SHAFT. FAILURE APPEARS TO BE FR	OM AN OVERLOAD CONDITION WITH AN INITIAL CRACK AND THEN A SECONDARY CRACK AT ABOUT 90 DEGREES. A THIRD CRACK ALSO FOUND 	PARALLEL TO INITIAL CRACK. FAILURE OF THIS TYPE WOULD BE HARD TO PICK UP ON A VISUAL INSP AS EARLY FAILURE TAKES PLACE I	N AN AREA NOT VISIBLE UNTIL UNIT IS DISMANTLED. ONCE FAILURE PROGRESSED TO COMPROMISE THE TORSION ABILITY OF THE SHAFT I	T WOULD SPREAD RAPIDLY TO COMPLETE FAILURE.  COMPLETE RUDDER AND STEERING SYS WAS INSPECTED TO DETERMINE IF RELATED SYS 	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
	20081124		EA  	2008	11	24	CA081016012      	2	20080925	G	7230		COMPRESSOR      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	SEIZED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ACFT WAS EN ROUTE WHEN THE LT ENGINE LOST POWER.  THE CREW COMPLETED EMERGENCY PROCEDURES, SECURED THE ENGINE AND 	FEATHERED THE PROPELLER.  THEY DECLARED AN EMERGENCY AND CONTINUED TO DESTINATION, WHERE THE ACFT PERFORMED A SINGLE ENG	INE LANDING.  POST FLIGHT INSPECTION REVEALED A SEIZED COMPRESSOR AND OIL FILTER CONTAMINATION.  THE ENGINE WILL BE REMO	VED AND FORWARDED TO STANDARD AERO FOR INVESTIGATION AND REPAIR.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20081124		NE  	2008	11	24	CA081016014      	2	20081002	G	7321		FUEL CONTROL    			GULSTM	200   	200         	4500308	NM  	PWC   	PW306 	PW306A      	52165	NE  					ENGINE	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) 2 TO 3 MINUTES AFTER ENGINE START, IT FLAMED OUT UNCOMMANDED.  NO FAULT CODES WERE RECORDED ON THE FADEC.  INSPECT	ION FOUND THE FAN FREE TO ROTATE WITH NO EVIDENCE OF INGESTION.  THE PILOT MOTORED THE ENGINE AND THEN PERFORMED AN ENGI	NE START.  THE BOOST PUMP AND MOTIVE FLOW WERE OPERATING NORMALLY.  THE ACFT IS SCHEDULED TO BE FLOWN TO BASE FOR MX. P&	WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	L	7	2 	4F	4	F	RT	A53NM   	E35NE				 
	20081124		NE  	2008	11	24	CA081016015      	2	20081002	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FIRE            	W				E	F	B		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	EMER. DESCENT           		A	R	J	FLAME/FIRE                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE PILOT SAW FLAMES COMING OUT OF THE ENGINE EXHAUST BEFORE LOSING POWER.  HE DECLARED EMERGENCY A	ND DIVERTED THE FLIGHT TOWARDS A NEARBY AIRPORT.  HE WAS NOT ABLE TO MAKE THE AIRPORT AND HE WAS FORCED TO LAND ON A ROA	D.  THE PILOT WAS NOT INJURED AND THE ACFT SUFFERED NO DAMAGE.  THE ACFT WAS LATER TOWED TO THE AIRPORT WHERE FAA IS INV	ESTIGATING.  THE ENGINE WILL BE REMOVED AND FORWARDED TO STANDARD AERO FOR INVESTIGATION.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081106			2008	11	6	CA081017001      	4	20081012	G	8300	3022375	SEAL            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ACCESSORY G/B	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			7524 	7524 							(CAN) PILOTS SHUT DOWN NR 1 ENGINE, DUE TO OIL PRESSURE FLUCTUATION AND OIL PRESS. ANNUNCIATOR ILLUMINATION. ACFT RETURN	ED TO YXS MX BASE.  OIL LOSS WAS FOUND TO BE COMING FROM THE HP PUMP DRAIN. OIL SEAL REPLACED, OIL CONSUMPTION ELIMINATE	D. EXPLORATORY WORK COMPLETED AS PER PRATT AND WHITNEY MX MANUAL.  ACFT RELEASED AS PER PRATT AND WHITNEY MX MANUAL PUTT	ING IN PLACE BOTH OIL FILTER/SCREEN AND CHIP DETECTOR INSPECTIONS.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20081106		EA  	2008	11	6	CA081017002      	1	20081007	G	6120	8210004	CSU             			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				1525 							(CAN) THE ACFT WAS IN CRUISE FLIGHT WHEN THE TORQUE ON THE RT ENGINE SURGED AND THE PROPELLER BEGAN TO FEATHER. AS THE P	OWER WAS BROUGHT BACK THE PROPELLER STOPPED FEATHERING. A PRECAUTIONARY ENGINE SHUTDOWN WAS PERFORMED AND THE ACFT RETUR	NED TO BASE WITHOUT FURTHER INCIDENT. THE ENGINE AND ASSOCIATED SYSTEMS WERE TROUBLESHOT, WHICH DETERMINED THAT THE PROP	ELLER GOVERNOR WAS AT FAULT. THE GOVERNOR WAS CHANGED, A GROUND RUN AND A TEST FLIGHT WERE PERFORMED WITH NO FURTHER PRO	BLEMS.		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081106		NM  	2008	11	6	CA081017003      	1	20081007	G	5720	190933321001	FAIRLEAD        			EMB   	ERJ190	ERJ190100IGW	3260408	NM  											DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT WING AILERON FAIRLEAD BRACKETS. REMOVAL OF THE PLASTIC FAIRLEADS FOUND THAT THE CABLES DID NOT SIT ROUGHLY IN T	HE MIDDLE OF THE BRACKET HOLES. COMPARISON OF THE BRACKETS ON MSN 19000049 TO OTHER EMBRAER E190S IT WAS SUSPECTED THAT	 THE WRONG BRACKETS HAVE BEEN INSTALLED FROM FACTORY. PICTURES ATTACHED OF THE BRACKETS INSTALLED ON MSN 19000049 AS REF	ERENCE.  PER E190 SRM 57-50-00 FIGURE 45A THE CORRECT BRACKETS ARE 190-933321-001, 190-93298-001, 190-93298-001 AND 190-	93318-001 (FROM IB MOST TO OB MOST BRACKETS).		2	L	7	2 	4F			RT	A57NM   					 
	20081106		WP  	2008	11	6	CA081017004      	2	20081017	G	7230	31081822	BLADE           	NORMALAIR   							GARRTT	TPE331	TPE33110UA  	01514	WP  					IMPELLER	DAMAGED         	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			4210 	4210 							(CAN) IT WAS NOTICED ON A GROUND RUN AFTER THE ENGINE WAS INSTALLED THAT THERE WAS A SQUEALING NOISE COMING FROM THE ENG	INE. THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR EVALUATION. UPON DISASSEMBLY THE NR 1 IMPELLER WAS FOUN	D TO HAVE A PIECE OF THE BLADE MISSING. THE NR 1 IMPELLER HAS NO OTHER DAMAGE EXCEPT WHERE THE BLADE PIECE IS MISSING. T	HE NR 1 IMPELLER WILL BE FORWARDED TO A METALURGY FACILITY FOR EVALUATION TO DETERMINE WHY THE BLADE PIECE BROKE OFF. TH	ERE WAS SUBSTANTIAL DAMAGE TO THE ENGINE FROM THE IMPELLER BLADE PIECE.							4	T			E4WE				 
	20081106		EA  	2008	11	6	CA081017005      	1	20081017	G	2910	AE4760H0592055	LINE            			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF343A2     	30067	NE  					NR 2 EDP	BURST           	W				O				OTHER                   				K	S		FLUID LOSS                	AFFECT SYSTEMS            		CR	CRUISE         	1			CA											(CAN) AFTER TAKEOFF IN CRUISE AND ON THE WAY NR 2 HYD PRESS LOST MASTER CAUTION ON REPORT BY THE CAPTAIN, HE STILL HAD H	IS NR 1 AND NR 3 HYD SYSTEM. ACFT LANDED SAFELY WITHOUT ANY EMERGENCY REQUEST. NR 2 ENGINE HYD PUMP OUTLET LINE FOUND BU	STED, LINE REPLACED.  NR 2 HYD PUMP CHANGED AS MTCE PREVENTIVE AND NR 2 HYD FILTER CHECKED FOR FOD. NOTHING WAS FOUND.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081106		SW  	2008	11	6	CA081017006      	1	20080925	G	5302	214001920101	HORN            			BELL  	214   	214B1       	1182105	SW  	LYC   	T55   	T5508D      	41555	NE  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2034 								(CAN) BOTH `EARS` (LT & RT) OF THE HORN TO WHICH THE ELEVATORS ATTACH CRACKED. COMMON PROBLEM WITH THESE HELICOPTERS. SE	NT A PREVIOUSLY CRACKED HORN TO BELL HELICOPTER FOR ENGINEERING ANALYSIS, BUT HAVE NOT HEARD ANY RESULTS YET.					2	G	7	1 	4U	4	U		H6SW    	E4NE				 
	20081106		GL  	2008	11	6	CA081017007      	2	20081017	G	7323	23065123	GOVERNOR        			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1683 							(CAN) UPON REMOVAL OF THE GOVERNOR IT WAS NOTED THAT THE DRIVE GEAR HAD COME SEPARATED. ALL PARTS WERE FOUND IN THE DRIV	E GEAR FOR THE GOVERNOR. THERE WAS DIFFICULTY GETTING FULL RANGE OF THE GOVERNOR, COULD NOT ADJUST FOR 100 PERCENT ON TH	E GROUND. THE DRIVE GEAR USUALLY HAS A BONDING MATERIAL ON THE END OF THE WASHERS THAT WAS NO LONGER THERE. THE GOVERNOR	 WAS CHANGED AND FUNCTIONALLY CHECKED SERVICEABLE.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081106		SW  	2008	11	6	CA081017008      	1	20081003	G	5302	204032806079A	LONGERON        			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A VISUAL INSPECTION OF THE ACFT THE AME NOTICED A CRACK IN THE UPPER LT TAILBOOM LONGERON APROX. 3 INCHES A	FT OF THE TAILBOOM ATTACHMENT FITTING. ACFT GROUNDED FOR REPAIRS.					1	G	7	1 	4U	4	U		H1SW    	E1EA				 
	20081106		CE  	2008	11	6	CA081020001      	1	20081003	G	5551		MOUNT           			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RUDDER CONTROL	MISINSTALLED    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) METAL FILINGS WERE FOUND UNDER THE RUDDER SERVO DUE TO THE MOUNTING STRUCTURE HAVING BEEN INSTALLED OFFSET FROM TH	E FACTORY. THIS CAUSED THE RUDDER CABLE TO EXIT THE DRUM ON AN ANGLE AND RUB THE CAPSTAN. THE SERVO WAS REPLACED AND A P	ERMANENT FIX IS SCHEDULED FOR MAR. 09 AT CESSNA CITATION SERVICE CENTER.  PICTURES ARE AVAILABLE.				1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
	20081106		CE  	2008	11	6	CA081020002      	1	20081011	G	3213		TORQUE LINK     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6035 								(CAN) DURING REGULAR MX, A MECHANIC NOTICED A CRACK ON THE UPPER TORQUE LINK OF THE LT MLG. THE TORQUE LINK WAS REPLACED	 AND ACFT RETURNED TO SERVICE. THE RT MLG TORQUE LINKS WERE INSPECTED WITH NO FAULTS FOUND.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
	20081106		CE  	2008	11	6	CA081020003      	1	20081019	G	8011	MMU6001	STARTER         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) SNAG REPORTED THAT ACFT WOULD NOT START. UPON INVESTIGATING IT WAS NOTED THAT THE STARTER HOUSING WHERE IT ATTACHE	S TO ENGINE WAS BROKEN. ALSO NOTED THAT THE BENDIX DRIVE TEETH WERE MISSING/SHEARED OFF. ENGINE CASE INSPECTED FOR DAMAG	E, NONE FOUND NEW STARTER INSTALLED AND FUNCTION CHECKED SERVICEABLE. A CHECK ON STARTER SOLENOID SHOWED NO FAULTS.  SUS	PECT STARTER WAS RE-ENGAGED BY PILOT AFTER ENGINE WAS RUNNING.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
	20081222		EU  	2008	12	22	CA081020004      	1	20081002	G	6720	350A21136324	BRACKET         			SNIAS 	350   	AS350*      	       	EU  										TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A US OPERATOR HAS REPORTED 7 CASES OF THE RT TAIL ROTOR BELLCRANK MOUNTING BRACKET CRACKING.  ALL THESE ACFT HAVE 	LIMITED LT PILOT MODIFICATION STC SH96-32 (FAA STC SR00429NY).  LIMITED HAS ISSUED A SB ECL-122 REQUIRING AN INSP BEFORE	 NEXT FLIGHT REPEATED AT 50 HOURS THEN EVERY 100 HOURS.				1	G	7	1 	3U				H9EU    					 
	20081106		GL  	2008	11	6	CA081020005      	3	20081017	G	6114	HCD4N3C	SEAL            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				3135 							(CAN) DURING WALK AROUND, RT PROPELLER NOTED TO HAVE OIL DRIPPING FORM THE BLADE FACES. SOME OIL WAS NOTED TO BE ON THE 	UPPER ENGINE COWL, HOWEVER THE REST OF THE ENGINE WAS DRY. PROP SPINNER WAS REMOVED, INSIDE OF SPINNER WAS DRY AS WELL. 	GROUND RUN CARRIED OUT WITH SPINNER REMOVED, AND OIL WAS NOTED TO BE LEAKING FROM THE FRONT OF THE PROP CYLINDER, THE PR	OP HAD TO BE EXERCISED FROM REVERSE, FINE PITCH AND FEATHER TO GET IT TO SHOW ANY LEAKAGE, THE LEAK WAS COMING FROM THE 	PITCH CHANGE ROD AND REVERSE ADJUST LEVER, THE MAJORITY OF THE OIL LEAKAGE ENDED UP ON THE BLADES ONLY, THE CYLINDER DID	 NOT SHOW VERY MUCH OIL LEAKAGE AT ALL, THE OIL SEEMED TO JUST SLING OUT ONTO THE BLADES AND A LITTLE BIT ON THE UPPER C	1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
	20081106		SW  	2008	11	6	CA081020006      	1	20081019	G	3230	KRP5064	BEARING         			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) UPON TAKEOFF THE CREW REPORTED THAT THE RT GEAR WOULD NOT REMAIN LOCKED. ACFT RETURNED TO BASE AND UPON MX INSPECT	ION IT WAS FOUND THAT THE UP-LOCK HOOK BEARING AND ATTACHING HARDWARE WERE MISSING. IT WAS ALSO NOTED THAT THE UP-LOCK H	OOK SHAFT ATTACH POINTS HAD BEEN MARRED. THIS LEADS US TO BELIEVE THAT THE BEARING WAS INSTALLED AND EITHER THE BEARING 	OR BOLT FAILED. FAILED PARTS WERE REPLACED - GEAR SWINGS CARRIED OUT AND ACFT RETURNED SERVICE.			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081106			2008	11	6	CA081020007      	4	20081019	G	2330	3042865102	ELECTRICAL BOX  			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					SEAT ROW 16ABC	ODOR            	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FLIGHT ATTENDANTS NOTICED ELECTRICAL ODOR AT ROW 16 AND SHORTLY AFTER THE ROW 16ABC MALFUNCTIONED. LIVETV SYSTEM S	HUT OFF IN FLIGHT DECK AND FLIGHT ATTENDANT STATION. THE SEB P/N 3042865-102 S/N 1792 WAS REMOVED. THIS SDR WILL BE UPDA	TED WHEN SEB TEARDOWN INFORMATION IS AVAILABLE.				2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
	20081219		SW  	2008	12	19	CA081020008      	1	20081009	G	5610	2621126005	WINDSHIELD      			SWRNGN	SA226 	SA226T      	8780122	SW  	GARRTT	TPE331	TPE3311     	01514	WP  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA				177  							(CAN) DURING CRUISE FLIGHT THE LT COCKPIT WINDSHIELD GLASS CRACKED WITH AN EXPLOSIVE BANG.  THE CREW IMMEDIATELY DESCEND	ED AND REDUCED CABIN PRESSURE TO AVOID THE POSSIBILITY OF THE WINDOW GLASS BLOWING OUT.  THE WINDOW WAS INSTALLED ON APR	IL 11, 2006 AND HAD A TOTAL OF 177 HOURS SINCE OVERHAUL AND INSTALLATION.  THE ACFT WAS IN THE USA AT THE TIME OF THE OC	CURRENCE AND THE ACFT WAS FLOWN TO ITS INTENDED DESTINATION AS IT WAS ONLY ABOUT 30 MINUTES FROM THE DESTINATION AT THE 	TIME OF OCCURRENCE.  THE WINDOW WAS REPLACED BY APPROPRIATELY RATED FAA REPAIR STATION.  THE WINDOW WILL BE SENT TO THE 	MANUFACTURER FOR WARRANTY AND EXAMINATION.	2	L	7	2 	4T	3	T	RT	A5SW    	E3WE				 
	20081229		SW  	2008	12	29	CA081020009      	1	20081007	G	3244	196K089	TIRE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33110U   	29066	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	SEPARATED       	W				O				OTHER                   				C			F.O.D.                    			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING GROUND HANDLING PROCEDURES THE NR2 MAIN WHEEL WAS FOUND TO BE SHREDDED AND THE TREAD PORTION OF THE TIRE MI	SSING. THIS TIRE WAS A RECAPPED TIRE RECEIVED FROM A CERTIFIED FAA REPAIR STATION.  THE TIRE WHEN IT SHREDDED CAUSED DAM	AGE TO THE ACFT FLAP AND SURROUNDING WW WHICH REQUIRED REPLACEMENT OF THE FLAP AND REPAIR OF THE WW AREA.  MAINT REPAIRE	D THE ACFT AND REPLACED THE TIRE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081106		SO  	2008	11	6	CA081020010      	1	20081015	G	7930		FITTING         			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	OIL PRESS LINE	FAILED          	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			59   								(CAN) DURING TAXIING OF THE ACFT, THE CREW NOTED THE ANNUNCIATOR FOR OIL PRESSURE ON THE LT ENGINE CAME ON. THEY SHUTDOW	N THE LT ENGINE AND TAXIED THE ACFT USING 1 ENGINE BACK TO THE HANGER. AFTER INSPECTION, IT WAS FOUND THAT THE HOSE ASSE	MBLY FROM THE ENGINE OIL COOLER TO THE ENGINE HAD FAILED AND WAS LEAKING ENGINE OIL FROM WHERE THE HOSE IS SECURED INTO 	THE FITTING ASSEMBLY ON THE HOSE ASSEMBLY. THE HOSE ASSEMBLY WAS REPLACED WITH A NEW HOSE ASSEMBLY. THE ENGINE CHIP DETE	CTOR AND ENGINE FILTER WAS INSPECTED WITH NO FAULTS FOUND. THE WAS SERVICED WITH OIL AND SATISFACTORY OPS AND LEAK CHECK	S WHERE CARRIED OUT WITH NO FAULTS FOUND. THE HOSE ASSEMBLY WAS REPLACED PRIOR BECAUSE THE HOSE ASSEMBLY TIME LIMIT WAS 	1	L	7	2 	3T	4	T	RT	A8EA    	E4EA	6	C	P15EA	 
	20081107		WP  	2008	11	7	CA081020011      	1	20081016	G	7714		TACHOMETER      			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) DURING DESCENT FROM ALTITUDE TO BEGIN LOW LEVEL FLIGHT FOR PIPE LINE SURVEILLANCE AT APPROX. 75 KNOTS INDICATED AI	RSPEED AND VSI AT APPROX. 500 FPM, THE ENGINE RPM TACH INDICATED ENGINE OVERSPEED WELL ABOVE 110%. ALL OTHER ENGINE PARA	METERS REGISTERED WITHIN LIMITS, INCLUDING THE ROTOR RPM TACH. NO WARNING OR CAUTION LIGHTS.  THE THROTTLE WAS LOWERED T	O MAINTAIN NR RPM WHEN LOW ROTOR RPM HORN SOUNDED.  A POWER ON LANDING PERFORMED WHILE ATTEMPTING TO MAINTAIN ENGINE TAC	H INDICATING WITHIN LIMITS. LOW ROTOR HORN SOUNDED REPEATEDLY DURING DESCENT WHILE ENGINE TACH INDICATED OVER 102%.  20 	MINUTES INTO THE FLIGHT, THE PILOT NOTICED A CHANGE IN ENGINE NOISE TO A HIGHER FREQUENCY, BUT NO ABNORMALITIES FOUND ON	1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081107		NE  	2008	11	7	CA081020012      	2	20081019	G	8530		VALVE           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	STUCK           	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) DURING STRAIGHT AND LEVEL CRUISE FLIGHT, THE PILOT NOTICED A SUDDEN INCREASE IN VIBRATION, THOUGHT TO BE COMING FR	OM THE ENGINE, AND AN INCREASE IN MANIFOLD PRESSURE. HE OPTED TO TURN AROUND AND LAND AT A NEARBY CAMP. DURING HIS DESCE	NT, THE VIBRATION STOPPED AND ENGINE PERFORMANCE RETURNED TO NORMAL. A COMPRESSION CHECK WAS FOUND NORMAL ON ALL CYLINDE	RS. A WIGGLE CHECK ON THE EXHAUST VALVES WAS FOUND SATISFACTORY, HOWEVER, 1 OF THE VALVES WAS AT 0.014 WHILE ALL THE OTH	ERS WERE AT 0.020 OR BETTER. IT IS SUSPECTED THAT THIS EXHAUST VALVE BECAME STUCK AND THEN CAME FREE AGAIN.		1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081107		CE  	2008	11	7	CA081021001      	1	20081001	G	3220	NAS150A48	BOLT            	BEECH       		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	NLG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOLT WAS FOUND LOOSE ON RT SIDE OF NLG. THE COTTER PIN AND NUT WERE MISSING.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
	20081107		NM  	2008	11	7	CA081021002      	1	20081018	G	3260	401020101	SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4571 								(CAN) ON INSPECTION FOUND NOSE GEAR DOOR CLOSED SENSOR CRACKED. SENSOR REPLACED IAW AMM 32-61-06-04						2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081107			2008	11	7	CA081021003      	4	20081019	G	3120	49712631	PRINTER         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					ACARS	SMOKE           	W				G				O2 MASK DEPLOYED        				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA			5044 	5044 							(CAN) DURING DESCENT TO YOW, CREW NOTICED SMOKE COMING FROM THE ACARS PRINTER, ELECTRICAL CIRCUIT BREAKER POPPED AND SMO	KE STOPPED. NO EMERGENCY DECLARED AND THE ACFT LANDED WITHOUT FURTHER INCIDENT. ACARS PRINTER DIFFERED IAW MEL 23-22-0 A	ND CIRCUIT BREAKER SECURED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081107		NM  	2008	11	7	CA081021004      	1	20081019	G	3260		SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG DOOR	OUT OF RIG      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) NOSE GEAR DOOR LIGHT FLICKERING ON AND OFF IN FLIGHT.  RIGGED NOSE GEAR DOOR PROXIMITY SENSOR IAW AMM 32-61-06. CY	CLED NOSE GEAR DOORS AND NO OTHER FAULTS FOUND.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081107		GL  	2008	11	7	CA081021005      	2	20081020	G	7323	23065121	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				1329 							(CAN) PILOT REPORTED ROTOR SPEED HUNTING IN CRUISE SO THE GOVERNOR WAS REMOVED TO CLEAN THE ORIFICES. ONCE REMOVED IT WA	S NOTICED THAT THE EPOXY BOND ON THE END OF THE DRIVESHAFT WAS MISSING AND THE SPLINE DRIVE WAS LOOSE ON THE GOVERNOR DR	IVESHAFT. IF LEFT THIS WOULD LIKELY TURN INTO WHAT WAS REPORTED IN SDR 20071015004 AND COULD LEAD TO AN ENGINE DECEL OR 	SHUT DOWN.			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
	20081107		EU  	2008	11	7	CA081021006      	1	20081020	G	2730	258CT29115A	JACKSCREW       	HAWKER      		BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					TRIM ACTUATOR	FROZEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8137 								(CAN) CREW REPORT THE ELEVATOR TRIM WAS DIFFICULT TO MOVE IN FLIGHT. UPON INSPECTION BY MX IT WAS FOUND THE ACTUATOR WAS	 CORRODED INTERNALLY AND THE GREASE WAS CONTAMINATED AND HARDENED. HAWKER BEECHCRAFT ALREADY HAS SB 27-3840 R1 TO CHECK 	FOR THIS SAME ISSUE WITH THESE ACTUATORS. BOTH LT AND RT ACTUATORS WERE REPLACED DUE TO THIS ISSUE AND THE ACFT RETURNED	 TO SERVICE.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
	20081107		NM  	2008	11	7	CA081021007      	1	20081017	G	7921	28E997	OIL COOLER      			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  					NR 1 ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NR 1 ENGINE OIL PRESSURE BELOW 40 PSI. NR 1 ENGINE SHUT DOWN IN FLIGHT. AFTER THE ACFT RETURNED TO BASE IT WAS FOU	ND AN OIL LEAK FROM THE NR 1 ENGINE OIL COOLER.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20081107		CE  	2008	11	7	CA081022001      	1	20081021	G	5343	AN35A	BOLT            	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG TRUNNION	WRONG PART      	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) CARRY OUT INSPECTION AS PER CAMPAIGN 851-53-11-047 CESSNA 550 CHANNEL-TRUNION BRACE.  FOUND INCORRECT HARDWARE INS	TALLED.  NO VISUAL DAMAGE TO STEERING ARM.  REPLACED HARDWARE AS PER CAMPAIGN.  NO RESTRICTED TRAVEL FOUND.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20081107		NM  	2008	11	7	CA081022002      	1	20081014	G	3240	14209114	CONTROL MODULE  			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					RT BRAKES	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			3089 								(CAN) AFTER LANDING, DURING DECELERATION ON RUNWAY AT APPROX 80 KTS, LT AND RT BRAKE FAULT MSG APPEARED ON EICAS ACCOMPA	NIED BY COMPLETE LOSS OF BRAKING. AFTER APPROX 8 SECONDS BRAKING RETURNED TO NORMAL AND EICAS MSG DISAPPEARED. SERVICE N	EWS LETTER SNL190-32-0023R00 IS RELATED NO MX MSG CORRELATION WITH LT AND RT BRAKE MSG. IN CMC MX MSG HISTORY OF OCT 14 	LEG 3 FOUND MSG: "MAU2 BCM2/MAU2 NWSCM" CODE 32533301NWS. PER FIM 32-53-00-810-813-A00, BCM2 WAS REPLACED PER MM			2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081230		CE  	2008	12	30	CA081022003      	1	20081020	G	5240	H1721050100	LATCH           			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE73123B   	 	WP  					SERVICE DOOR	UNSERVICEABLE   	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) SINGLE POINT FUEL DOOR LATCH OPENED IN FLIGHT.						2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
	20081107		EU  	2008	11	7	CA081022004      	1	20081015	G	2421	200322	GENERATOR       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	NR 1	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE NR 1 A/C WILD GENERATOR WENT OFF LINE. MX INSPECTED AND FOUND NR 1 AC WILD GENERATOR HAD FAILED 	INTERNALLY WITH SMALL SCREWS, WASHERS, ETC LAYING ON OUTLET COOLING SCREEN. TSO UNKNOWN.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20081107		NM  	2008	11	7	CA081022005      	1	20081021	G	3260	401020101	PROXIMITY SENSOR			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					RT MLG	OUT OF RIG      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) RT MLG FAILED TO RETRACT NORMAL, AMBER DOOR LIGHT, HANDLE LIGHT AND RED DISAGREEMENT LIGHT ILLUMINATED.  RT MLG PR	OXIMITY SENSOR FOR UPLOCK INDICATION RIGGED AS PER AMM 32-61-06-400-802. GAP SET TO .045, MH 8.621					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081107		WP  	2008	11	7	CA081022006      	2	20081019	G	7261		CARBON SEAL     			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE3315     	01514	WP  					NR 1 ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) NR 1 ENGINE CREW SHUT DOWN DUE TO STEADY DROP OF OIL PRESSURE AND TORQUE FLUCTUATION, BELIEVED LATER THAT THE REAR	 CARBON SEAL BEGAN TO LEAK THUS INGESTION OIL IN ENGINE AND BURNT. ENGINE REMOVED FROM ACFT TO BE SENT FOR FURTHER TESTI	NG AT ENGINE SHOP.				2	H	7	2 	4T	4	T	RT	A16EU   	E4WE				 
	20081230		GL  	2008	12	30	CA081022008      	1	20081021	G	2710	AN2412	CLEVIS BOLT     			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	CONTROL CABLE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN AILERON CABLE (IN WING) REPLACEMENT THE CLEVIS BOLTS WERE FOUND TO BE WORN MORE THAT 30 PERCENT, REPLACE	D WITH NEW AN 24-12 CLEVIS BOLTS.					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P736	 
	20081107		NE  	2008	11	7	CA081022009      	2	20081007	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						DAMAGED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE PILOT HEARD AN UNUSUAL NOISE FROM THE ENGINE FOLLOWED BY A DECREASE IN COMPRESSOR TURBINE SPEED.	 THE PILOT RETURNED TO HIS POINT OF DEPARTURE WHERE AN UNEVENTFUL LANDING WAS MADE. THE ENGINE WAS NOT SHUT DOWN AND THE	 EMERGENCY POWER LEVER WAS NOT USED. THE ENGINE HAS BEEN SENT TO REPAIR STATION FOR INVESTIGATION, MANUFACTURER WILL CON	TINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081230		CE  	2008	12	30	CA081022010      	1	20081002	G	2752	503801537	DRIVE ASSY      	BEECH       		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	FLAP ACTUATOR	SHEARED         	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE FLAPS WERE SELECTED TO 17 DEG BUT FAILED TO EXTEND PAST 10 DEG. THE FLIGHT CREW INITIATED AN OVERS	HOOT TO TROUBLESHOOT THE PROBLEM, THEY WERE UNABLE TO FIX THE BROKEN FLAPS AND RETURNED TO BASE. MX REPLACED THE FLAP DR	IVE AND NO FURTHER FAULTS WITH SYS FOUND.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
	20081230		NM  	2008	12	30	CA081023001      	1	20081023	G	2710		BEARING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CABLE PULLEY	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING FLAP INSP, AN ENGINEER FOUND AN AILERON PULLEY INSIDE THE WING BOX SEIZED.  FURTHER INVESTIGATION REVEALED 	THE ADJACENT PULLEY WAS ALSO CORRODED.  BOTH PULLEYS WERE REPLACED AND THE ACFT RETURNED TO SERVICE. 1915 HRS WERE REMAI	NING BEFORE COMPLETION OF TASK 2710/02 (11000 HRS).				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		NM  	2008	12	30	CA081023002      	1	20081013	G	2910	19071270901	RESTRICTOR VALVE			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					HYDRAULIC SYS	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) HYD LEAK 10 DPM ON SYS NR2 RETURN LINE AND UNION FREE FALL SELECTOR VALVE RT WW AREA. WRENCH CHECK NIL FIX. FOUND 	RESTRICTOR VALVE CRACKED ON EMERGENCY EXTENSION SELECTOR VALVE. RESTRICTOR VALVE REPLACED, BUT STILL HAD A LEAK. UPON CL	OSE INSP, FOUND A VERTICAL CRACK IN THE THREADED PORTION OF THE VALVE UNDER THE B-NUT (BOTH RESTRICTOR VALVES). THESE FI	NDINGS RAISED THE CONCERNS OF ATTACHING A STAINLESS STEEL LINE AND B-NUT TO THE LIGHTER ALUMINUM RESTRICTOR VALVE. A 1.1	250 IN WRENCH IS REQUIRED TO TIGHTEN THE "B" NUT. NOTE, WE ALSO REPLACED THE HYD LINE ASSY.		2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081107		NM  	2008	11	7	CA081023003      	1	20081019	G	2797	19019564401	WIRE HARNESS    			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					SLAT SYSTEM	DAMAGED         	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON FLAP RETRACTION AFTER T/O. SLAT FAIL EICAS MSG DISPLAYED. CARRIED OUT QRH FOR SLAT FAIL. DID NOT RECTIFY PROBLE	M. ACFT RETURNED RT SLAT SKEW SENSOR HARNESS W611 REPLACED AS PER AMM 27-83-07 PB 401, RT SLAT 2/3 SKEW SENSOR  REPLACED	 AS PER AMM 27-83-01 PB- 401.				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081230		NE  	2008	12	30	CA081023004      	1	20081016	G	7922	28E251	THERMOSTAT      			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR 2  OIL COOLER	UNSERVICEABLE   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP 8 EXCEEDED RED LINE LIMIT.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
	20081222		SW  	2008	12	22	CA081023005      	1	20080727	G	5302	205032807003	FITTING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CONDUCTING 100 HR INSP NOTED AREA IN LT LOWER TAIL BOOM LONGERON AT FWD FITTING TO BE CRACKED. NDT CONFIRMED	 A CRACK INDCATION OF 1.5 INCHES LONG IN THE FITTING.					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
	20081222		SO  	2008	12	22	CA081024001      	1	20081024	G	5343	6705403	TRUNNION        			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  	HARTZL	HCC3Y	HCC3YR      	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4771 								(CAN) FOUND GREASE LEAKING FROM TOP PORTION OF THE LWR BRG SUPPORT. CLEANED AREA AND RE GREASED TRUNNION. GREASE WAS FOU	ND COMING OUT OF CRACK. THE CRACK IS APPROXIMATELY ONE INCH LONG, HORIZONTAL. THIS CRACK INDICATION DOES APPEAR TO BE CA	USED BY IMPROPER GROUND HANDLING. STEPS ARE BEING TAKEN TO REPLACE PART AT THIS TIME.				1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P25EA	 
	20081230		NE  	2008	12	30	CA081024002      	1	20081021	G	2910	9265004900101	HEAT EXCHANGER  			SKRSKY	S92   	S92A        	       	NE  	GE    	CT7TS 	CT78A       	30136	NE  					HYD SYSTEM	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) ENROUTE AT 7000 FT, ACFT STARTED TO NOD UNCHARACTERISTICALLY. IT WAS NOTED THAT THE NR 1 HYD SYS PRESSURE WAS HIGH	 (IN THE RED). DECISION TO RETURN MADE AND NR 1 HYD SYS DE-SELECTED BUT PRESSURE REMAINED HIGH. NO OTHER ADVISORY/CAUTIO	N LIGHTS WERE ON AT THIS POINT. ABOUT 10 MINUTES AWAY FROM DESTINATION, PRESSURE DROPPED AND "HYD NR 1 RESEV LOW" LIGHT 	CAME ON FOLLOWED BY M/R AND T/R SERVO NR 1 PRESS, HYD NR 1 PUMP FAIL, PSAS PRESS AND AUTO-PILOT FAIL LIGHTS. EMERGENCY C	HECKLIST CONSULTED AND CARRIED OUT.  ACFT LANDED AND SHUTDOWN WITH NO FURTHER INCIDENT.  PAX WERE BRIEFED IN-FLT AND AT 	SHUTDOWN. THE HYD NR 1 SIDE OF THE RT HEAT EXCHANGER FOUND TO HAVE CRACK AT BOTTOM OF HSG. NR 1 HYD SYS DRAINED OUT ALL 	2	G	7	2 	4U	4	U		R00024BO	E8NE				 
	20081107		WP  	2008	11	7	CA081024003      	1	20081015	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			413  								(CAN) STARTER GEN WOULD NOT ENGAGE ENGINE, REPLACED WITH SERVICEABLE STARTER GEN.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081107		WP  	2008	11	7	CA081024004      	1	20081011	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					PILOT VALVE	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			1690 								(CAN) SERVO LEAKING FROM PILOT VALVE						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081107		WP  	2008	11	7	CA081024005      	1	20081011	G	6730	D2121	SERVO           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					PILOT VALVE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) SERVO LEAKING FROM PILOT VALVE						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081230			2008	12	30	CA081024006      	4	20081010	G	2216		GROUND WIRE     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					TRIM SYS	OPEN            	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) ON LANDING, A WHITE CAS MESSAGE (SECONDARY TRIM FAULT) APPEARED. SYS TROUBLESHOT AND FOUND AN OPEN GROUND WIRE AT 	RBA0664N-22 AT SPLICESP322. SPLICE REPAIRED AND FUNCTION CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
	20081107		NE  	2008	11	7	CA081025001      	2	20081024	G	7530	BRH10211MS3215	PIN             			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					LINKAGE	MISSING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			10795								(CAN) ON 26 SEPT, ENGINE RECORDED 73-2138, BBV/FMU MECHANICAL FAULT. BVV AND FMU WAS CHANGED. ENGINE GOOD FOR 2 FLIGHTS 	BEFORE ENG SYS FAIL CAME BACK INFLIGHT FOR THE SAME FAULT. ACFT DIVERTED, OPERATOR REPORTS PROBLEMS WITH THE BVV LINKAGE	 THAT CANNOT BE CORRECTED ONWING. ENGINE WAS REMOVED IN UNSERVICEABLE CONDITION DUE TO BOOSTER BLEED VALVE MECHANISM MAL	FUNCTION. IT HAS BEEN REPORTED BY OPERATOR THAT BVV LEVER WAS NOT OPERATING PROPERLY. ENGINE AT ROLLS ROYCE CANADA FOR R	EPAIR TO DETERMINE THE ROOT CAUSE OF MECHANISM MALFUNCTION. STRIP WAS CARRIED OUT TO EXPOSE THE BOOSTER BLEED VALVE MECH	ANISM AND IT WAS NOTED THAT PIN AND RETAINING RING WERE MISSING.  THIS PIN IS THE JUNCTION BETWEEN THE BELL CRANK LEVER 	2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
	20081107		NE  	2008	11	7	CA081025002      	2	20081010	G	7320	251818	BRACKET         			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA				22738							(CAN) ENGINE AUTO IFSD, ACFT DIVERTED TO ATL UNEVENTFUL LANDING. FSO CABLE RELEASE, PIECES FOUND IN THE TAILPIPE. LPT3 S	CUFFED AND NICKED CONSISTENT WITH CABLE DAMAGE. NO EVIDENCE OF A TURBINE FAILURE. LP SYSTEM FREE TO TURN SMOOTHLY. ENGIN	E IN RRC FOR INVESTIGATION. FURTHER DETAIL WILL BE SUBMITTED.				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
	20081107		CE  	2008	11	7	CA081027001      	1	20081023	G	6120	8930861	SHAFT           			MTSBSI	MU2   	MU2B36      	5780412	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	BINDING         	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			25508	5965 							(CAN) PROP OVERSEED DURING DESCENT. FOUND ENGINE INNER CONCENTRIC SHAFT TO BE BINDING ON OUTER CONCENTRIC SHAFT. AS POWE	R LEVER IS RETARDED, INNER CONCENTRIC SHAFT ROTATES SLIGHTLY CLOCKWISE INCREASING PROP GOVERNOR HIGH SETTING. THERE IS N	O PROVISION FOR LUBRICATION IN THIS AREA AND IT ONLY RELIES ON SPRING FORCE TO RETURN THE PROP GOVERNOR TO A LOWER SETTI	NG. INNER SHAFT REMOVED, CLEANED, LUBRICATED AND REINSTALLED			1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P15EA	 
	20081230		EA  	2008	12	30	CA081027002      	1	20080910	G	2435	23048016	STARTER GEN     			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  		WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				612  							(CAN) STARTER GEN HAD LONG LIFE BRUSHES INSTALLED AT OVERHAUL. BRUSHES ONLY LASTED 611.5 HRS WHEN THEY SHOULD HAVE WENT 	THEIR 1200 HOURS. ONE BRUSH WAS RT AT THE LIMIT WHERE THE OTHER BRUSH WAS ABOUT 40 PERCENT WORN ONLY.					1	H	7	1 	3R	4	T		A815    	E4EA	6	C	P15EA	 
	20081230		EA  	2008	12	30	CA081027003      	2	20081025	G	7321		SHAFT           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FCU THROTTLE	STIFF           	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			2888 								(CAN) UPON APPROACH, THE LT ENG PWR LEVER WAS RETARDED WITH NO EFFECT ON ENG. THE ENG REMAINED AT 91 PERCENT NG. THE APP	ROACH WAS ABORTED AND THE ACFT DIVERTED. ON ARRIVAL, AN EMERGENCY WAS DECLARED AND THE LT WAS SHUTDOWN IN ORDER TO CARRY	 OUT THE LANDING. MX INVESTIGATION DETERMINED THE INPUT SHAFT ON THE FCU WAS VERY STIFF, THE FCU WAS REPLACED AND THE AC	FT RETURNED TO SERVICE.			1	L	7	2 	3T	4	T		A14CE   	E4EA	5	C	STC	 
	20081222		EA  	2008	12	22	CA081027004      	1	20081024	G	5280	491184	BRACKET         			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C5     	30050	NE  					RT MLG DOOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INBD MLG RT DOOR ATTACHMENT BRACKET ON STRUT FOUND LOOSE DURING HEAVY MAINT VISIT.  REFERENCE: CMM 32-11-05, FIGUR	E 1, PAGE 1019, ITEM 290.  IT IS WORTH NOTING THAT THIS IS THE 2ND TIME, IN THE MONTH OF OCTOBER 2008, THAT THIS ISSUE H	AS BEEN RAISED. PREVIOUSLY, A MAINT IRREGULARITY REPORT SUBMITTAL, DATED 03 OCTOBER 2008, REVEALED THAT THE SAME PROBLEM	 WAS FOUND. NO SDR RAISED FOR THIS ONE.			2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081229		CE  	2008	12	29	CA081027005      	1	20081022	G	3233	ADI79990038	FORK            		ADI7999003  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ACTUATOR	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THE PILOT SELECTED GEAR UP, RT MLG FAILED TO RETRACT.  GEAR WAS CYCLED WITH NO SUCCESS.  GEAR WAS RE	TURNED TO DOWN POSITION AND THERE WERE 3 GREEN LIGHTS. DISPATCH AND MX WERE CONTACTED AND IT WAS DECIDED TO RETURN TO BA	SE.  LANDING WAS UNEVENTFUL. UPON INSP BY MX, THE RT MLG ACTUATOR FORK END THAT ATTACHES TO THE UPPER DRAG BRACE WAS SHE	ARED OFF, HOWEVER THE DOWNLOCK WAS STILL IN PLACE. IT LOOKED LIKE THE FORK END HAD DEVELOPED A FATIGUE CRACK AND FINALLY	 LET GO JUST ABOVE THE LOCK NUT THAT HOLDS THE FORK END IN PLACE ON THE ACTUATOR. THE FORK END, AND TAB WASHER WERE REPL	ACED WITH NEW PARTS. CYCLES OR HRS ON BROKEN FORK END IS UNKNOWN. THE GEAR WAS INSPECTED FURTHER AND NO OTHER DEFECTS FO	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
	20081230		EU  	2008	12	30	CA081027006      	1	20081023	G	2130		BUTTERFLY VALVE 			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	CABIN PRESSURE	STICKING        	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) FOLLOWING DEPARTURE, THE ACFT FAILED TO PRESSURIZE IN AUTO OR MANUAL MODE. THE ACFT RETURNED TO POINT OF DEPARTURE	 AND LANDED WITHOUT FURTHER PROBLEM.  THE GROUND AIR CONNECTION CHECK VALVE WAS FOUND TO BE STUCK IN THE OPEN POSITION. 	 MAINT CLEANED AND LUBRICATED THE VALVE TO RESTORE PROPER FUNCTION.  THE SYS WAS GROUND CHECKED SERVICEABLE AND THE ACFT	 RETURNED TO SERVICE WITH NO FURTHER PROBLEM REPORTED.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20081230		CE  	2008	12	30	CA081028001      	1	20081001	G	2497	70002405D	CIRCUIT BREAKER 			CESSNA	680   	680CE       	2076811	CE  	PWC   	PW306 	PW306C      	52169	NE  					LT POWER FEED	TRIPPED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			81   								(CAN) LT POWER FEED CIRCUIT BREAKER (1 OF 3 IN PARALLEL) POPS OPEN IN FLIGHT. P/N 700-024-50 REPLACED NEW.  NOTE: THIS C	/B WAS REPLACED AT 261 HRS. AND AGAIN AT 342 HRS.					2	L	7	2 	4F	4	F	RC	T00012WI	E35NE				 
	20081222		SW  	2008	12	22	CA081028003      	1	20081024	G	6320	407040035101	BEVEL GEAR      	BELL        		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TRANSMISSION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6089 	1122 							(CAN) TRANSMISSION CHIP LIGHT ILLUMINATED. MECHANIC FOUND SMALL DEBRIS ON THE LWR CHIP PLUG. UPON INSP BY THE OVERAUL SH	OP, THEY DISCOVERED THE BEVEL GEAR DAMAGED. A SMALL PIECE OF GEAR TOOTH APPROX. .360X.073 HAD BROKEN OFF THE GEAR ASSY A	ND DISCOVERED THE BEVEL GEAR CRACKED AT THE DAMAGED GEAR TOOTH ARED.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
	20081230		GL  	2008	12	30	CA081028004      	1	20081021	G	2720	2227271200	TUBE            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	RUDDER CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1742 								(CAN) DURING ROUTINE INSP/OPS CHAEK IT WAS FOUND THAT THE S-TUBE WHICH ALLOWS FOR THE POSITIONING OF THE RUDDER PEDAL ON	 THE PILOTS RT SIDE, HAD WORN THE CABLE TO THE POINT OF FINDING A FEW BROKEN CABLE STRANDS. THE RUDDER CABLES WERE ONLY 	DUE FOR REPLACEMENT AT 3000 HRS.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081230		WP  	2008	12	30	CA081028005      	1	20081022	G	2435	14924HTH	STARTER GEN     			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	DISENGAGED      	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			201  								(CAN) STARTER WOULD NOT ENGAGE THE RING GEAR.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20090102		WP  	2009	1	2	CA081028006      	1	20081024	G	6310	C0183	BAR             			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					SPRAG CLUTCH	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			930  								(CAN) DURING AN AES MIDLIFE INSP FOUND: SPRAG CAGE CRACKED (2) CROSSBARS SHAFT WORN UNDERSIZE HOUSING WORN OVERSIZE.						1	G	7	1 	3O	3	O		H11NM   	E295				 
	20090102		GL  	2009	1	2	CA081028007      	1	20081020	G	5320	C2CE329A	BRACKET         			DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	FIREWALL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSP, AN AME FOUND A CRACK IN RADIUS OF MIXTURE CONTROL BRACKET ATTACHED TO FIREWALL, BRACKET WA	S REMOVED, REPAIRED AND REINSTALLED.					1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P736	 
	20090102		EA  	2009	1	2	CA081029001      	1	20081027	G	2820		TUBE            			CNDAIR	CL604 	CL604       	1900301	EA  										FUEL SYS	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE TROUBLESHOOTING A FUEL TRANSFER PROBLEM ON THE CHALLENGER 604, SERIAL NR 5320,  WE FOUND 3 DAMAGED FUEL TUBE	S IN THE CENTER FUEL TANKS, 2 IN THE RT SIDE AND 1 IN THE LT SIDE. ALL 3 FUEL TUBES WERE REPLACED.					2	L	7	2 	4F			RT	A21EA   					 
	20090102		SO  	2009	1	2	CA081029002      	1	20081027	G	7721	1020007	PROBE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CYLINDER HEAD	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) PILOT OBSERVED LT ENG CYLINDER HEAD TEMP OVER RED-LINE. OTHER ENG PERIMETERS WERE NORMAL. PILOT CHOSE TO SHUTDOWN 	THE ENG AND FEATHER THE PROPELLER. LANDED WITHOUT INCIDENT. MAINT TROUBLESHOT AND FOUND LT ENGINE CHT READ 150 DEGREES W	HEN ENGINE WAS COLD. CHANGED THE PROBE TO P/N AN5546-1 IAW IPC. THE PROBE REMOVED IS AN FAA/PMA ALTERNATE TO THE REQUIRE	D P/N IN THE IPC.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20090102		NM  	2009	1	2	CA081029003      	1	20081024	G	6120	30005000024	SIGNAL COND UNIT			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	PROPELLER	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			35236	35236							(CAN) JUST AFTER TAKEOFF, NR 2 ENGINE WENT TO FEATHER. AUTO FEATHER WAS ARMED/CREW HAD NOT COMMANDED AN ENG FEATHER. CRE	W COMPLETED SHUT DOWN OF NR2 ENG, DECLARED AN EMERGENCY AND RETURNED TO ORIGINATING AIRPORT. NO OTHER INCIDENTS DURING L	ANDING. MAINT INTERROGATION OF FDR RECORD SHOWS ELECTRONIC FEATHER SIGNAL WAS GENERATED BY THE TSCU AND SYSTEMS RESPONDE	D TO THIS SIGNAL AND COMMENCED FEATHERING OF THE NR 2 ENGINE. ENG MFG EXAMINATION OF FDR DATA SHOWS ENGINE AND PROP OVER	 TORQUE DURING ENGINE FEATHER. DILASTIC TEST OF ENG HARNESS AND TSCU SHOWED NO CONFIRMED FAULTS. ENG HARNESS AND TSCU (T	SCU SUSPECTED) REPLACED FOR TROUBLESHOOTING. ENGINE OVER TORQUE INSPECTIONS COMPLETED AND ALLOWED TO CONTINUE IN SERVICE	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090102		EA  	2009	1	2	CA081029004      	1	20081026	G	2750	8004301	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) ON DECENT CREW SELECTED FLAPS DOWN AND FLAPS STOPPED AT 3 DEGREES. CREW ELECTED TO DO A GO AROUND AND PERFORMED TH	EIR CHECKLIST.  ADVISED TOWER THEY WOULD LIKE TRUCKS ON STANDBY BUT DID NOT DECLARE AN EMERGENCY.  CREW BRIEFED F/A AND 	MADE ANNOUNCEMENT TO PASSENGERS THEY WOULD BE LANDING A LITTLE FASTER THAN USUAL.  FLIGHT LANDED WITHOUT INCIDENT. RESET	 OF FLAP SYS AND MEL 27-02 APPLIED. NEXT FLIGHT HAD FLAP SNAG INTO. ACFT THEN FLOWN WHERE THE FLAP SKEW DETECT CONTROL U	NIT REPLACED AND SYS CHECKED SERVICABLE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090105		NE  	2009	1	5	CA081029005      	2	20080915	G	7261		OIL SYSTEM      			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE PILOTS OBSERVED ENG TEMPERATURE RISING THRU 800C AND PEAKING OVER 1000C. FLAMES WERE NOTICED 	FROM THE EXHAUST. THE ENG WAS SHUTDOWN AND FIRE BOTTLES DISCHARGED. A SINGLE ENG LANDING FOLLOWED.  POST FLIGHT INSPECTI	ON REVEALED OIL LEAKING FROM GAS GENERATOR CASE AND EXHAUST AREA. THE ENG WAS REMOVED AND SENT FOR INVESTIGATION WHERE T	EARDOWN REVEALED A NR 1 BEARING DISTRESS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABL	ISHED.		2	H	7	2 	4T	4	T		A41EU   	E4EA				 
	20090102		NE  	2009	1	2	CA081029006      	2	20081016	G	7250		TURBINE         			AEROSP	ATR72 	ATR72201    	8680943	EU  	PWA   	PW120 	PW124B      	 	NE  					LT ENGINE	SEIZED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, THE PILOT REPORTED LT ENG TQ INCREASE TO 109 PERCENT. THE PLA WAS MOVED TO GI BUT THE ENG SHUTDOWN	 ITSELF. THE ACFT WAS DIVERTED TO THE GATE. DURING TROUBLESHOOTING, THE ENG PARAMETERS WERE DOWNLOADED AND ANALYZED. REV	IEW SHOWED A DROP OF NH FROM 92 PERCENT TO 0, AND FUEL FLOW REDUCING FROM 550 TO 300, AND THEN TO ZERO. THE NL SENSOR AN	D THE TMM CHIP DETECTOR WERE INSPECTED AND FOUND CONTAMINATED. THE STARTER GEN WAS REMOVED IN ORDER TO ROTATE THE HP SHA	FT BUT THE HP TURBINE WAS SEIZED. BORESCOPE INSP PERFORMED AND CONFIRMED THAT THE HP TURBINE WAS NOT ROTATING. SUSPECTIN	G DISTRESS IN THE TOWERSHAFT AREA, THE COVER OF THE AGB DRIVE WAS REMOVED. INSP SHOWED A TOWERSHAFT WITH SIGNIFICANT RAD	2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
	20090102		CE  	2009	1	2	CA081030001      	1	20081012	G	2160	HYLZ503361	CONTROLLER      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	A/C SYSTEM	SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			CA											(CAN) THE FLIGHT CREW REPORTED SMOKE IN THE CABIN, THE ACFT LANDED SAFELY. MX INSPECTED AND SMOKE WAS THOUGHT TO BE COMI	NG FROM THE VENT BLOWER, THE BLOWER WAS REPLACED, GROUND RUN-UP CHECK WAS CARRIED OUT AND NO SMOKE WAS EVIDENT COMING FR	OM AIR CONDITIONING SYS. DURING TEST FLIGHT, THERE WAS NO HEATING CONTROL IN AUTO MODE. THE SYS WAS SWITCHED TO MANUAL A	ND HEAT CONTROLLING WAS POSSIBLE. WHEN THE SYS WAS SWITCHED BACK TO AUTO, A SLIGHT BURNING SMELL WAS NOTICED BUT THERE W	AS NO SMOKE IN THE CABIN. THE SYS WAS TURNED OFF AND THE ACFT RETURNED TO BASE. THE CABIN TEMP CONTROLLER WAS REMOVED AN	D INSPECTED. THERE WAS EVIDENCE OF DAMAGE AND ARCING ON THE UNIT AND IT WAS REPLACED AND THE ACFT RETURNED TO SERVICE.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
	20081230		EA  	2008	12	30	CA081030002      	1	20081024	G	3246	472439473232	SEAL            	CLEVELANDPNU		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WHEEL	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS PROBLEM WAS IDENTIFIED WHILE CARRYING OUT ROUTING MX ON  AMPHIBIAN FLOAT MAIN WHEELS. THE MFG PARTS BOOK SPEC	IFIED WHEEL GREASE SEAL THAT WHEN INSTALLED WERE 0.010 TOO SMALL OF A DIAMETER, CAUSING THE SEAL TO FALL OUT OF POSITION	.  HAVE CONTACTED THE OEM MFG TO DISCUSS THIS ISSUE AND THEY CONFIRMED THE GREASE SEAL LISTED IN THE PARTS MANUAL IS TOO	 SMALL OF A DIAMETER AND THAT THEY ARE IN THE PROCESS OF AMMENDING THEIR PARTS MANUAL TO SHOW THE CORRECT SEAL.  THESE F	LOATS ONLY HAVE 32 HOURS TSN, MFG FAILED TO INFORM THEIR CUSTOMERS OF THIS PROBLEM WITH THE SIZE OF THE GREASE SEAL.		1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081230		NM  	2008	12	30	CA081030003      	1	20081016	G	2751	1817392	TRANSMITTER     			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D17      	52049	NE  					LT FLAP POSITION	FAILED          	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) DURING FINAL APPROACH, WHEN THE PILOTS SELECTED FLAPS 25, THE FLAPS STOPPED SLIGHTLY PAST FLAPS 15. THE PILOTS SEL	ECTED FLAPS UP AND OVERSHOT THE APPROACH. THE FLAPS RETRACTED OK. ON THE NEXT APPROACH, THE FLAPS OPERATED NORMALLY. MX 	INSPECTED AND OPERATED THE FLAPS SYS AND FOUND NO FAULTS. REPLACED THE COCKPIT FLAP INDICATOR, SUSPECTING THE ACFT HAD A	 FALSE FLAP ASSYMETRY PROBLEM.  THE ACFT FLEW THE NEXT 2 DAYS WITH NO PROBLEMS.  THE FOLLOWING DAY, THE ACFT EXPERIENCED	 THE SAME PROBLEM ON APPRAOCH INTO AIRPORT. ON THIS OCCURANCE THE PILOTS HAD TIME TO SELECT THE FLAPS UP AND RESELECT TH	E FLAPS DOWN. ON THE SECOND TRY, THE FLAPS OPERATED NORMALLY.  MX INSPECTED AND FUNCTIONED THE FLAP SYS A SECOND TIME AN	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
	20081230		WP  	2008	12	30	CA081030004      	1	20080313	G	7810	C1693	EXHAUST DUCT    			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	DEFORMED        	W				O				OTHER                   				S			AFFECT SYSTEMS            			NR	NOT REPORTED   	1			CA											(CAN) VISUAL INSP (CF90-03R2) FOUND DEFORMATION AND CRACK IN MUFFLER ASSY AT THE BASE OF THE EXHAUST PIPE WITH SUBSEQUEN	T LEAK OF EXHAUST GASES INTO CABIN HEAT SYS, NO CO WARNING LIGHTS OR PILOT REPORTS POSTED. PART REPLACED AS REQ`D.					1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081230		SW  	2008	12	30	CA081031001      	1	20081031	G	6510	327211	COUPLING        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					T/R DRIVE SHAFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SHEDULED 100/300 HR INSP OF THE FWD T/R DRIVESHAFT SEGMENT THOMAS COUPLINGS, THE FWD THOMAS COUPLING WAS 	FOUND CRACKED. UPON FURTHER DISSASSEMBLY ONLY ONE OF THE LAMIATES WAS FOUND CRACKED. THE COUPLING WAS REMOVED FROM SERVI	CE AND REPLACED NEW. THE AFT COUPLING WAS ALSO INSPECTED FUTHER WITH NO DAMAGE NOTED.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20081230		SW  	2008	12	30	CA081031002      	1	20081029	G	3210	ESI2440	HOUSING         			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE33110T   	29065	NE  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9283 	53   							(CAN) DURING THE REQUIRED 5 YEAR OVERHAUL ON THE LANDING GEAR, A CRACK WAS DISCOVERED ON THE MLG HSG VISUALLY.   IR WAS 	CONFIRMED USING NDT METHODS LPI AS WELL AS EDDY CURRENT FOR CONFIRMATION.  EDDY CURRENT READING INDICATED A DEPTH OF .04	0".   THIS WAS THE FIRST OVERHAUL OF THIS LANDING GEAR BY THE OPERATOR SINCE PURCHASE 3 YEARS AGO.				1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P15EA	 
	20081230		SW  	2008	12	30	CA081031004      	1	20081031	G	2710		ROLL PIN        			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A67A     	52043	NE  					AILERON PUSHROD	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14   								(CAN) LT WING AILERON PUSHROD ASSY FOUND TO BE MISSING ONE ROLL PIN THAT RETAINS THE INBD END ROD END BEARING. THIS IS A	 DEFECT FROM THE FACTORY (INSIDE OF HOLE IS PAINTED). ALL OTHER ROD ENDS INSPECTED NO OTHER DEFECTS FOUND, ARROW SHOWS M	ISSING PIN HOLE.				1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
	20081230			2008	12	30	CA081103001      	4	20081016	G	2300		DISPLAY         			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  						FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			CA											(CAN) IN FLIGHT DURING DESCENT ACFT LOST ALL RADIOS AND NR 2 MFD. THEY WERE ABLE TO COMMUNICATE TO ATC BY GOING TO THE R	EVERSIONARY PANEL AND TURNING THE TUNE KNOB TO THE COMM1 121.5 SELECTION.  LANDING WAS UNEVENTFUL.  AFTER LANDING 20 MIN	UTES LATER CREW INDICATED THAT ALL THE FREQUENCIES WENT AMBER AND LOST THEIR ABILITY TO TUNE THE RADIO THROUGH THE FMS. 	WHEN THEY WOULD TRY TO TUNE THE RADIOS THE FREQUENCIES WOULD CHANGE ON THERE OWN. THE TRANSPONDER WAS ALSO INTERMITTENT,	 AND THEN THE COPILOT`S MFD WENT BLACK.  HAD THE CREW GO INTO THE MDC FAULT HISTORY AND THEY CAME UP WITH A LOT OF FAULT	S. PLEASE SEE ATTACHED PIC`S BELOW FOR FAULTS AND THE B3 CODES.  CREW THEN DID A COMPLETE POWER DOWN ACFT AND WAIT A FEW	2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
	20081230		NM  	2008	12	30	CA081103002      	1	20080716	G	3320	BR63031023	SOCKET          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CABIN LIGHTS	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A C-CHECK INSP OF THE CABIN LIGHTING SYS IT WAS FOUND THAT THE NR 5 FLOURESCENT CABIN LIGHTING BALLAST WAS 	MELTED AT THE BULB SOCKET. BALLAST WAS REMOVED AND REPLACED.  TT ON THE BALLAST CAN NOT BE ACURATLY DETERMINED BUT WITH 	A DATE STAMP OF FEB 11, 1987 IS LIKLEY ORIGINAL EQUIPMENT.  LIGHT WAS FUNCTIONING AT THE TIME THE DEFECT WAS FOUND. ONE 	OTHER LIGHTING BALLAST WAS ALSO FOUND WITH MINOR DAMAGE OF A SIMILAR NATURE. IT WAS REPLACED AS WELL.  SUBMITTED LATE AS	 THE C-CHECK WAS COMPLETED BY AN OUTSOURCE FACILITY AND UNTIL RECENTLY WAS NOT AWARE OF THE DAMAGED PARTS.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		EA  	2008	12	30	CA081103003      	1	20081102	G	2910	82970009325	LINE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	HYD SYSTEM	CHAFED          	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA			38294	38294							(CAN) DURING CRUISE FLIGHT, THE ACFT REPORTED LOSING NR1 HYD SYS FLUID AND ACTIVATION OF NR1 ISO VALVE. COMMERCIAL DECIS	ION MADE FOR ACFT TO RETURN TO ORIGINATING AIRPORT. FLAP (0) DEGREES AND LANDING CARRIED OUT THAT WAS DUE TO ACTIVATION 	OF NR1 HYD SYS ISO VALVE.  MAINT INSP FOUND HYD LINE FROM ENG DRIVEN PUMP TO PRESSURE MANIFOLD CHAFED AT NACELLE CLAMP. 	LINE REPLACED. ENG DRIVEN PUMP REPLACED AS PUMP HAD OPERATED AFTER FLUID DEPLETION. LEAK AND FUNCTION CHECKS CARRIED OUT	. ACFT RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230			2008	12	30	CA081103004      	4	20081008	G	8300	310186401	BEARING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ACCESSORY G/B	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			7114 	2318 							(CAN) NR 1 BRG FAILED WITHOUT OUTSIDE INFLUENCE. RESULTANT METAL CONTAMINATION CONTAINED TO THE GB,  MAIN OIL FILTER AND	 OIL PUMP.					1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20081230		SW  	2008	12	30	CA081103005      	1	20081030	G	8000	31057463	IGNITION SWITCH 			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	29073	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL LEAK ON THE ENG FROM LWR ENG COWL FOUND. TROUBLESHOOTING REVEALED THE PROBLEM AS A AUTO IGNITION PRESSURE SWIT	CH LEAKING AT THE BASE WELD.  INSP WITH A MAGNIFYING GLASS FOUND A CRACK APR .7500 AROUND THE CIRCUMFERENCE OF THE WELD.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
	20081230		EU  	2008	12	30	CA081104001      	1	20081028	G	3231		HOSE            			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					DOOR ACTUATOR	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) PILOTS REPORTED LOSS OF HYD PRESSURE AFTER LANDING WHILE TAXING BACK TO AMO.  ON INSP, FOUND IN THE RT GEAR WELL A	 FLEX HYD LINE INSTALLED WITH A SLIGHT TWIST ON IT. THE LOCKWIRE ON THE B-NUT WAS LOOSE, AND THE TWIST ON THE HYD LINE A	IDED IN ALLOWING THE B-NUT TO BACK OFF CAUSING THE HYDR LEAK IN THE RT GEAR WELL.  AREA CLEANED UP. THE LINE WAS INSPECT	ED FOR CRACKS AND PROPER ALIGNMENT RE-INSTALLED RE-TORQUES AND RE-LOCKWIRED. INSPECTED HYDR PRESSURE FILTER AND FOUND IT	 TO BE SERVICEABLE AND RE-INSTALLED FILTER. CARRIED OUT HYD FUNCTIONS AND LEAK CHECKS ON THE ACFT USING GROUND HYD CART.	 THERE WERE NO APPARENT LEAKS FOUND. CARRIED OUT GROUND RUNS ON AIRCRAFT, BLED HYD PUMPS AND CHECKED SYS PRESSURE AND CY	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
	20081222		NE  	2008	12	22	CA081104002      	2	20081031	G	7230		COMPRESSOR      			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	RT EINGE	SEIZED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE RT GENERATOR KICKED OFF-LINE. SHORTLY AFTER THAT TEMP INDICATIONS IN THE RT ENG CLIMBED CAUSING	 THE FLIGHT CREW TO SHUT DOWN THE ENGINE AND CONTINUE ON TO LAND AT THE SCHEDULED POINT OF LANDING. THE STARTER GEN WAS 	REMOVED AND THE COMPRESSOR SECTION OF THE ENGINE WAS FOUND TO BE SEIZED.				2	L	7	2 	4R	4	T		A669    	E26NE	6	C	P44GL	 
	20081222		GL  	2008	12	22	CA081104003      	1	20080927	G	2410	07A19474	BRACKET         			DIAMON	DA40  	DA40        	2990002	GL  	LYC   	O360  	IO360M1A    		NE  	MUHBR	MTV	MTV3BC      	EU  	ALTERNATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			805  								(CAN) DURING A ROUTINE INSP, THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE BROKEN ACROSS THE WIDTH OF THE BRACKET ADJA	CENT ONE OF THE MOUNTING HOLES. (REAR MOUNTING BOLT THAT IS USED TO ATTACH THE BRACKET TO THE ENGINE).					1	L	7	1 	3O	3	O	NT	A47CE   	1E10	5	C	USSR	 
	20081222		NM  	2008	12	22	CA081104004      	1	20081031	G	5554	17063073405	FITTING         			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					RUDDER	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			6515 								(CAN) ON PUSHBACK, RECEIVED FLIGHT CONTROL- NO DISPATCH MESSAGE. INVESTIGATION FOUND THE RUDDER UPPER FTG LUG BROKEN. RU	DDER PCU ACTUATOR WAS INSTALLED 2007-05-17.  CAUSE WAS FOUND TO BE MISSING SLIDING BUSHING, P/N 170-62218-003, IPC 27-21	-05 FIG.01 ITEM 170. THE ITEM WAS FOUND GREASED BUT NOT WORN IN A NEARBY CAVITY OF THE RUDDER. THIS IS CONFIRMED BY A CU	T/SLICED COTTER PIN THAT IS STILL IN THE BOLT, WHICH WAS PULLED THROUGH THE LOWER LUG, AND CAUSED DAMAGE ON THE FLANGED 	BUSHING IN THE LOWER LUG, BUT NO DAMAGE WAS FOUND ON THE INSIDE OF THE SLIDING BUSHING. THE BUSHING WHEN CORRECTLY INSTA	LLED, SITS INSIDE THE FLANGED BUSHING, AND PREVENTS SIDE LOADS FROM BEING APPLIED ON THE LUGS WHEN THE ATTACH BOLT IS TO	2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081222		EU  	2008	12	22	CA081105001      	1	20081105	G	2822	D107318D1	PUMP            			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL BOOST	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) TWICE NOW WE HAD FOUND THE FWD MAIN TANK BOOST PUMPS WHERE INSTALLED IN THE WRONG ORIENTATION, THE TRANSFER TUBES 	(FEED LINE) WAS PULL OUT OF THE FEED TANK. THE FORWARD TRANSFER PUMP HAS SYMMETRICAL MOUNTING HOLE. THE ORIENTATION OF T	HE PUMP DETERMINES THE FUEL FEED LINE POSITION. IF THE PUMP IS ROTATED THE FUEL FEED LINE MAY COME OUT OF POSITION. THIS	 HAS FOR CONSEQUENCE TO REDUCE THE FUEL TRANSFER TO THE FEED TANK. THE PROPER INSTALLATION FOR THE FORWARD FEED PUMP IS 	THE FEED LINE ATTACHING HARDWARE SHOULD BE ORIENTED 12.00 O`CLOCK, WITH THE LONGITUDINAL AXIS. (SEE FIGURE 62-3 DETAIL F	) IN THIS CASE THE HARDWARE WAS LOCATED AT 8.00 O`CLOCK.	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
	20081222		NE  	2008	12	22	CA081105002      	2	20080908	G	7200		ENGINE          			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  						OVERTEMP        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	M	J	PARTIAL RPM/PWR LOSS      	OVER TEMP                 	WARNING INDICATION        	DE	DESCENT        	1			CA											(CAN)  WHILE DEPARTING AREA WITH AN AIRSPEED OF 30 TO 40 KNOTS AND A 500 FT PER MINUTE RATE OF DESCENT, NR 2 ENG N1 LOW 	RPM AUDIO HORN SOUNDED ALONG WITH ILLUMINATION OF NR 2 ENG LOW OIL PRESSURE LIGHT. A SCAN OF ENG GAUGES REVEALED NR 2 EN	G HAD LOW N1 RPM WITH A CLIMBING T5 TEMP. FLT CREW IDENTIFIED PROBLEM AS AN ENG ROLL BACK AND SHUTDOWN OF NR 2 ENGINE CA	RRIED OUT. ACFT THEN RETURNED TO LANDING AREA AND MADE AN SINGLE ENG LANDING.  A POST FLT INSP OF T5 RECORDING SYS REVEA	LED ENGINE TEMP HAD REACHED 798 DEGREES C. ENGINE, FREE TURBINE ASSEMBLY AND FUEL CONTROL UNIT REPLACED AND AFTER A COMP	LETE GROUND CHECK ACFT RETURNED TO SERVICE.  ENGINE, FREE TURBINE AND FUEL CONTROL UNIT WERE RETURNED FOR AN OVER TEMP I	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
	20081222		EU  	2008	12	22	CA081105003      	1	20081102	G	3250	5322012040	LANDING GEAR    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NOSE	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXING FOR TAKEOFF, THE NOSE STEERING BECAME VERY STIFF. PILOT RETURNED TO THE RAMP AND MAINT DISCOVERED THA	T WITH THE ACFT WEIGHT ON THE STRUT, AND EVEN WITH THE SCISSORS DISCONNECTED, THE STEERING WAS EXTREMELY HARD, AND MADE 	A RATCHETING SOUND. THE NOSE GEAR ASSY WAS REPLACED AND THE ACFT RETURNED TO SERVICE. AWAITING TEAR DOWN REPORT ON NOSE 	GEAR ASSY TO ASCERTAIN CAUSE.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081222		NM  	2008	12	22	CA081105004      	1	20081103	G	2910		LINE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CREW NOTICED HYD QTY LOSS ON NR 2 SYS. REPORTEDLY, NR 2 HYD ISOLATON VALVE CAUTION LIGHT CAME ON, BUT HYD PRESSURE	 REMAINED NORMAL. THE CREW DECIDED TO PERFORM ALTERNATE GEAR EXTENSION FOR LANDING.  ACFT TOWED TO HANGAR, WHERE TECHNIC	IANS DISCOVERED RUPTURED HYD LINE IN NR 1 MLG GEAR BAY. LINE HAD BEEN CHAFED FROM A BONDING CLAMP (AN735C4). TECH REPORT	ED BONDING CLAMP WAS LOOSE, AND APPEARED TO BE INSTALLED WITHOUT SEALANT. RUPTURED HYD LINE WAS FOR THE NR 1 MLG DOWNLOC	K ACTUATOR. LINE REPAIRED WITH A PERMASWAGED SPLICE SECTION, AND A/C RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081219		NM  	2008	12	19	CA081105005      	1	20081103	G	2910	82974351003	LINE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, CREW NOTICED NR 2 HYD ISO VALVE CAUTION LIGHT CAME ON, NR 2 HYDRAULIC PRESSURE REMAINED NORMAL, AND	 THERE WAS A "SMALL QUANTITY" OF FLUID REMAINING IN NR 2 SYSTEM.  CREW DECLARED EMERGENCY LANDING. CREW PERFORMED AN ALT	ERNATE GEAR EXTENSION, AND ACFT LANDED.  ACFT TOWED TO HANGAR WHERE TECHNICIANS DISCOVERED HYDRAULIC FLUID DRIPPING FROM	 NR 2 NACELLE, O/B OF JET PIPE CENTER SECTION.  JET PIPE REMOVED AND TECHNICIANS DISCOVERED A SPLIT IN THE HYDRAULIC LIN	E, WHERE IT HAD BEEN CHAFFING ON THE FWD JET PIPE SHROUD DAMAGED LINE WAS PART OF MLG `NR 2 GEAR UP` PIPING, P/N 8297435	1-003.  LINE TO BE REPLACED.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081222		NE  	2008	12	22	CA081105006      	2	20081028	G	7200		ENGINE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 2	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB SHORTLY AFTER T/O, THE NR 2 ENGINE HAD AN UNCOMMANDED AUTOFEATHER AND SUBSEQUENT OVERTORQUE. THE CREW	 SHUT THE ENGINE DOWN AND THE ACFT RETURNED TO THE POINT OF DEPARTURE WHERE AN UNEVENTFUL SINGLE ENGINE LANDING WAS ACCO	MPLISHED. TROUBLESHOOTING LED TO THE REPLACEMENT OF THE TORQUE SIGNAL CONDITIONER UNIT AND THE TORQUE SENSOR. MM REQUIRE	MENTS ARE BEING PERFORMED FOR THE OVERTORQUE CONDITION BEFORE A DECISION FOR FURTHER ACTION IS TAKEN.  MFG WILL CONTINUE	 INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		NE  	2008	12	30	CA081105007      	2	20081029	G	7200		ENGINE          								PWA   	PT6   	PT6A68      	 	NE  						MAKING METAL    	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) DURING FLIGHT TEST, THE ENG HAD A PARTIAL FEATHERING OF THE PROPELLER LEADING TO A PARTIAL LOST OF THRUST. THE ENG	INE "CHIP LIGHT" CAME APPROX 20 SECONDS AFTER LOST OF THRUST. THE PILOT REDUCED POWER TO FLIGHT IDLE AND RETURNED TO BAS	E. POST FLIGHT INSP REVEALED METALLIC DEBRIS ON THE CHIP DETECTOR AND MAIN OIL FILTER. THE ENGINE WILL BE RETURNED TO MF	G FOR INVESTIGATION. UPDATES WILL BE PROVIDED IN DUE COURSE.								4	T			E26NE				 
	20081229		NE  	2008	12	29	CA081105008      	2	20081031	G	7261		CARBON SEAL     			AMD   	FALC50	FALCON2000  	2730170	NM  	PWC   	PW308 	PW308C      	52182	NE  					ENGINE	CRACKED         	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL, AT 90 KNOTS, THE OIL PRESSURE DROPPED TO ZERO AND THE LOW OIL PRESSURE WARNING ANNUNCIATED. T	HE CREW RETARDED THE POWER TO IDLE, ABORTED THE T/O AND RETURNED TO THE RAMP. TROUBLESHOOTING FOUND AN OIL LEAK FROM A C	RACKED CARBON SEAL ON THE FRONT HYD PUMP DRIVE PAD. THE ACFT WAS RETURNED TO SERVICE FOLLOWING ITS REPLACEMENT.				2	L	7	2 	4F	4	F	RT	A50NM   	E00065EN				 
	20081222		NE  	2008	12	22	CA081105009      	2	20081101	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					NR 2	FLAMED OUT      	W				A				UNSCHED LANDING         				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL270, THE PILOT NOTICED A POWER ROLL BACK ON NR 2 ENGINE.  HE IMMEDIATELY DIVERTED THE ACFT TO A	N ALTERNATE AIRPORT.  THE ENGINE THEN FLAMED OUT AND THE PILOT MADE A SINGLE ENGINE LANDING.  THE FUEL CONTROL WAS REPLA	CED AND THE ACFT RELEASED TO SERVICE.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE 	ESTABLISHED.			1	L	7	2 	4F	4	F		A22CE   	E00053EN				 
	20081222		WP  	2008	12	22	CA081105010      	1	20081105	G	5340	C8303	ANGLE           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ELT MOUNT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2149 								(CAN) FOUND CRACKED ANGLE DURING INSPECTION OF ELT MOUNT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081229		EA  	2008	12	29	CA081105011      	1	20080924	G	5240	33130131	PISTON          			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			256  								(CAN) DURING ANNUAL INSP, WATER DOOR UNLATCHING JACKS WERE REMOVED FOR INSPECTION. THE PISTONS OF THE JACKS WERE INSPECT	ED USING LIQUID PENETRANT INSPECTION FOR PRECAUTIONARY REASONS. BOTH PISTONS OF THE ACTUATORS WERE FOUND TO HAVE INDICAT	IONS SHOWING THERE WERE CRACKS. BOTH SHAFTS WERE SENT TO OUR AMO`S NDT COMPANY FOR MAGNETIC PARTICLE INSPECTION TESTING 	TO VERIFY THE CRACKS. CRACKS WERE VERIFIED. SERVICE BULLETIN 215-528 WAS CREATED TO ELIMINATE THE POSSIBILITY OF THE PIS	TONS CRACKING. BOTH OF THESE ACTUATORS HAD BEEN THROUGH OUR OVERHAUL SHOP. ONE ACTUATOR WAS REPAIRED, THE OTHER WAS OVER	HAULED. IN BOTH CASES, THE ACTUATORS HAD NEW PISTONS INSTALLED AND ACCUMULATED.	2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
	20081229		EA  	2008	12	29	CA081105012      	1	20081020	G	2751	601R930303	TRANSMITTER     			CNDAIR	CL600 	CL6002B19   	1900309	EA  											MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			12282								(CAN) UPON REACHING FL280 (CRUISING ALT) THE FLT CREW REPORTED THAT THEY RECEIVED THE SAME INDICATIONS ON EICAS AS THEY 	WOULD HAVE RECEIVED ON APPROACH (BRAKE TEMP, GEAR ICONS AND FLAP INDICATOR AND SPEED RASTER MOVING DOWN TO 210 KTS) AND 	THAT DURING THESE INDICATIONS, ACFT WITH AUTOPILOT ENGAGED STARTED TO PORPOSE UP AND DOWN +/- 50 TO 100 FT. THE FLAP DEG	RADED (S) MSG WAS POSTED AS WELL.  DURING THESE ALTITUDE FLUCTUATIONS, F/A WAS ASKED TO VERIFY WHETHER FLAPS WERE MOVING	. SHE INDICATED TO CREW THAT THE FLAPS WERE NOT MOVING.   ATC WAS NOTIFIED AND ACFT DIVERTED. JUST BEFORE THE FLT CREW S	TARTED THEIR DEVIATION, THE ACFT NOSED OVER BRIEFLY WITH ABOUT A 500 FT LOSS IN ALTITUDE BUT INSTANTLY RECOVERED BACK TO	2	L	7	2 	4F			RT	A21EA   					 
	20081229			2008	12	29	CA081106001      	4	20081104	G	2562	E01	ELT             																		INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLETING AN ANNUAL BENCH RECERTIFICATION CHECK ON AN ELT, NO POWER OUTPUT COULD BE MEASURED ON BOTH 121.5 	AND 243 MHZ FREQUENCIES. THE UNIT WAS STILL UNDER WARRANTY BY THE MFG AND IT WAS BELIEVED THIS WAS THE FIRST CHECK SINCE	 BEING PUT INTO SERVICE. THE UNIT WAS RETURNED TO THE MFG FOR REPAIR.																	 
	20081229			2008	12	29	CA081106002      	4	20081104	G	2562	E01	ELT             																		MALFUNCTIONED   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING THE ANNUAL BENCH RECERTIFICATION INSP OF AN ELT THE VALUE OF MEASURED CURRENT DRAW WAS OBSERVED TO EXCEED T	HE MFG SPECIFICATION BY 50MA. THE UNIT WAS STILL UNDER THE MFG WARRANTY AND IT WAS BELIEVED THIS INSP WAS THE FIRST CHEC	K COMPLETED SINCE BEING PUT INTO SERVICE. THE ELT WAS RETURNED TO THE MFG FOR REPAIR.																	 
	20081229		EA  	2008	12	29	CA081106003      	2	20081030	G	8520		CASE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINT (OIL CHANGE) OIL WAS DISCOVERED LEAKING FROM THE UPPER ENGINE CRANK CASE. FUTHER INSP CONFI	RMED A CRACK 3 INCHES LONG BETWEEN CYLINDER NR 2 AND 4.  ENGINE WAS REMOVED FOR REPAIR.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
	20081229		GL  	2008	12	29	CA081106004      	1	20081010	G	2840		FLOAT           	GE          		DHAV  	DHC2  	DHC2MKI     	2801830	GL  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	FUEL TRANSMITTER	DETACHED        	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) GENERAL ELECTRIC FUEL TRANSMITTER MODEL NR 56949-248, TYPE TJ-13. FUEL GAUGE READINGS WERE STUCK AT 22 GAL, INDICA	TING ON CENTER FUEL CELL. INVESTIGATION REVEALED THAT THE FUEL TRANSMITTER. FLOAT HAD BECOME DETACHED FROM THE FUEL TRAN	SMITTER.  FUEL TRANSMITTER REMOVED, REPAIRED, TESTED AND REINSTALLED.				1	H	7	1 	3R	3	R	RC	A806    	5E1	5	C	P206	 
	20081229		SO  	2008	12	29	CA081106005      	1	20081031	G	7820		BAFFLE          			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	MUFFLER	FAILED          	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) POWER LOSS ON TAKEOFF DUE TO BAFFLE FAILURE INSIDE MUFFLER WHICH RESTRICTED EXHAUST OF ENGINE CAUSING PARTIAL POWE	R LOSS.					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
	20081229		GL  	2008	12	29	CA081106006      	1	20081105	G	3220		ARM             			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	NLG WHEEL FORK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2010 								(CAN) BOTH ARMS OF THE NLG WHEEL FORK ASSY WERE FOUND CRACKED APPROXIMATELY 1.75 INCH FWD OF THE WHEEL AXLE BOLT. BOTH A	RMS ARE CRACKED THRU THE LOWER PORTION AND A .25 INCH CRACK HAS STARTED ON THE UPPER SIDE OF THE ARMS.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081229		EA  	2008	12	29	CA081106007      	1	20081103	G	2440	671GA01Y00	POWER UNIT      			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C5     	30050	NE  					APU	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) NOT ACCEPTING AC EXTERNAL OR APU GEN AC.  MX DETECT A BURNED CONTACTOR.  CURRENTLY ACFT EXTERNAL AVAILABLE LIGHT I	S ON.  ACFT ONLY MAINTAINS POWER FOR 3 SECONDS, AND KICKS OFF.  MFG HAS ISSUED A CONCESSION SL STATING NO OBJECTION TO F	ERRY PROVIDED THE FOLLOWING MTC PROCEDURES BE ACCOMPLISHED.  DISCONNECT CONNECTORS K119-S4 AND K119-S3 2. CAP AND STOW C	ONNECTORS K119-S4 AND K119-S3 IAW EEC/SPM 20-12-05 3. APU GENERATOR IS INHIBITED IAW MEL 24-22-01 4. EXTERNAL ACFT POWER	 SYS IS INHIBITED IAW MEL 24-41-03 FROM A FLT OPS PERSPECTIVE, FOR ENGINE START.  START ENG IAW QRH SUPP-2 ENGINE START 	(BATTERY/EXTERNAL AIR) PROCEDURE.	2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081222		NM  	2008	12	22	CA081107001      	1	20081104	G	6322	B1741	MOUNT           			ROBSIN	R22   	R22BETAII   	7640110	NM  										FAN WHEEL ASSY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			162  								(CAN) AT REINSTALLATION OF FANWHEEL ASSEMBLY, FOUND TAPERED MOUNTING FLANGE COMPLETELY CRACKED LONGITUDINALLY.  UNIT SEN	T TO MANUFACTURER FOR WARRANTY EXCHANGE.					1	G	7	1 	3O				H10WE   					 
	20081222		WP  	2008	12	22	CA081107002      	1	20081104	G	5340	C8303	ANGLE           			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ELT MOUNT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2197 								(CAN) THE ANGLE USED AS PART OF ELT INSTALLATION WAS FOUND SHEARED DURING 2200 HR OVERHAUL TEARDOWN.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081229		CE  	2008	12	29	CA081107003      	1	20081103	G	5347	MC07106582	SEAT TRACK      			CESSNA	182   	182J        	2072722	CE  	CONT  	O470  	O470R       	17026	SO  					LT PILOTS/LTPAS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2250 								(CAN) 3 CRACKS LT PAS RAIL, 1 CRACK LT PILOTS RAIL, SEAT RAILS SOME WEAR, WEAR WITHIN LIMITS.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
	20081222		NE  	2008	12	22	CA081107004      	2	20081026	G	7414	106006169	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAGNETO INTERMITTENT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081222		NE  	2008	12	22	CA081107005      	2	20081026	G	7414	1060064620	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAGNETO INTERMITTENT.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081222		WP  	2008	12	22	CA081107006      	1	20081029	G	6310	C0511	ACTUATOR        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CLUTCH	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CLUTCH ACTUATOR REMOVED DUE TO FAULTY SWITCHES.						1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081229		GL  	2008	12	29	CA081107007      	2	20081030	G	7323	23076061	DRIVE SHAFT     			BELL  	206   	206B1       	1181503	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE GOVERNOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2021 	2021 							(CAN) DURING REMOVAL OF THE GOVERNOR FOR SCHEDULED OVERHAUL, AT REMOVAL FROM ENGINE GEARBOX, THE CLIP THAT RETAINS THE D	RIVEGEAR ON THE PT SHAFT WAS NOT LOCATED IN THE GROOVE ON THE SHAFT, AND THE WASHERS THAT ARE RETAINED BY THE CLIP AND S	ET AGAINST THE DRIVE GEAR, WERE FOUND SITTING IN THE MALE SPLINE OF THE GEARBOX DRIVE. IT APPEARS AS THOUGH THE END OF T	HE DRIVESHAFT WAS WORN DOWN TO ALLOW THE CIRCLIP TO BECOME DISLODGED FROM THE GROOVE AND WORK IT`S WAY OFF THE SHAFT, HO	WEVER THE DAMAGE TO THE SHAFT COULD HAVE BEEN DUE TO THE DISLODGED WASHERS SITTING IN THE DRIVE SPLINE. THE ONLY ITEM FO	UND RETAINING THE DRIVEGEAR WAS THE SPRING ON THE BACK SIDE OF IT. THE ENGINEER INSPECTED THE GEARBOX DRIVE BUT WAS UNAB	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081229		EU  	2008	12	29	CA081107008      	1	20081104	G	6220	117775P	BALL JOINT      			SNIAS 	350   	AS350*      	       	EU  	LYC   	LTS101	LTS101*     		NE  					STARFLEX	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			277  								(CAN) IT WAS DISCOVERED DURING A DAILY INSP THAT THE TEFLON LINING INSIDE ONE OF THE STARFLEX BALL JOINTS WAS DISPLACED.	 THE BEARING WAS REPLACED BEFORE FURTHER FLIGHT AND IT WAS NOTICED THAT THE TEFLON WAS STILL GLUED FIRMLY IN PLACE BUT I	T WAS MISALIGNED FROM ITS ORIGINAL POSITION.				1	G	7	1 	3U	3	U		H9EU    	E5NE				 
	20081222			2008	12	22	CA081110001      	4	20081101	G	2562	C362042702	BATTERY         	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ULB	INCORRECT       	W				K				NONE                    				W	L		INADEQUATE Q C            	NO TEST                   		IN	INSP/MAINT     	1			CA											(CAN) WRONG BATTERY INSTALLED IN UNIT.  CORRECT BATTERY INSTALLED INTO ULB. REF WO NR 214939						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081222		CE  	2008	12	22	CA081110002      	1	20081105	G	3260	1003810061	SWITCH          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					NLG	INTERMITTENT    	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) AFTER PILOT SELECTED GEAR DOWN, THERE WAS NO INDICATION THE NOSE GEAR WAS DOWN AND LOCKED, ACFT DIVERTED BACK TO M	X BASE.  ON ROUTE NOSE GEAR INDICATION CAME ON.  ACFT LANDED WITHOUT INCIDENT.  MX REPLACED NOSE GEAR DOWN LOCK INDICATO	R SWITCH AND RETURNED TO SERVICE.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
	20081229		GL  	2008	12	29	CA081110003      	1	20081106	G	5311		SPAR            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					FUSELAGE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5972 								(CAN) DURING THE 6000 HOUR INSP DELAMINATIONS AND CRACKS WERE DISCOVERED ON THE SPAR BRIDGE. THE DELAMINATIONS AND CRACK	S WERE FOUND ON THE RT SIDE ON THE AFT UPPER CORNER AT THE FILLET FROM BRIDGE TO SKIN INSIDE OF THE FUESLAGE AS VIEWED F	ROM THE GAS TANK AREA. A SERIES OF INTERCONNECTED CRACKS THAT APPREAR TO BE IN THE RESIN ONLY. OVERALL LENGTH IS APPROX 	40 MM, VARYING IN DEPTH FROM SURFACE CRACKS TO APPROX 3 MMM DEEP. THE LT SIDE HAD DELAMINATIONS AND CRACKS ON THE UPPER 	AFT CORNER AT THE FILLET FROM BRIDGE TO SKIN INSIDE OF THE FUSEALGE (THE OPPOSITE TO THE RT SIDE). LENGTH WAS 6-8MM AND 	DEPTH 5MM.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
	20081222		EA  	2008	12	22	CA081110004      	1	20081109	G	5751		CONTROL CABLE   			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					AILERONS	DISLODGED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT WING FWD AILERON CONTROL CABLE FOUND SITTING BEHIND THE AILERON INPUT ROD QUADRANT GUARD.  CABLE MOVED OUT OF I	TS LOCATION WITH SLIGHT FINGER ACTION.  CABLE HAS LIGHT RUBBING MARK BUT ALUMINUM QUADRANT GUARD FOUND BADLY GROOVED.  W	INGS CONTROL CABLE TENSION TOOK ON BOTH SIDE.  LT SIDE MEASURED AT 30 LBS AND RT SIDE AT 20 LBS.  RIGGING TENSION IS BET	WEEN 55 AND 65 LBS AT 20 DEGREES CELSIUS.  TENSION TOOK WITH CABLE MISROUTED AND AT PROPER PLACE,  NO SIGNIFICANT TENSIO	N DIFFERENCE AT 2-3 LBS.  LT SIDE CABLE SECTION INSPECTED AT SAME LOCATION, CABLE FOUND ROUTED PROPERLY.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20081229		GL  	2008	12	29	CA081110005      	1	20081109	G	3220	203220080	FORK            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					NOSE GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1541 								(CAN) ON PREFLIGHT OF ACFT, PILOT DISCOVERED CRACKS IN NOSE WHEEL FORKS APPROXIMENTLY 1 INCH FROM AXLE AT RADUS OF MACHI	NING (MACHINED FOR WEIGHT REDUCTION DURING PRODUCTION), ON SIDE OF FORKS.   RT SIDE IS CRACKED DEPTH OF MACHINE AREA ON 	TOP AND .7500+ ON THE BOTTOM  LT SIDE OF FORK CRACKED BOTTOM DEPTH OF MACHINING AND .5+ ON TOP.  ACFT WAS HAD PROPELLER 	STIKE ON LANDING APPROX 1000 HRS AGO, NOSE GEAR LEG WAS REPLACED AT THAT TIME AND FORK VISUALY INSPECTED WITH NO CRACKS 	DETECTED. NO CRACKS WERE NOTED DURING 100 HR INSP THAT WAS COMPLETED 75 HR AGO.   NO OTHER REPORTED HARD LANDING HAVE BE	EN REPORTED. ACFT INSPECTED, NO OTHER DAMAGE DETECTED.   MFG HAS ASKED FOR PARTS TO BE RETURNED FOR ENGINEERING EVALUATI	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
	20081222		WP  	2008	12	22	CA081110006      	1	20081030	G	2432	B4151	RELAY           			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					BATTERY	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA			386  								(CAN) BATTERY WOULD NOT COME ONLINE ALTHOUGH FULL BATTERY VOLTAGE WAS OBSERVED AT BATTERY CONNECTIONS.  BATTERY RELAY WA	S REPLACED AND ACFT RETURNED TO SERVICE.					1	G	7	1 	3O	3	O		H11NM   	E295				 
	20081222		NM  	2008	12	22	CA081110007      	1	20081110	G	5310	87140011001	STRUCTURE       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			51173								(CAN) BIRD STRIKE JUST UNDER NOSE AREA.   FOUND NR 2 LOWER COWL WITH INTERNAL CONE DAMAGE, LOWER COWL REMOVED.  ENGINE B	OROSCOPED WITH MINIMAL DEBRIS FOUND INSIDE ENGINE.  NO DAMAGE NOTED NO DEBRIS FOUND ON LP COMPRESSOR.  AIRFRAME INSPECTI	ON STILL TO BE CARRIED OUT.  AIRFRAME INSPECTION COMPLETED AS PER MM CHAPTER 5.  PROP INSPECTED AS PER HS MM.61.10.  NEW	 LOWER COWL INSTALLED, GROUND RUN COMPLETED FOR POWER ASSURANCE AND TESTING OF LOWER COWL.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081229		EA  	2008	12	29	CA081111001      	1	20081107	G	2150	8084402	BYPASS VALVE    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					NR 1 ACM	STUCK           	W				O				OTHER                   				B	G	M	SMOKE/FUMES/ODORS/SPARKS  	MULTIPLE FAILURE          	OVER TEMP                 	TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI IN, CREW NOTICED ONE OF THEIR AIR-CONDITIONING PACKS WAS OVER TEMPING. THEY WHERE NOT ABLE TO CONTROL IT, 	SOON NOTICED SMOKE ON FLIGHT DECK. F/A WAS NOTIFIED AND A RAPID DEPLANEMENT WAS CONDUCTED AT GATE. MX FOUND THE DUAL BYP	ASS VALVE STUCK IN THE FULL HOT POSITION.  NR 1 ACM WAS ALSO FOUND SEIZED (P/N 782790-15, S/N 930930. TSN 28517 HOURS, C	YCLES 14277, TSO 878735).  IN ADDITION COMPRESSOR OUTLET OVERTEMP SWITCHES (P/N 750659-16. RATED TO 415F) WERE FOUND IN	STALLED IN THE LT AND RT DUCT OVERTEMP SWITCH POSITIONS INSTEAD OF (P/N 750665-9. RATED TO 220F). THIS WAS REPORTED TO 	COMPANY MX SAFETY DEPT.  BYPASS VALVE, NR 1 ACM AND THE SWITCHES WERE REPLACED, FUNCTION CHECKED SERVICEABLE AND THE ACF	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081230		EA  	2008	12	30	CA081111002      	1	20081028	G	2612		FIRE WARNING    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  						ILLUMINATED     	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											EXPERIENCED AN EMERGENCY EVACUATION A/P ON TAXIWAY (M), DUE SMALL FIRE EMITTING FROM ENG WHILE TAXIING. LOCAL ARRF RESPO	NDED, PASSENGERS & CREW EVACUATED ACFT WITHOUT INCIDENT. MX VISUALLY INSPECTED ACFT & ENG WITH NO DEFECTS NOTED. ENGINES	 WERE RUN UP WITH NO DEFECTS NOTED. MX ISSUED A SPECIAL FLT PERMIT FOR FURTHER INVESTIGATION.  NO INFORMATION TO DETERMI	NE IF THERE WAS FLAME AS WELL AS SMOKE, ASSUMED FIRE REPORTED RESTRICTED TO ONE OR BOTH ENG JETPIPES. REPORT MENTIONS "L	T ENGINE FLAMES/FIRE".		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081222		NM  	2008	12	22	CA081111003      	1	20081107	G	5610	8SC0043014	WINDSHIELD      			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, THE CREW WITNESSED THE RT COCKPIT HEATED WINDSHIELD CRACK.  THE CRACK SLOWLY KEPT PROGRESSING TO	 A LENGTH OF ABOUT 5 INCHES.  THE CREW INITIATED A RETURN TO BASE AND LANDED WITHOUT FURTHER INCIDENT.  MX R&R THE WINDS	HIELD.  NO CAUSE AS TO THE FAILURE COULD BE DETERMINED, OTHER THAN IT APPEARS TO HAVE ORIGINATED AT THE EDGE OF THE WIND	OW AT A HEATING ELEMENT.  THE TOTAL TIME ON THIS WINDSHIELD COULD NOT BE DETERMINED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081222		EA  	2008	12	22	CA081111004      	1	20081110	G	2750		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) FLAPS SELECTED TO 20 DEGREES FOR TAKE-OFF.  AFTER TAKE-OFF, FLAPS WERE SELECTED TO 8 DEGREES AND THE FLAPS LOCKED 	AT 20 DEGREES.  FLAP FAIL CAUTION EICAS MSG AS WELL.  FOUND SKEW DETECT FAULT LIGHTS ILLUMINATED, BOX RESET CARRIED OUT 	ALONG WITH BREAKER RESET.  FLAPS CYCLED NUMEROUS TIMES WITHOUT FAILURE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081229		NM  	2008	12	29	CA081111005      	1	20081104	G	3230	483003	SELECTOR VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) CREW REPORTED A NOSE STEERING CAUTION ON TAKEOFF. UPON LANDING, ALL 3 GEARS SHOW RED WITH GEAR DOWN SELECTION. ALT	ERNATE EXTENSION USED IAW QRH. ALL GREEN WITH ALT EXTENSION. FAULT CODES HAVE BEEN RETRIEVED AND ENTERED INTO THERE COMP	UTER SYS. MX FOUND A SHORT TO GROUND IN THE UP SOLENOID OF THE LANDING GEAR SELECTOR VALVE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081229		EA  	2008	12	29	CA081111006      	1	20081020	G	2916	9604501	RESERVOIR       			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5B1   	30052	NE  					HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) NR3 HYD SYS LOW PRESSURE CAUTION MESSAGE DURING CLIMB. INBD SPOILERS CAUTION MESSAGE ALSO PRESENT DUE TO HYD LOW P	RESSURE.  ACFT DECLARED EMERGENCY, ALTERNATE EXTENSION USED TO DEPLOY LANDING GEAR, AND RETURNED TO FIELD.   FLUID LOSS 	WAS DISCOVERED FROM HYD SYS NR 3 RESERVOIR.  HYD RESERVOIR WAS CHANGED AND ALL SYS TESTED AND FUNCTIONED SATIS. ACFT RET	URNED TO SERVICE.  NO P/N`S OR S/N`S AVAILABLE AT THIS TIME. UPDATE: 17-NOV-08, 08:08, "P/N 960450-1 S/N OFF: 239 S/N ON	: 484".		2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20081229		NM  	2008	12	29	CA081112001      	1	20081110	G	3260	401020101	PROXIMITY SENSOR			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	LT MLG	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			6338 								(CAN) PILOTS REPORT:  AFTER GEAR SELECTED UP, LT MAIN GEAR DOOR REMAINED OPEN WITH AMBER ADVISORY LIGHT. CONTINUED CLIMB	 NOT ABOVE 185KTS, CONDUCTED AFTER TAKE-OFF CHECKLIST. QRH CONSULTED AND ACTIONED ALTERNATE GEAR EXTENSION.  LINE MX CON	FIRMED DEFECT AND INVESTIGATION REVEALED THE `LT GEAR DOOR CLOSED` PROX SENSOR TO BE UNSERVICEABLE. UNSERVICEABLE SENSOR	 REPLACED WITH A NEW ITEM AND THE INSTALLED SENSOR WAS RIGGED IAW THE ACFT MM.  ACFT RETURNED TO SERVICE WITHOUT FURTHER	 INCIDENT.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081229		NM  	2008	12	29	CA081112002      	1	20080529	G	5714	85730800002	SHROUD          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					WING BOX	MISMANUFACTURED 	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			9    	9    							(CAN) DURING PRODUCTION OF 4208 IT WAS DISCOVERED THAT THE CENTER WING LOWER SHROUD RT DRAIN HOLES WERE NOT PRESENT. A D	ISCREPANCY WAS RAISED AND CLEARED BY DRILLING NEW HOLES IN SITER. UPON THE DELIVERY/ACCEPTANCE FLIGHT, IT WAS DISCOVERED	 THAT THE AFT COFFEE MARKER WAS UNSERVICEABLE. A TECHNICAL INVESTIGATION REVEALED 6 OF 9 (115 VAC) WIRES DAMAGED. A REPA	IR WAS MADE IAW WDM 20-16-00. A SMS/SRS WAS RAISED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081229		EU  	2008	12	29	CA081112003      	1	20081030	G	7500	9550170290	PRESSURE SWITCH 			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			CA											AFTER A LANDING AND COOLDOWN THE PILOT PRESSED THE START/DETENT SWITCH TO MOVE THE TWIST GRIP TO CUTOFF. THE ENGINE IMME	DIATELY FLAMED OUT WHEN THE SWITCH WAS DEPRESSED (TWIST GRIP WAS NOT TURNED).  THEN ATTEMPTED TO RECREATE THIS PROBLEM A	ND IT HAPPENED AT ALL ENGINE SPEEDS. AFTER TROUBLESHOOTING IT WAS DETERMINED THAT THE P3 PRESSURE SWITCH WAS THE PROBLEM	.			1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
	20081229		GL  	2008	12	29	CA081112004      	1	20081110	G	5755	GT41501009	SPOILER SYS     			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF AND DURING CLIMB, A LATERAL CONTROL MOVEMENT TO THE LT WAS NOTICED . ONE SPOILERON DEPLOYED ON THE L	T WING (2 PAIR OF MULTI-FUNCTION SPOILER (MFS) IAW WING ON THIS ACFT). THE LT NR 2 MFS WAS AMBER LINE ON THE FLIGHT CONT	ROL SYNOPTIC PAGE. SEVERAL EXTRACT AND RETRACT ACTIONS ON THE SPOILERS SYS PERFOMED, WITHOUT SUCCESS AND AILERON TRIM WA	S ADJUSTED TO CORRECT THE ACFT LEVELING. CREW DECIDED TO ABORT THE FLIGHT AND LAND TO THE AIRPORT DEPARTURE .  AFTER LAN	DING ,THE LT NR 2 MFS WAS STILL FULLY DEPLOYED AND RETRACTED BY ITSELF WITH THE BLEED DOWN OF HYD PRESSURE OF THE SYSTEM	. (HYD OFF)	2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
	20081229		NM  	2008	12	29	CA081112005      	1	20081107	G	2697	FRF6E12S3S	CONNECTOR       			BOEING	727   	727247      	138408F	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					FIRE WARNING SYS	DAMAGED         	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AT APPROX 700 FT, AGL T/O YHZ FIRE WARNING LIGHTS ON GLARE SHIELD WERE DIMMLY ILLUMINATED. NO AURAL WARNING. APU F	IRE HANDLE ILLUMINATED. SWITCH PULLED AND BOTTLE  DISCHARED.  ACFT RETURNED TO DEPARTURE.   RECTIFICATION AFTER TROUBLES	HOOTING FOUND APU FIRE SENSOR/RESPONDER CONNECTOR D1428 SEVERELY CORRODED.  INTERIOR OF CONNECTOR FOUND PACKED WITH GREE	NISH REDIDUE.  BOTH ENDS OF CONNECTOR (SOCKETS AND PINS) CLEANED AND INSPECTED.  APU FIRE DETECTION SYS TESTED IAW AMM 2	6-15-00  FOLLOWUP:  REF: WRI 26-11/3077 APU FIRE SENSOR/RESPONDER CONNECTOR D1428 TO BE REPLACE. FOUND CONNECTOR WEATHER	 GASKET DAMMAGED CAUSING CORRROSION IN SOCKETS.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081222		SO  	2008	12	22	CA081112006      	1	20081106	G	3245	40140	TUBE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					MLG TIRE	FLAT            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING, IT WAS NOTICED THAT THE NOSEWHEEL WAS FLAT. DISASSEMBLY OF THE NOSEWHEEL HUB SHOWED A POSSIBLE WEAR	 SPOT BETWEEN THE TIRE AND TUBE.  THE TUBE WAS DAMAGED DURING THE LANDING AND TAXI SO IT IS NOT KNOWN IF THIS WAS THE AC	TUAL CAUSE OF THE PROBLEM.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20081222		NE  	2008	12	22	CA081112007      	2	20081031	G	7200		ENGINE          			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  						MAKING METAL    	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) DURING FLIGHT, THE ENGINE LOST TORQUE AND OIL PRESSURE.  THE PILOT SHUT IT DOWN AND PERFORMED A SINGLE ENGINE LAND	ING.  POST FLIGHT INSPECTION FOUND THE PROPELLER SEIZED AND METAL DEBRIS IN THE EXHAUST.  MANUFACTURER WILL CONTINUE INV	ESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
	20081229		CE  	2008	12	29	CA081112008      	1	20081112	G	3210	130909B19	BOLT            	BEECH       		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	SUPPORT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3428 								(CAN) SUPPORT ASSY BRACKET ON BOTH SIDES OF THE NLG ACTUATOR PIVOT HAD 5 OF THE 6 BOLT HEADS SHEARED OFF LEAVING THE BOL	T SHANK AND CAPTURE NUT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
	20081229		EA  	2008	12	29	CA081112009      	2	20081031	G	7200		ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL180, THE CREW FELT A STRONG JOLT AND VIBRATIONS THROUGH THE AIRFRAME. A QUICK REVIEW OF THE GAG	ES SHOWED A POWER LOSS ON NR 2 ENG.  THE ENG WAS SECURED AND THE CREW PERFORMED A SINGLE ENGINE LANDING. GROUND INSP FOU	ND NOTHING OF SIGNIFICANCE AND THE ACFT WAS FERRIED BACK TO BASE. DURING FINAL APPROACH OF THE FERRY FLIGHT, THE ENGINE 	LOST TORQUE BUT RECOVERED WITHOUT ANY PILOT INPUTS. THE ACFT  LANDED SAFELY AT DESTINATION.  MFG WILL CONTINUE INVESTIGA	TING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20081229		NE  	2008	12	29	CA081112010      	2	20081104	G	7532		BLEED VALVE     								PWA   	305   	PW305B      	52128	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) DURING LANDING, THE ENGINE FLAMED OUT. RE-START ATTEMPT WAS UNSUCCESSFUL. TROUBLESHOOTING LED TO THE REPLACEMENT O	F THE COMPRESSOR BLEED VALVE ASSY.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.										4	F			E35NE				 
	20081229		WP  	2008	12	29	CA081112011      	1	20081031	G	2421		GENERATOR       			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	NR 2	INOPERATIVE     	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE CREW OBSERVED THE NR 2 GENERATOR GO OFF LINE WITH AN INCREASE IN ENG TEMP.  IT WAS SHUTDOWN AND	 A SINGLE ENG LANDING FOLLOWED. POST FLIGHT INSP FOUND THE COMPRESSOR HARD TO ROTATE. THE ENGINE WILL BE REMOVED AND FOR	WARDED FOR INVESTIGATION AND REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHE	D.			2	L	7	2 	4R	4	T		A669    	E26NE	6	C	P44GL	 
	20081229		EU  	2008	12	29	CA081112012      	1	20081111	G	3230	5322012289	DRAG LINK       			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			9376 								(CAN) ON CALL MAINT RECEIVED A PHONE CALL FROM CAPTAIN, PILOT REPORTED HEARING A LOUD NOISE FROM THE NOSE GEAR AREA WHEN	 DEPARTING THE NORTHERN AIRPORT. HE SAID THE NOSE GEAR TRANSIT LIGHT DID NOT EXTINGUISH AND HE THEN PROCEEDED TO RESWING	 THE GEAR WHICH THEN CAUSED THE LIGHT TO EXTINGUISH. ON DECENT, HE EXTENDED THE GEAR AND SAID THE NOSE GEAR TOOK LONGER 	THAN NORMAL TO FULLY EXTEND AND GIVE GREEN DOWN AND LOCKED INDICATION. MX INSTRUCTED HIM TO VISUALLY INSPECT THE NOSE GE	AR AND GEAR BAY AND FOUND NOTHING UNUSUAL. THE DESISON WAS MADE TO RETURN TO DEPARTURE WITH THE GEAR EXTENDED.  MX WAS T	HERE TO MEET THE ACFT WHEN IT RETURNED. THE ACFT WAS HANGERED AND PLACED ON JACKS. MX THEN DID A GEAR SWING AND THE NOSE	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081229			2008	12	29	CA081113001      	4	20081113	G	3460	0710159803	CONTROLLER      			PILATS	PC12  	PC1247      	7090552	EU  	PWA   	PT6   	PT6A67      	52043	NE  					MFD	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			147  	147  							(CAN) WE HAVE JUST EXPERIENCED THE 4TH FAILURE OF THE KMC 2220 MFD CONTROLLER.   THE JOYSTICK FUNCTION FAILS TO ALLOW CU	RSOR MOVEMENT ON THE FLIGHT SCREENS AND DOES NOT ALLOW FLIGHT CREWS TO ENTER OR MODIFY ROUTING IN FLIGHT.  THE REPLACEME	NT UNIT CLEARED PROBLEM FOR NOW.   HAVE BEEN TOLD MFG IS LOOKING INTO THE PROBLEM AS WE ARE NOT THE ONLY CUSTOMER HAVING	 THIS ISSUE.			1	L	7	1 	4T	4	T	RT	A78EU   	E26NE				 
	20081229			2008	12	29	CA081113002      	2	20081113	G	7497		WIRE            																	MAGNETO	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COIL TO POINTS WIRE WORN THROUGH TO STRANDS DUE TO RUBBING ON FRAME OF DISTRIBUTOR BLOCK.																			 
	20081229			2008	12	29	CA081113003      	2	20081022	G	7414	K3822	DISTRIBUTOR GEAR																	MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DISTRIBUTOR FINGER LOOSE ON GEAR ASSY.																			 
	20081229		NM  	2008	12	29	CA081113004      	1	20081112	G	7500	ZZ84M46P01	DUCT            			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					BLEED AIR SYS	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT PRECOOLER INLET RUBBER DUCT SHOWS SIGNS WHERE THE SEAM HAS COME APART, AS A RESULT THE FAN AIR HAS FROM THE SPL	IT SEAM HAS CAUSED DAMAGE TO THE THRUST REVERSER HEAT SHIELD. T/R FIRE BLANKET PN 104M1031-22, SN6011203-013 THIS HAS AL	SO OCCURRED ON ACFT FIN 317 C-FHKI SN 190-0052 AND FIN 342.C-FNAP SN 190-00142.				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20081229		EA  	2008	12	29	CA081113005      	1	20081112	G	2751	8004301	DETECTION SYS   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					FLAP SYSTEM	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			18700								(CAN) FLAP FAIL, SELECTED 20, FAILED AT 8 DEGREES. ON APPROACH, CREW UNAWARE OF OAT DUE TO WORK LOAD.   FLAP SKEW DETECT	ION UNIT REPLACED IAW AMM 27-51-15, PG 401. FLAPS CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081230		SO  	2008	12	30	CA081113006      	1	20081107	G	3246	06104700	WHEEL           			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6560 								(CAN) DURING A TIRE CHANGE, THE AME NOTICED A 4 INCH CRACK ALONG THE WHEEL, WHERE THE TIRE BEAD SITS. THIS TYPE OF FINDI	NG IS RATHER UNUSUAL AT THE AMO. NO HARD OR UNUSUAL LANDINGS WERE REPORTED. THE WHEEL HALF WAS REPLACED, AND THE ACFT RE	TURNED TO SERVICE.				1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920	 
	20081230		SW  	2008	12	30	CA081113007      	1	20081104	G	6420	407012108101	BUSHING         			BELL  	407   	407         	1182206	SW  										PITCH HORN ASSY	DEFORMED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WASHER BETWEEN THE T/R PITCH HORN AND PITCH LINK FOUND DEFORMED.						1	G	7	1 	3U			O	H2SW    					 
	20081230		SW  	2008	12	30	CA081113008      	1	20081016	G	6210	206010200133	TAB             			BELL  	206   	206B        	1181511	SW  										ROTOR BLADE	DEFORMED        	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			11   								(CAN) LOUD BANG WAS NOTED WITHING 10 MINUTES OF FLIGHT. LEVEL OF VIBRATION DID NOT INCREASE. INSP AFTER LANDING FOUND TH	AT THE TRIM TAB WAS DEFORMED (UPPER SIDE WAS BENT UPWARD AND LOWER SIDE BENT DOWNWARD). PEEL-PLY HAS BEEN LEFT ON THE TR	IM TAB.				1	G	7	1 	3U				H2SW    					 
	20081230		NM  	2008	12	30	CA081114001      	1	20081113	G	3297	464605	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROXIMITY SWITCH	SHORTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) CREW SELECTED GEAR DOWN AND GOT 3 GREENS AND LT MLG DOOR AMBER LIGHT.  ALTERNATE EXTENSION C/O AND CREW OBSERVED A	LTERNATE INDICATION SHOWED LT MLG (UNSAFE). CREW DECLARED EMERGENCY AND LANDED. PAX DEPLANED ON RUNWAY AND AFTER GEARS W	ERE PINNED ACFT TAXIED TO GATE. FAULT CONFIRMED BY PSEU TO BE LT LGDNLK2 OPEN CIRCUIT.  PROXIMITY SWITCH HARNESS ASSY PN	 46460-5 REPLACED AND ACFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081230			2008	12	30	CA081114002      	4	20081111	G	3413	4067644901	INDICATOR       			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	IVSI	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) AFTER TAKOFF, CAPTAINS SIDE IVSI FAILED, ACFT RETURNED TO AIRPORT - IVSI REPLACED AND FUNCTION CHECK SERVICEABLE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		GL  	2008	12	30	CA081114003      	1	20081112	G	2720	2227271300	PEDAL           			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3313 								(CAN) DURING ROUTINE INSP THE RUDDER PEDAL WAS FOUND CRACKED.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081230		NE  	2008	12	30	CA081114004      	1	20081103	G	6320	S613522032001	GEARBOX         			SKRSKY	S61   	S61N        	8142104	NE  										MAIN ROTOR	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA		CFCLM									(CAN) MGB HAD A INDICATION ON THE MGB BEING CONTAMINATED WITH METAL. REMOVED THE MGB AND RETURNED IT TO MANUFACTURER WHO	 DISASSEMBLED THE MGB TO FIND THAT THE CAUSE OF THE METAL CONTAMINATION WAS FROM THE UPPER BRG SUPPORT NUT, P/N: S6135-2	2032-001  THE CAUSE OF THE METAL CONTAMINATION WAS FROM THE UPPER BRG SUPPORT NUT.				2	G	7	2 	4U				1H15    					 
	20081230		NE  	2008	12	30	CA081114005      	2	20081104	G	7230	8934825	IMPELLER        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	29073	NE  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2407 								(CAN) HOT SECTION INSPECTION WAS BEING CARRIED OUT BY ENGINE SHOP ON ENGINE SN P44659C AND IT WAS NOTED THAT THE IMPELLE	R WAS CRACKED. THIS IMPELLER IS NOT TRACKED. THE TIMES ON THE IMPELLER SINCE INSTALL ARE 2407.0 AND 3434 CYCLES. THIS IS	 NOT THE 1ST INSTANCE OF PROBLEMS IN THIS 2ND STAGE IMPELLER.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20081230			2008	12	30	CA081114006      	2	20081113	G	7200	SB3208A1	BEARING         																	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RECEIVED NEW BEARING FROM WHS 290 WITH CORROSION ON BEARING JOURNAL AND ROLLERS. CURE DATE ON PACKAGE IS 0206, BEA	RING PN SB3208A-1. BATCH PN 0605118341.  HSI HAVE BEEN INFORM OF VARIOUS BEARINGS DELIVERED THAT HAVE SIGNS OF CORROSION	 ON THEM.																	 
	20081230		NM  	2008	12	30	CA081114007      	1	20081114	G	5710	85720013006	STRUCTURE       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT WING LE	DAMAGED         	W				O				OTHER                   				C			F.O.D.                    			LD	LANDING        	1			CA			45006								(CAN) BIRD STRIKE ON LANDING RT WING ENGINE AREA.  LE NR 3,  ACFT INSPECTED IAW AMM 05-50-26. IMPACT DAMAGE CONCENTRATED	 AT RT NR 3 LE.  RT NR 3 LE REPLACED IAW AMM, LEAK AND FUNCTION CHECKED.  SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		EA  	2008	12	30	CA081114008      	1	20081113	G	5714		FASTENER        			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING BOX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5636 								(CAN) DURING INSP, THERE WAS SEVERAL CHERRY MAX RIVETS FOUND TO BE LOOSE ON THE UNDERSIDE OF THE RT WING BETWEEN STATION	 35.15 AND 97.50. THE RIVETS WERE ALL LOCATED ON A TRIPLE ROW OF RIVETS AT THE AFT SPAR. FURTHER INSPECTION REVEALED A T	OTAL OF 160 RIVETS NEEDING REPLACEMENT. THE RIVETS WERE REPLACED AND THE ACFT RETURNED TO SERVICE.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20081230		NM  	2008	12	30	CA081114009      	1	20081112	G	5310		STRUCTURE       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUSELAGE	DAMAGED         	W				O				OTHER                   				C			F.O.D.                    			DE	DESCENT        	1			CA											(CAN) FLT ENCOUNTERED MULTIPLE BIRD STRIKES AT 4000 FT, DURING AN APPROACH FOR LANDING INTO AIRPORT. CREW CONTINUED ON D	ESCENT PATH AND LANDING UNEVENTFUL. MX REQUESTED. SUBSTANTIAL DAMAGE TO THE RT SIDE OF RADOME AND STRUCTURE IMMEDIATELY 	BEHIND RADOME FROM IMPACT OF GOOSE. ALSO EVIDENCE OF ANOTHER GOOSE HAVING STRUCK THE LT SIDE OF ACFT. POINT OF IMPACT BE	ING JUST ABOVE LT ENGINE INTAKE. GOOSE HAD SUBSEQUENTLY ENTERED INTAKE AND EXITED THROUGH THE OPEN ENG INTAKE BYPASS DOO	R THAT WAS DAMAGED AS WELL.  ACFT INSPECTED IN AIRPORT. RADOME REPLACED AND ACFT WAS THEN FERRIED TO MX BASE, UNDER A FE	RRY FLT PERMIT. RADOME REMOVED AGAIN TO FACILITATE REPAIRS TO BULKHEAD ON NOSE BEHIND RADOME. WEATHER RADAR ALSO REPLACE	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230			2008	12	30	CA081115001      	4	20081112	G	2312	G340ENI	CONTROL HEAD    			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	COCKPIT	CONTAMINATED    	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) DURING APPROACH COM BECAME TEMPORARILY UNUSABLE DUE TO WATER CONTAMINATION IN COMM CONTROL HEAD. PART REMOVED AND 	DRIED OUT AND FUNCTION TESTED SERV, NO FURTHER PROBLEMS.					2	L	7	2 	4R	4	T		6A6     	E282	6	C	P898	 
	20081230		EA  	2008	12	30	CA081117002      	1	20081114	G	2750	865D1007	DRIVE SYSTEM    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) FLAP FAIL MESSAGE AFTER SELECTING FLAP, FLAPS FAILED AT 8 DEGREES.  ACFT LANDED SAFELY WITH FLAPS AT 8 DEGREES.   	REPLACED PDU, COMPLETED FLAP TORQUE CHECK, CHECKED FOR ACTUATOR OVER TEMP IAW AMM 27-52-01-000-8001 AND AMM 27-53-00-750	-802. FLAP SYS CHECKS SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081230		SW  	2008	12	30	CA081117003      	1	20081113	G	8012	31057463	IGNITION SWITCH 			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE3311     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ACFT DEPARTED AIRPORT AND CREW NOTICED SMOKE IN THE CABIN. THE CREW TURNED THE TEMP CONTROLLER OFF - THE BLEEDS WE	RE TURNED OFF WHICH DUMPED THE CABIN PRESSURIZATION.  THE LOW OIL PRESSURE LIGHT CAME ON ALONG WITH THE EGT STARTING TO 	RISE.  ENGINE WAS THEN SHUTDOWN AND FEATHERED AT THIS POINT. ACFT RETURNED TO POINT OF ORIGIN AND LANDED WITHOUT INCIDEN	T. MX WAS CONTACTED AND THEY DISCOVERED THE AUTO IGNITION SWITCH WAS CRACKED ALLOWING THE ENGINE OIL TO BLEED OUT OF THE	 ENGINE. THE SWITCH WAS REPLACED - GROUND RUNS CARRIED OUT IAW EMM AND ACFT RETURNED TO SERVICE.		2	L	7	2 	4T	3	T	RT	A8SW    	E3WE	6	C	3PNE	 
	20081230		EU  	2008	12	30	CA081117004      	1	20081114	G	6700	ASNA013735E2	BEARING RACE    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					INNER R ACE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A 12 YEAR INSP WAS BEING CARRIED OUT ON THE HELICOPTER.  2 CRACKS WERE FOUND ON THE INNER RACE OF A BALL BEARING A	SSY. THE CRACKS ORIGNALLY STARTED FROM THE RIVET HOLES. THE BEARING ASSY/SUPPORT ATTACH THE INNER RACE OF BEARING BY 4 R	IVETS TO THE PILOT`S CYCLIC FOR AND AFT TORQUE TUBE LOCATED UNDER THE CABIN FLOOR. THIS IS THE SECOND 12 YEAR INSPECTION	 FOR THIS HELICOPTER.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081230			2008	12	30	CA081117005      	4	20081113	G	2210	103791101	CIRCUIT BOARD   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT642A      		NE  	HARTZL	HCE4N	HCE4N3      	NE  	AUTOPILOT	INTERMITTENT    	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CL	CLIMB          	1			CA				428  							(CAN) ACFT IN NORMAL CLIMB CONFIGURATION WITH FCS DISPLAYING CLIMB (GREEN) AND ALT ARM (WHITE.) THE VERTICAL MODE DISPLA	Y MAY THEN CHANGE TO ALT (GREEN) EVEN THOUGH THE TARGET ALTITUDE IS SEVERAL THOUSAND FT ABOVE (E.G. WITH THE ALT SELECT 	SET FOR 20,000 FEET, THRU, SAY, 12,000 FT THE VERTICAL MODE WILL CHANGE FROM CLIMB TO ALT) WITH THE VERTICAL MODE IN ALT	 AND STILL SEVERAL THOUSAND FT BELOW SELECTED ALTITUDE THE ACFT WILL BEGINNING PITCHING UP SEVERAL DEGRESS (+10 DEGREES 	OR HIGHER) REQUIRING AUTOPILOT DISCONNECT, RESET AND MONITORING BY THE PILOT. ALTITUDE ALERTER REMOVED FOR INSP.   INTER	NAL PRINTED CIRCUIT BOARD IDENTIFIED AS THE PROBLEM SOURCE AND SUBSEQUENTLY REPLACED.	1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P10NE	 
	20081230		EA  	2008	12	30	CA081117006      	1	20080926	G	7160	CT2EC10221	YOKE            			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	INTAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSP, THE YOKE LT INTAKE COWL BROKE AT MACHINED LOCKING TAB EAR CUT OUT UPON INSTALLATION WHILE 	RIVETING, LT YOKE-INTAKE COWL WAS REPLACED.					1	H	7	1 	3T	4	T		A806    	E4EA	6	C	P15EA	 
	20081230		SO  	2008	12	30	CA081117007      	2	20081115	G	8530		CYLINDER        								CONT  	O300  	O300C       	17022	SO  					NR 3	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NR 3 CYLINDER ASSY WAS FOUND CRACKED BETWEEN THE CYLINDER HEAD AND THE BARREL, APPROX .7500 AROUND THE CICUMFERENC	E OF THE ASSY. THIS RESULTED IN LOSS OF COMPRESSION AND ENGINE VIBRATION.										3	O			E253				 
	20081230		CE  	2008	12	30	CA081118001      	1	20081115	G	3040	MS24166DI	RELAY           	BEECH       		BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	WINDSHIELD HEAT	UNSERVICEABLE   	W				H				DEACTIVATE SYST/CIRCUITS				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) CREW DEFECT PILOT WINDSHIELD HEAT NOT WORKING, TROUBLESHOOT TO LOW HEAT RELAY, TERMINAL A2 MELTED OFF THE RELAY AS	SY, DAMAGING WIRES ATTACHED TO THE TERMINAL APPROX 3 INCHES BACK THE WIRE COVER MELTED OFF. RELAY WAS REPLACED AND SYS O	PERATES PROPERLY.				2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
	20081230		SW  	2008	12	30	CA081118003      	1	20081103	G	7603	701981	LOCK TAB        	AIRTRC      		AIRTRC	AT500 	AT502B      	0390307	SW  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	POWER LEVER	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			4325 								(CAN) FCU FUEL CONDITION LEVER LOCK SPRING TAB THAT IS USED TO PREVENT THE LEVER MOVING TO FUEL CUT-OFF HAS FAILED.						1	L	7	1 	3T	4	T	NC	A17SW   	E4EA	6	C	P15EA	 
	20081230		NM  	2008	12	30	CA081118004      	1	20081116	G	2910	82970009325	LINE            			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 HYD SYS	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			24324								(CAN) ON DESCENT AT NIGHT IN HEAVY RAIN, FLIGHT CREW GOT NR 2 HYD PUMP CAUTION FOLLOWED BY TOTAL LOSS OF QUANTITY IN NR 	2 HYD SYS.  LEVELED AT F110 FOLLOWED QRH, DECLARED PAN, BRIEFED F/A AND PASSENGERS ON RETURN TO BASE FOR NORMAL LANDING 	WITH PRECAUTIONARY SERVICES IN ATTENDANCE. LINE MAINT INVESTIGATION AND CONFIRMED DEFECT, TRACED LEAK TO `RIGID LINE` P/	N  82970009-325. WALL OF LINE FOUND CRACKED ADJACENT TO AN END FITTING. RIGID LINE REPLACED WITH NEW ITEM. AS ENGINE DRI	VEN HYD PUMP WAS RUN IN FLIGHT FOR LONGER THAN FIFTEEN MINUTES, IT WAS ALSO REPLACED AS REQUIRED BY ACFT MANUAL. ALL SYS	 FUNCTIONED IAW THE AIRCRAFT`S MM.  THE ACFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		GL  	2008	12	30	CA081118005      	1	20081117	G	2720		TUBE            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	RUDDER PEDAL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4521 								(CAN) INSP OF THE RUDDER PEDAL ASSY REVEALED EXCESSIVE WEAR ON THE S TUBE CAUSED BY WEAR FROM THE RUBBER CABLE. THE WEAR	 WAS DETECTED BY VISUALLY CHECKING THE OUTSIDE OF THE S TUBE FOR MATERIAL DEFORMATION IN THE AREA WHERE THE CABLE CAUSES	 THE MOST FRICTION ON THE INSIDE OF THE TUBE. THE RUDDER PEDAL ASSY AND CABLE WERE REPLACED WITH NEW.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081230		NM  	2008	12	30	CA081118006      	1	20081114	G	3220	82253	TUBE            	MESSIER     	8200103     	DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON SELECTING LANDING GEAR DOWN-PILOT REPORTED A LOUD CRACKING NOISE FROM THE NLG AREA. COULD NOT CONFIRM THAT THE 	GEAR WAS DOWN AND LOCKED USING NORMAL OR ALTERNATE VERIFICATIONS. AN EMERGENCY LANDING WAS MADE SUCCESSFULLY AFTER A FLY	BY INSP SHOWED THAT THE NLG WAS EXTENDED.  ACFT MADE A SUCCESSFUL LANDING AND WAS SECURED ON NOSE JACK INSPECTED . INSP 	REVEALED THAT THE PIVOT TUBE HAD CRACKED AND THAT THE DOWN LOCK HAD NOT GONE FULLY OVERCENTER. PART REPLACED AND ACFT WA	S REMOVED OFF THE RUNWAY. AN PHYSICAL INSP OF THE PIVOT TUBE REVEALED THAT THIS WAS A PRE-MOD PIVOT TUBE AND NOT IAW AD 	CF-95-15. MFG`S ARE INVESTIGATING THE EVENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		CE  	2008	12	30	CA081118008      	1	20081115	G	3310	1015245001	PANEL           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			14882	14882							(CAN) ACFT RETURNED SHORTLY AFTER DEPARTURE DUE TO AN ELECTRICAL ODOR AND A WISP OF SMOKE AT THE CO-PILOTS CONTROL WHEEL	. IT LASTED FOR A FEW SECONDS AND THEN DISAPPEARED. MX INSPECTED THE ACFT UPON ARRIVAL AND FOUND THAT THE EDGE-LIGHTED P	ANEL AT THE CO-PILOTS CLOCK WAS AT FAULT. THE LIGHTING WAS DISABLED AND DEFERRED IAW THE MEL UNTIL REPLACEMENT PARTS ARR	IVE. THE AREA WAS INSPECTED AND ADJACENT SYS TESTED WITH NO ADDITIONAL FAULTS NOTED AND THE ACFT RELEASED.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
	20081230		SW  	2008	12	30	CA081118010      	1	20081118	G	7120	5082119	MOUNT           			AIRTRC	AT602 	AT602       	0390309	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2498 								(CAN) DURING THE 300HR/ANNUAL INSP,  ENGINE MOUNT WAS BEING INSPECTED IAW AD2008-10-12 AND AIR TRACTOR`S SL NR 253C, A C	RACK WAS FOUND ON THE LT LOWER ENGINE ATTACH POINT VIA 10X MAGNIFYING GLASS.  ACFT HAS BEEN NOTIFIED ABOUT THE CRACK AND	 A NEW ENGINE MOUNT HAS BEEN SINCE INSTALLED WITH THE GUSSET UPGRADE IAW AD2008-10-12 AND SL NR 253C WHICH WAS SUPPLIED 	BY THE MFG.			1	L	7	1 	3T	4	T	NC	A19SW   	E4EA	6	C	P44GL	 
	20081230		NM  	2008	12	30	CA081119001      	1	20081119	G	5330		SKIN            			EMB   	ERJ170	ERJ170100SE 	3260406	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS WERE SUSPECTED AFTER GVI AND CONFIRM BY NDT RADIATING FROM ONE FASTENER HOLE IN LT FUSELAGE SKIN PANEL AT F	RAME 94 STR 03 AND 04 LT AND SAME AT FRAME 94 STR 03 AND 04 RT.					2	L	7	2 	4F			RT	A56NM   					 
	20081230		EA  	2008	12	30	CA081119002      	1	20081118	G	2751	800440304	PROXIMITY SENSOR			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) FLIGHT WAS SET UP FOR LANDING AND SELECTED FLAPS TO 8 DEGREES. FLAPS ON 1 SIDE CAME DOWN TO 2 DEGREES AND FLAPS ON	 THE OTHER SIDE REMAINED AT 0 DEGREES. AN EMERGENCY WAS DECLARED AND PASSENGERS WERE BRIEFED. FLIGHT LANDED WITHOUT FURT	HER INCIDENT AND STOPPED ON RUNWAY FOR FIRE CREWS TO DO A WALK AROUND AND THEN TAXIED TO THE GATE. MX TROUBLESHOOTING IA	W FAULT CODES AND SKEW DETECTOR INDICATION LED TO REPLACEMENT OF THE LT L3 (P/N 8044-04, S/N 2676) AND L4 (P/N 80-044-03	, S/N 2676) SKEW DETECTOR PROXIMITY SENSORS. FLAP OPERATION AND SKEW DETECTOR SYS OPS CHECKS CARRIED OUT WITH NO FURTHER	 FAULTS AND THE ACFT WAS RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081230		NE  	2008	12	30	CA081119003      	2	20081118	G	7261	0292507350	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	BLOCKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3412 	660  							(CAN) OIL WAS COMING OUT OF TURBINE EXHAUST AND M03 BEARING VENT TUBE ON START UP. DISASSEMBLED THE ENGINE AND FOUND M03	 REAR BEARING CAKED WITH BURNED OIL. M03 REAR BEARING OIL RETURN TUBE PARTIALLY BLOCKED WITH BURNED OIL.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081230		NM  	2008	12	30	CA081119004      	1	20081118	G	2750	MS391130Z	MOTOR           			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) ENROUTE, SYS A HYD QTY DROPPED TO ZERO.  MX FOUND OTBD FLAP HYD MOTOR FAILED.  MOTOR REPLACED AND SYS CHECKED SERV	ICABLE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081230		EU  	2008	12	30	CA081120001      	1	20081119	G	2560	SL12	BUCKLE          	GROB        		GROB  	G115  	G115C       	1660303	EU  	LYC   	O320  	O320D1A     	41508	EA  					SEAT BELT ASSY	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			437  								(CAN) BUCKLE WOULD NOT RELEASE.						1	L	7	1 	3O	3	O	NT	A57EU   	E274				 
	20081230		CE  	2008	12	30	CA081120002      	1	20081118	G	2840		MONITOR         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	FUEL QTY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORT ERRATIC ON FUEL QTY INDICATION. TROUBLESHOOTING REVEALED FAULTY CONTROL MONITOR.  MONITOR REPLACED BY	 REPAIRED UNIT THAT FAILED 2 DAYS LATER, REPLACED WITH OTHER ONE FROM SAME VENDOR THAT DOESN`T WORK, SWAPPED WITH AN SER	VICEABLE UNIT FROM AN OTHER ACFT (FLTS) TO CONFIRMED TROUBLESHOOTING. IT TAKES 3 DIFFERENT UNIT TO FINALLY FIXED THE PRO	BLEM.			1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	3PNE	 
	20081230		NM  	2008	12	30	CA081120003      	1	20081107	G	3240	900005831PR	BRAKE SYS       			EMB   	ERJ170	ERJ170200SU 	NIR    	NM  	GE    	CF34  	CF348E5A1   	30062	NE  					MLG	DISINTEGRATED   	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PUSHBACK, GRND PERSONNEL REPORTED SMOKING BRAKES. FOUND NR3 BRAKE ROTORS HAD FAILED. REPLACED BOTH NR3 WHEE	L AND BRAKE ASSY IAW AMM 32-49-05 AND 32-49-11.  S/N OF THE BRAKE IS JAN05-0530.					2	L	7	2 	4F	4	F	RT	A56NM   	E00063EN				 
	20081230		SW  	2008	12	30	CA081120004      	1	20081116	G	6220	K974004107	MOUNT           			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					M/R HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DISCOVERED ON LT FWD STRUT MOUNT FITTING.						1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
	20090102		NE  	2009	1	2	CA081120005      	2	20081106	G	7532	BRH10211	BLEED VALVE     			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IT HAS BEEN REPORTED BY OPERATOR THAT BVV LEVER WAS NOT OPERATING PROPERLY. ENG WAS REMOVED IN UNSERVICEABLE CONDI	TION DUE TO BOOSTER BLEED VALVE MECHANISM MALFUNCTION.  ENG IN RRC FOR REPAIR.  DURING INITIAL INSP, IT WAS CONFIRMED TH	AT BOOSTER BLEED VALVE RING ASSY (ATA 72-38-19 01-400) WAS NOT OPERATING PROPERLY. STRIP WAS CARRIED OUT TO EXPOSE THE B	OOSTER BLEED VALVE MECHANISM AND IT WAS NOTED THAT ONE PIN (ATA 72-38-19 01-408) AND ONE RETAINING RING (ATA 72-38-19 01	-409) WERE MISSING. THIS PIN IS AT THE CONNECTION BETWEEN THE BELL CRANK LEVER ASSY (ATA 72-38-19 01-100) AND THE BOOSTE	R BLEED VALVE RING ASSY (ATA 72-38-19 01-409) AT TOP DEAD CENTER POSITION (ACTUATING ROD POSITION).  (6) REMAINING PINS 	2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
	20081230		EU  	2008	12	30	CA081120006      	1	20081119	G	6220	350A37116200	STOP            			SNIAS 	350   	AS350B2     	8680813	EU  	LYC   	LTS101	LTS101*     		NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2834 								(CAN) CRACK DISCOVERED ON 2 OF THE 3 YOKE, STOP, ASSYS REMOVED FROM THE ACFT DURING NDT. THE CRACKS ARE ALLONG THE SECON	D RADIUS FROM THE TOP, AND WERE NOT VISIBLE TO THE NAKED EYE.					1	G	7	1 	3U	3	U		H9EU    	E5NE				 
	20081230		EU  	2008	12	30	CA081120007      	1	20081119	G	6220	350A37116200	STOP            	SNIAS       		SNIAS 	350   	AS350B1     	8680811	EU  										ROTOR SHAFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10002								(CAN) CRACK DETECTED IN 2 OF THE 3 YOKE, STOP, ASSYS ON THE MAST. FOUND DURING A 6 YEAR CORROSION INSPECTION OF THE MAST	. THE PARTS WERE SENT FOR NDT AS PART OF THE AVIATION INSP PROCEDURES FOR THE MAST ASSY (NO MFG REQUIREMENT IN THE TECHN	ICAL PUBLICATIONS TO NDT THESE PARTS). CRACK NOTED IN THE SECOND RADIUS FROM THE TOP.				1	G	7	1 	3U				H9EU    					 
	20081230			2008	12	30	CA081121001      	4	20081120	G	3420	7004544314	SYMBOL GENERATOR			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	NR 1	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			30171	458  							(CAN) SHORTLY AFTER TAKEOFF, THE CAPT`S PRIMARY FLIGHT DISPLAYS WERE MALFUNCTIONING, CAPTS EADI AND EHSI ARE BLANKING OU	T INTERMITTENTLY , CREW ELECTED TO RETURN TO ORIGINATING AIRPORT.  MX REPLACED NR 1 SYMBOL GENERATOR AND ACFT RETURNED T	O SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		EA  	2008	12	30	CA081121002      	1	20081120	G	2750	855D1009	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	FAILED          	W				D				RETURN TO BLOCK         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			27770	27770							(CAN) DURING PUSH BACK FROM THE GATE, FLAP LEVER WAS MOVED TO 8 DEGREES BY THE FLIGHT CREW BUT THE FLAP DIDN`T EXTEND AN	D "FLAP FAIL" CAUTION MESSAGE APPEARED ON THE ENGINE INDICATION AND CREW ALERTING SYS (EICAS). THE ACFT WAS TOWED BACK T	O THE GATE. FLAP ELECTRONIC CONTROL UNIT (FECU) FAULT CODES WERE RETRIEVED AND DECISION WAS MADE TO REPLACE THE RT BRAKE	 POSITION SENSOR UNIT (BPSU). THE UNIT WAS REPLACED AND THE ACFT RETURNED INTO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081230		NM  	2008	12	30	CA081121003      	1	20081119	G	2150	8209063	ACM             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RIGHT	ODOR            	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) IN CRUISE F/A CALLED TO REPORT SMELL AND MIST. ASKED FOR AN UPDATE IF IT WORSENED, THEN PREPARED FOR OXYGEN DRILL 	IAW QRH. ON APPROACH TO LAND THE (CABIN PACK HOT CAUTION) LIGHT CAME ON. THE QRH WAS CONSULTED AGAIN AND THEN THE CAUTIO	N LIGHT WENT OUT. WE THEN LANDED AND COMPLETED THE FLIGHT NORMALLY.  ON-SITE LINE MX INVESTIGATION IDENTIFIED THE RT (CA	BIN) AIR CYCLE MACHINE (ACM) TO BE NON-OPERATIONAL DUE BEING SEIZED. FUNCTIONAL CHECK AIR CONDITIONING SYS SATISFACTORY 	WITH FLIGHT COMPARTMENT PACK ONLY WITH TEMP COMTROL AT 1 O`CLOCK POSITION. ACFT POSITIONED BACK TO MX BASE UNDER MEL 21-	50-1PROVISIONS. ACM REPLACED AND TESTED IAW THE MM 21-51-21. ACFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081230		EU  	2008	12	30	CA081121004      	1	20081121	G	5751		SEAL            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT AILERON	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7654 	7654 							(CAN) THE AILERONS WERE REMOVED AT THE ANNUAL INSP FOR BEARING REPLACEMENT. A SMALL RIP WAS FOUND IN THE INNER SEAL OF T	HE LT AILERON WHICH ATTACHES BETWEEN THE WING AND THE AILERON BALANCE WEIGHT ATTACHMENT. WHEN THE MS35207-XXX SCREWS WER	E REMOVED THE WERE FOUND TO BE CORRODED. THE AREA WAS INSPECTED FOR CORROSION CLEANED AND NEW SCREWS INSTALLED WITH CPC 	GRADE 2 COMPOUND. THE RT AILERON WAS INSPECTED AND FOUND WITH SIMILAR CORROSION.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20081230		CE  	2008	12	30	CA081121005      	1	20081119	G	2435	23080023A	STARTER GEN     			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE73123B   	 	WP  					NR 1	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA				235  							(CAN) GENERATOR FELL OFF, INE AND A SLIGHT VIBRATION WAS FELT.						2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
	20081230		GL  	2008	12	30	CA081121006      	1	20081120	G	2720	2227271200	TUBE            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	RUDDER PEDAL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2794 								(CAN) DURING THE ACFT PRE-FLIGHT THE PILOT REPORTED THAT THE RUDDER PEDAL ASSY ON THE RT SIDE WAS DIFFICULT TO ADJUST AL	ONG THE SLIDE TUBE ASSY. CLOSER INSPECTION BY MAINT REVEALED THAT THE RT OTBD FWD RUDDER CABLE HAD WORN THROUGH THE S-TU	BE THAT IS WELDED TO THE PEDAL ASSY.  CABLE WAS EXPOSED THROUGH THE LOWER BEND OF THE S-TUBE TO A POINT WHERE IT WAS JAM	MED IN ITS WEAR HOLE THUS RESRICTING THE SLIDE ACTION OF THE PEDAL ASSY. THE DEFECTIVE PARTS ARE BEING REMOVED FOR REPLA	CEMENT WITH NEW.		1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081230		GL  	2008	12	30	CA081121007      	1	20081107	G	2910	1005354226007	LINE            			BOMBDR	BD100 	BD1001A10   	1390044	GL  										HYDRAULIC SYS	CHAFED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA			5443 								(CAN) ACFT LOST ALL HYD FLUID IN THE RT SYS DURING FLIGHT. NO INFO ON FLIGHT PROFILE, CAS MESSAGES OR QTY`S NOTED.  CREW	 UNAVAILABLE FOR DEBRIEF AT THIS TIME. REPLACED AFFECTED LINE, CLAMP AND HARDWARE.					2	L	7	2 	4F			RT	T00005NY					 
	20081230		GL  	2008	12	30	CA081121009      	1	20080711	G	2910	1005354226007	LINE            			BOMBDR	BD100 	BD1001A10   	1390044	GL  										HYDRAULIC SYS	CHAFED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			5162 								(CAN) DURING CRUISE FLIGHT, THE AMBER (R HYD PRESS LOW) CAS MESSAGE ILLUMINATED. PILOT OBSERVED THE HYD SYNOPTIC PAGE AN	D NOTED THE FLUID LEVEL IN THE RT HYD RESERVOIR BEGAN DROPPING. ACFT BEGAN DESCENT. DURING APPROACH, PILOT NOTED THE RT 	HYD RESERVOIR QUANTITY WAS READING (4 PERCENT). AFTER LANDING, VISUAL INSP OF THE ACFT REVEALED HYD FLUID STREAMING FROM	 THE WHEEL WELL AREA TO THE TAIL OF THE ACFT.  FOUND LINE IN THE AFT EQUIPMENT BAY HAD A HOLE CHAFED INTO IT BY A FAIRLE	AD BLOCK.		2	L	7	2 	4F			RT	T00005NY					 
	20081230			2008	12	30	CA081121010      	1	20081119	G	3411	20131421B	STATIC LINE     																	PITOT/STATIC SY	UNBONDED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FITTING GLUE AND LINE GOING TO IT IS ALUMINUM WITH A COMPRESSION FITTING WHEN LINE WAS TIGHTEN TO ENSURE NO STATIC	 LEAK THE GLUE THAT ADHEARS THE FITTING LET GO THIS SUBMITTED ON BEHALF OF SKYLINE MAINT AND AVIONICS AMO 21-80.																		 
	20081230		NM  	2008	12	30	CA081121011      	1	20081120	G	3230	656021132	ACCESSORY UNIT  			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) JUST AFTER TAKEOFF, THE CREW ATTEMPTED TO SELECT GEAR UP, THE GEAR HANDLE WOULD NOT GO PAST THE OFF POSITION.  ACF	T RETURNED TO WHERE MAINT REPLACED THE LANDING GEAR ACCY UNIT. A/C RETURNED TO SERVICE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081230		EU  	2008	12	30	CA081121012      	1	20081120	G	2913	S40	COUPLING SLEEVE 			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					HYD PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING DISASSEMBLY FOR OTHER WORK THE HYD PUMP WAS REMOVED AND THE SPLINE DRIVE WAS FOUND EXTREMELY WORN. PART S40	 WAS FOUND TO HAVE ALMOST NO SPLINE AT ALL REMAINING AND THE JOINING HYD PUMP PN A5026780 HAD IT`S SPLINES WORN TO HALF 	THEIR NORMAL WIDTH. THERE IS ALREADY AN AD CF2004-10 AND AN SB 29.00.04 ON THIS ISSUE. ESTIMATED TIME TO FAILURE OF HYD 	DRIVE WAS LESS THAT 100 HOURS.			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20081230		NM  	2008	12	30	CA081122001      	1	20080929	G	5312		BULKHEAD        			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING WALK-AROUND INSP, FOUND BELTFRAME AT 9G BULKHEAD CRACKED BY LT CARGO CAN CUTOUT. TEMPORARY REPAIR CARRIED O	UT. A/C FERRIED. PERMANENT REPAIR CARRIED OUT.  ACFT RETURNED TO SERVICE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081230		EA  	2008	12	30	CA081122002      	1	20081117	G	2752	852D10021	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  										TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			2078 								(CAN) FLAP FAIL IN APPROACH WHEN SELECTED FROM 0 DEGREE. FLAP FAILED AT 0 DEGREE.						2	L	7	2 	4F			RT	A21EA   					 
	20081230		EA  	2008	12	30	CA081122003      	1	20081117	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  										TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) DECENDING THROUGHT 10,000 FT, FLT CREW REPORTED FLAP FAIL MSG WITH FLAPS AT 0 DEG, AIRSPEED WAS 250 KTS.  QRH FOLL	OWED AND ACFT LANDED WITHOUT FURTHER INCIDENT.  COMPLIED WITH FLAP RESET IAW SUPPLEMENT 98-018B (CB RESET) AND FLAPS OPS	 CHECKED NORMAL. ACFT RETURNED TO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
	20081230		EA  	2008	12	30	CA081122004      	1	20081116	G	2742	AV67023105	ACTUATOR        			CNDAIR	CL600 	CL6002C10   	1390015	EA  										HORIZONTAL STAB	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AV670-23105-003 (LT) AND -004 (RT)  DURING ROUTINE MX ON THE HORIZONTAL STAB TRIM ACTUATOR (HSTA), LOOSE BOLTS (IT	EMS 24 AND 35) WERE FOUND IN THE UPPER BOLT LOCATIONS OF THE RT AND LT HSTA UPPER ATTACHMENT FITTING ASSY ITEM 33).					2	L	7	2 	4F			RT	A21EA   					 
	20081230		EA  	2008	12	30	CA081122005      	1	20081111	G	2120		UNKNOWN         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  						SMOKE           	W				C				ABORTED TAKEOFF         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) "A08C0232: AS FLIGHT WAS ON THE TAKEOFF RUN, WHEN THE CREW RECEIVED A CAUTION MESSAGE FOR SMOKE IN THE LAVATORY. T	HE TAKEOFF WAS REJECTED AT 60 KTS AND ARFF WAS CALLED OUT. THE FLIGHT RETURNED TO THE APRON, PASSENGERS WERE DEPLANED, A	ND MX INSPECTED THE AIR CONDITIONING PACKS AND THE ACFT WAS RETURNED TO SERVICE. AFTER DE-ICING AGAIN, ANOTHER TAKEOFF W	AS ATTEMPTED, BUT WAS REJECTED AT 100 KTS WHEN THE SMOKE IN THE LAVATORY CAUTION MESSAGE OCCURRED AGAIN. THE ACFT WAS IN	SPECTED AND FERRIED, WHERE MX IS CHANGING THE RT ENGINE (GE CF34-3B1).		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081230		EA  	2008	12	30	CA081122006      	1	20081110	G	5610	NP13922001	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) F/O SIDE WINDOW IS CRACKED. INNER PLY. ALSO SMALL SLIVER FROM RT WINDOW HAS CHIPPED OFF APPROX  2 INCHES BY .25 IN	CH AT THE WINDOW EDGE. CALLED TO VERIFY THE CRACKED PLY.  ACFT TO FERRY UNPRESSURIZED FOR REPAIRS".					2	L	7	2 	4F			RT	A21EA   					 
	20081230		WP  	2008	12	30	CA081124001      	1	20081006	G	3246		BUNGEE          	FEDERAL     		DOUG  	DC3   	DC3CS4C4G   	3021460	WP  	PWA   	PT6   	PT6A67R     	52043	NE  					SKI	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING AERIAL WORK WITH SKIS INSTALLED THE RT MAIN GEAR DID NOT EXTEND FULLY. WITH THE ASSISTANCE OF A BELLY MOUNT	ED CAMERA THE CAUSE WAS DETERMINED TO BE THE SKI FWD LIMIT CABLE ASSY. THE LANDING GEAR WAS CYCLED AND EXTENDED SUCCESSF	ULLY. BOTH LT AND RT SKI FWD LIMIT CABLE ASSEMBLIES WERE REPLACED. THE ENSUING INVESTIGATION DETERMINED THAT THE BUNGEE 	ASSEMBLIES ON THE FWD LIMIT CABLE ASSEMBLIES WERE TOO LONG ALLOWING THE CABLE TO HOOK ITSELF UNDER THE SKI PIVOT BOLT NO	T ALLOWING THE LANDING GEAR TO EXTEND FULLY. THE PROPER LENGTH BUNGEE WOULD NOT ALLOW THE CABLES TO BE LOCATED IN THAT A	REA. THE ORIGINALLY INSTALLED BUNGEE ASSEMBLIES WERE UNITS SUPPLIED BY THE ACFT STC HOLDER, WHO HAS BEEN NOTIFIED OF THE	2	L	7	2 	4R	4	T		A669    	E26NE				 
	20081230		EA  	2008	12	30	CA081124002      	1	20081123	G	2497	D3899920MJ43SN	CONNECTOR       			CNDAIR	CL600 	CL6002D24   	1390016	EA  											BURNED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) AT APPROX 1540Z AT 15000 FT 220 KIAS AS THE PF WAS CHECKING THAT THE PITCH DISCONNECT SYS WAS RE-ENGAGED. A LOUD N	OISE WAS HEARD IN THE COCKPIT, AT THE SAME TIME THE PILOTS WINDSHIELD WIPER MOVED .2500 DISPLACEMENT AND THE A/SKID INBD	, INBD BRAKE BRESS AND OB BRAKE PRESS CAUTION MESSAGES POSTED. MDC WAS CHECKED FOR FAULTS AND INDICATED TRU 1, ESS TRU 1	 AND A/SKID INBD HAD FAILED. CB`S CHECKED, 1B5 TRU 1, 1G4 ANTI-SKID, 1G5 WIPER PILOT, 1G10 MAINT LIGHT, 1T2 ESS TRU 1, A	ND 2G3 BRAKE PRESS IND FOUND TO BE POPPED. DUE TO ELECTRICAL FAILURE AND NO INDICATIONS OF BRAKE PRESSURE, EMERGENCY DEC	LARED AND EMERGENCY VEHICLES REQUESTED FOR LANDING. AFTER LDG, ACPC CB`S FOR HYD PUMP 1B, 2B, 3A POPPED.	2	L	7	2 	4F			RT	A21EA   					 
	20081230		SW  	2008	12	30	CA081124003      	1	20081121	G	3260	MS243314	SWITCH          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF CREW WAS UNABLE TO RETRACT THE ACFT LANDING GEAR. THE CREW ELECTED TO RETURN TO AIRPORT OF ORIGIN AN	D CONTACT MX. THE ACFT WAS FERRIED HOME WITH THE GEAR DOWN.  UPON INSP FROM MX, THE MLG SAFETY SWITCH WHICH CONTROLS THE	 AIR/GROUND PORTION OF THE LANDING CONTROL SYS WAS FOUND TO BE INOPERATIVE. MX CHANGED THE SWITCH AND THE GEAR FUNCTIONE	D CHECKED SERVICEABLE.  TOTAL TIME ON THE SWITCH COULD NOT BE DETERMINED.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081230		SW  	2008	12	30	CA081124004      	1	20081117	G	3260	MS243314	SWITCH          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110U   	29066	NE  	HARTZL	HCE4N	HCE4N3      	NE  	INTERNAL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ATTEMPTED ENGINE START THE CREW WAS UNABLE TO GET ENGINE ROTATION OR LIGHT OFF. MX INVESTIGATED AND DETE	RMINED THE MLG SAFETY MICROSWITCH WHICH CONTROLS THE AIR/GROUND PORTION OF THE ENGINE START CONTROL SYS TO BE INOPERATIV	E. MX REPLACED THE SWITCH AND RETURNED THE ACFT TO SERVICE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081230		SW  	2008	12	30	CA081124005      	1	20081120	G	3260	1EN516	SWITCH          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	NLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) THE CREW COULD NOT GET A NOSE GEAR DOWN AND LOCKED INDICATION AFTER SEVERAL DOZEN GEAR POSITION CYCLES OR WITH MAN	UAL GEAR EXTENSION. WITH THE LAST ATTEMPT IT ILLUMINATED WITH ELECTRICAL SELECTION. EMERGENCY SERVICES AT AIRPORT WERE O	N STANDBY.  THE ACFT LANDED AND MX DISCOVERED THAT ONE OR BOTH OF THE NOSE LANDING GEAR DOWNLOCK SWITCHES WAS INOPERATIV	E. MX REPLACED BOTH SWITCHES AS A PRECAUTION AND GEAR FUNCTIONAL CHECKS COMPLETED. NO FURTHER PROBLEMS WITH THE LANDING 	GEAR SYS HAVE OCCURED.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081230		SW  	2008	12	30	CA081124006      	1	20081121	G	3260	1EN516	SWITCH          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	NLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO LAND THE FLIGHT CREW COULD NOT GET THE GREEN DOWN AND LOCKED LIGHT FOR THE NLG TO ILLUMINATE. THE G	EAR WAS CYCLES SEVERAL TIMES AND THE EMERGENCY GEAR EXTENSION USED. AFTER SEVERAL MINUTES THE NOSE GEAR DOWN AND LOCKED 	GREEN LIGHT ILLUMINATED AND THE ACFT LANDED WITHOUT FURTHER INCEDENT.  MX TRACED THE PROBLEM TO A INOPERATIVE NOSE LANDI	NG GEAR DOWNLOCK MICRO SWITCH. BOTH DOWNLOCK MICROSWITCHES WERE REPLACED AS A PRECAUTION AND THE LANDING GEAR FUNCTION T	ESTED. THERE HAS BEEN NO FURTHER RECURRANCE OF THIS ISSUE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
	20081230		NM  	2008	12	30	CA081124007      	1	20081121	G	5751		SUPPORT BRACKET 			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING HEAVY CHECK INSPECTION FOR ACFT (316), BOTH THE LT AND RT AILERON INPUT QUADRANT SUPPORT BRACKET ASSEMBLIES	, ON BOTH THE INBD AND OTBD SIDES, WERE FOUND TO HAVE SIGNIFICANT CRACKING.   FLEET CAMPAIGN HAS BEEN INITIATED TO INSPE	CT THE AFOREMENTIONED ASSEMBLIES ON THE DHC8-300 SERIES ACFT. REFERENCE IPC 27-12-00, FIGURE 10, PAGE 0, ITEM 130.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		NM  	2008	12	30	CA081125001      	1	20081125	G	2497		WIRE HARNESS    			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  						CHAFED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) IN FLIGHT CREW NOTICED SMOKE AND FLASHES ABOVE ROW 4DEF.  MX FOUND WIRING HARNESS CHAFED BY CEILING PANEL RESULTIN	G IN EXPOSED WIRES ARCHING.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
	20081230		NM  	2008	12	30	CA081125002      	1	20081125	G	2910	DSC252A40272	FLEX LINE       			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	BROKEN          	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			16282								(CAN) AFTER LANDING AND PARKING, VISIBLE SMOKE FROM RT LDG. SMOKE DUE TO AN HYD LEAK FROM BRAKE NR 3 BOKEN FLEXIBLE HOSE	. HOSE REPLACED IAW AMM 32-42-52.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081230		NM  	2008	12	30	CA081125003      	1	20081118	G	5610	80260008	WINDSHIELD      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			568  								(CAN) AT ABOUT 500 FT ON FINAL APPROACH TO THE AIRPORT THE RT WINDSHIELD SHATTERED.  THE FLIGHT CREWS INITIAL REACTION W	AS THAT THE WINDSHIELD HAD SUFFERED A BIRD STRIKE, BUT THIS WAS NOT THE CASE. THERE WAS NO EVIDENCE OF A BIRD STRIKE AND	 IT WAS THE INNER GLASS PLY THAT SHATTERED AND COVERED THE COPILOT WITH FINE GLASS DEBRIS. THE RESISTANCE OF THE HEATING	 ELEMENT (TERMINAL L1 AND L2) AND THE TEMPERATURE HEAT SENSORS (TERMINALS CB, DA AND FE) WAS CHECKED AND ALL FOUND TO BE	 WITHIN THE SPECIFICATIONS THE TEST REQUIREMENTS OF CMM 56-10-12. RT WINDSHIELD REMOVED AND REPLACED WITH A NEW WINDSHIE	LD IAW AMM TASKS 56-10-01-000-801, 56-10-01-400-801 AND 30-41-00-710-802.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
	20081230		SO  	2008	12	30	CA081125004      	2	20081112	G	8500	IO360KB	ENGINE          			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  		MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			2050 								(CAN) LOSS OF OIL PRESSURE DURING FLIGHT. PRECAUTIONARY LANDING ON NEARBY LAKE. INSP REVEALED HEAVY METAL CONTAMINATION 	IN OIL SCREEN, POSSIBLY CRANKSHAFT BEARING.					1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
	20081230		SW  	2008	12	30	CA081125005      	1	20081124	G	6500	1400191	WASHER          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					PITCH CHANGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE VERTICAL FIN WAS REMOVED TO FACILITATE SEAL REPLACEMENT OF THE PITCH CHANGE MECHANISM. THE RADIUS WASHERS THAT	 ARE USED ON THE VERTICAL FIN ATTACHMENT WERE INSPECTED, AND IT WAS NOTED THAT 3 OF THE 4 WASHERS HAD CRACKS ON THE OUTS	IDE PERIMETER OF THE WASHER. THE WASHERS P/N 140-019-1 WERE REPLACED AND THE FIN RE-INSTALLED. IT IS NOT KNOWN IF THIS C	ONDITION IS DUE TO OVERTIGHTENING OF THE FASTENER, OR THE INCREASE IN TORQUE VALUE FOLLOWING ISSUANCE OF ASB 206-06-107.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081230		NE  	2008	12	30	CA081125006      	2	20081111	G	7200		ENGINE          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  						FLAMED OUT      	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) DURING SHORT FINAL, UPON REDUCING THE POWER TO IDLE, THE ENGINE FLAMED OUT. THE EVENT OCCURRED AT AN ALTITUDE OF A	PPROX. 100 FEET AND THE CREW LANDED THE ACFT SINGLE ENGINE.   NOV. 12 2008: ENGINE FLAME-OUT EVENT OCCURRED WHILE DEPLOY	ING THE THRUST REVERSERS DURING LANDING ROLLOUT. THIS IS THE SECOND EVENT IN 2 DAYS ON THE SAME ENGINE. TROUBLESHOOTING 	IS ON-GOING WITH THE HELP OF MFG`S.			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
	20081230		NE  	2008	12	30	CA081125007      	2	20081104	G	7200		ENGINE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						VIBRATION       	W				O				OTHER                   				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) AT FL100 IN STEADY STATE, THE PILOT HEARD A STRONG NOISE COMING FROM THE ENG AND THE INSTRUMENTS INDICATED TEMP AT	 800C, NG AT 100 PERCENT AND TORQUE AT 2000 FT-LB. THE POWER LEVER WAS RETARDED AND PARAMETERS CAME BACK TO (NORMAL).  	THE FLIGHT CONTINUED AND DURING FINAL APPROACH, THE POWER REDUCED TO IDLE UNCOMMANDED AND THE ENG STOPPED RESPONDING TO 	POWER LEVER INPUTS. THE PILOT WAS ABLE TO LAND SAFELY WITH IDLE POWER. ONCE ON THE GROUND, THE COWLING WAS OPENED AND SM	OKE WAS OBSERVED COMING OUT OF THE ENGINE. THE ENG WILL BE REMOVED AND FWD FOR INVESTIGATION. UPDATES WILL BE PROVIDED T	O TC.	1	H	7	1 	3T	3	T		A37CE   	E4EA				 
	20081230		NE  	2008	12	30	CA081125008      	2	20081112	G	7200		ENGINE          								PWA   	PW120 	PW127       	 	NE  					NR 2	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE CREW FELT A SUDDEN YAW AND OBSERVED NR 2 ENGINE TEMP GAGE AT MAX. READING ACCOMPANIED BY AN EEC 	FAULT. NO UNUSUAL NOISES WERE REPORTED BUT PERSONNEL IN THE REAR OF CABIN REPORTED A SPIKE OF FLAME FROM THE EXHAUST. TH	E CREW ELECTED TO SHUT THE ENGINE DOWN AND A SINGLE ENGINE LANDING WAS PERFORMED. GROUND INSP FOUND ALL 3 ENGINE ROTORS 	NOT CAPABLE OF ROTATION. ENGINE WILL BE REMOVED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE	 ESTABLISHED.							4	T			E20NE				 
	20081230		NE  	2008	12	30	CA081125009      	2	20081017	G	7323		GOVERNOR        			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	PW121 	PW121       	52124	NE  					OVERSPEED	LEAKING         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) TEN MINUTES AFTER TAKEOFF, THE CREW GOT A RT ENG LOW OIL PRESSURE WARNING. THE PROPELLER DID NOT AUTO FEATHER AND 	THE CREW ATTEMPTED TO FEATHER THE PROPELLER MANUALLY WITHOUT SUCCESS. THE ENGINE REMAINED FUNCTIONING FOR FIVE MINUTES B	EFORE THE CREW ELECTED TO SHUT IT DOWN. THE PROP HOWEVER DID NOT FEATHER AND THE ACFT FLEW FOR 60 MINUTES WITH THE ENGIN	E SHUTDOWN BUT PROP WINDMILLING AT AROUND 70 PERCENT NP. A SINGLE ENGINE LANDING FOLLOWED. GROUND INSP FOUND AN OIL LEAK	 AT THE OVERSPEED GOVERNOR HYD PUMP MOUNTING PAD. CHIP DETECTOR CONTAMINATION AND SEIZED LP IMPELLER WAS ALSO OBSERVED. 	ENGINE WAS REMOVED AND FWD FOR REPAIRS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS	2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
	20081230		NE  	2008	12	30	CA081125010      	2	20081113	G	7200		OIL SYSTEM      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL270, THE PILOT NOTICED OIL ODOR AND SMOKE IN CABIN. HE ELECTED TO SHUTDOWN THE ENG AND SHORTLY 	AFTER, PERFORMED A UNEVENTFUL SINGLE ENGINE LANDING. POST FLIGHT INSP AND GROUND RUNS REVEALED OIL COMING OUT OF THE INL	ET AND COMPRESSOR BLEED VALVE.  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081230			2008	12	30	CA081125011      	1	20081113	G	6100		SLEEVE          								PWA   	PT6   	PT6A68      	 	NE  					PROP TRANSFER	DAMAGED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA											(CAN) WHILE IN THE VFR PATTERN THE ACFT EXPERIENCED A LOSS OF POWER ACCOMPANIED BY A CHIP LIGHT. THE ENG STABILIZED AT A	 REDUCED POWER SETTING AND 85 PERCENT NP AND THE CREW MADE AN EMERGENCY LANDING. AN INSP OF THE PROPELLER TRANSFER SLEEV	E REVEALED BLUING. THE ENGINE IS TO BE REMOVED AND REPLACED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROO	T CAUSE ONCE ESTABLISHED.								4	T			E26NE				 
	20081230		NE  	2008	12	30	CA081125012      	2	20081116	G	7200		ENGINE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					LEFT	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, WITH NO WARNING THE LT ENG SHUTDOWN ACCOMPANIED WITH A LOUD NOISE. THE FIRE WARNING FOLLOWED AND TH	E CREW DISCHARGED BOTH FIRE BOTTLES BEFORE DIVERTING THE FLIGHT WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED. POST FLI	GHT INSP REVEALED THAT THE PROPELLER WAS HARD TO ROTATE AND DEBRIS WERE FOUND IN THE ENG TAILPIPE. MFG WILL CONTINUE INV	ESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20081230		NE  	2008	12	30	CA081125013      	2	20081115	G	7321		EEC             			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					LT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA											(CAN) DURING CLIMB PASSING FL110, A SEVERE YAW TO THE LT WAS FELT AND THE CREW NOTED THAT THE LT ENG INDICATED 0 TORQUE 	(ENGINE STILL RUNNING). ATTEMPTS TO REGAIN ENG PWR WERE UNSUCCESSFUL AND THEY ELECTED TO RETURN TO THE POINT OF DEPARTUR	E. SHORTLY AFTER, VIBRATIONS WERE FELT AND THE CREW SHUT THE ENGINE DOWN. A SINGLE ENGINE LANDING FOLLOWED. TROUBLESHOOT	ING LED TO THE REPLACEMENT OF THE ENGINE ELECTRONIC CONTROL BEFORE THE ACFT WAS RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20090102		EA  	2009	1	2	CA081125014      	1	20081011	G	2822	RR12830	PUMP            			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL BOOST	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				6    							(CAN) OVERHAULED FUEL BOOST PUMP MAKING GRINDING NOSE WHEN TURNED ON.  PUMP REMOVED AND REPLACED WITH OVERHAULED BOOST P	UMP. FAILED PUMP HAD ONLY 6.1 HOURS TIME IN SERVICE SINCE OVERHAUL AND 5 FLIGHT CYCLES.  FAILED PUMP RETURNED TO INSTALL	ER.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
	20090102		NE  	2009	1	2	CA081125015      	2	20081115	G	7200		ENGINE          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					NR 1	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT, THE NR 1 ENG CHIP DETECTOR LIGHT ILLUMINATED. THE PILOT "BURNED" THE CHIP DETECTOR AND THE L	IGHT WENT OUT. SHORTLY AFTER THE LIGHT CAME ON AGAIN AND THE PILOT BURNED AGAIN AND THE LIGHT WENT OUT. HE DECIDED TO AB	ORT THE MISSION AND RETURN TO BASE DURING WHICH TIME HE HEARD A LOUD NOISE FROM THE ENGINE WITH PARAMETER DECAYING. THE 	ENG WAS SECURED AND AN UNEVENTFUL SINGLE ENGINE LANDING FOLLOWED. GROUND INSP FOUND HEAVY METAL CONTAMINATION AND FRACTU	RED POWER TURBINE BLADES. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.		1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
	20090102		NE  	2009	1	2	CA081125016      	2	20081117	G	7200		ENGINE          			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  						SHUTDOWN        	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL190, THE ENGINE SPOOLED DOWN UNCOMMANDED. EMERGENCY WAS DECLARED AND THE FLIGHT DIVERTED AND A 	SINGLE ENGINE LANDING WAS ACCOMPLISHED. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLIS	HED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
	20090102		EA  	2009	1	2	CA081125017      	2	20081107	G	7230		BLADES          								PWA   	PT6   	PT6A28      	 	EA  					COMPRESSOR	FRACTURED       	W				A				UNSCHED LANDING         				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL170, THE LT ENG LOST POWER AND THE TEMP INCREASED TO 850 DEGREES C.  (1) PASSENGER SAW FLAMES O	UT THE EXHAUST. THE ENG WAS SHUTDOWN AND A SINGLE ENGINE LANDING FOLLOWED. POST FLIGHT INSP FOUND FRACTURED COMPRESSOR T	URBINE BLADES. THE ENG WILL BE INVESTIGATED AT IN PRESENCE OF A MFG REP AND UPDATES WILL BE PROVIDED.									4	T			E4EA				 
	20090102		EA  	2009	1	2	CA081125018      	2	20081116	G	7250		BLADES          								PWA   	PT6   	PT6A6       	52043	EA  					POWER TURBINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) ACFT TYPE ID PC-9. WHILE APPLYING POWER DURING A TOUCH AND GO, THE ENGINE STARTED VIBRATING. THE PILOT REDUCED THE	 POWER TO IDLE AND ABORTED T/O.   AS THE A/C SLOWED DOWN ON THE RUNWAY, OIL BEGAN TO SPRAY OVER THE CANOPY. ONCE CLEARED	 OF THE RUNWAY, THE PROPELLER SLOWED DOWN RAPIDLY AND THE ENG WAS IMMEDIATELY SHUTDOWN. POST FLIGHT INSP FOUND FRACTURED	 PT BLADES, THE EXHAUST DUCT HAS A HOLE THROUGH THE INNER "SKI JUMP", THE EXHAUST STACK HAS MULTIPLE HOLES AND DENTS AND	 THE ENGINE COWLING IS DENTED. MFG IS REQUESTED THE ENG BE FWD TO PLT 5 FOR INVESTIGATION.							3	T			E4EA				 
	20090102		NE  	2009	1	2	CA081125019      	2	20081119	G	7261		OIL SYSTEM      			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					RT ENGINE	LEAKING         	W				B				EMER. DESCENT           				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		DE	DESCENT        	1			CA											(CAN) APPROX 20 MILES SOUTH OF AIRPORT, THE PILOT REPORTED SMOKE IN CABIN. HE DECLARED AN EMERGENCY AND THEY WERE GIVEN 	PRIORITY TO LAND. MX  PERFORMED GROUND RUNS AND FOUND THE RT ENG OIL LEAKING INTO THE BYPASS AIR AND REACHING CABIN BLEE	D AIR DUCTS. THE ENG IS BEING REMOVED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
	20090102		NE  	2009	1	2	CA081125020      	2	20081121	G	7200		ENGINE          			AGUSTA	A109  	A109E       	0260119	EU  	PWC   	PW206C	PW206C      		NE  					NR 2	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	R		PARTIAL RPM/PWR LOSS      	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA											(CAN) PILOT REPORTED NR 2 ENG CHIP LIGHT ILLUMINATED AT TOP OF CLIMBOUT, IMMEDIATELY FOLLOWED BY A SURGE AND POWER LOSS.	 PILOT PREPARED FOR A RUN-ON LANDING. NR 2 ENG WAS SECURED, PASSENGERS WERE BRIEFED AND TRAFFIC AND DISPATCH WERE ALERTE	D.  NR 1 ENG WENT TO 124 PERCENT TORQUE AFTER NR 2 ENG POWER LOSS. SUCCESSFUL RUN-ON LANDING WAS ACCOMPLISHED AND ACFT W	AS GROUND-TAXIED TO PARKING AREA. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			1	G	7	2 	3U	3	U	RT	H7EU    	E42NE				 
	20090102		NM  	2009	1	2	CA081126001      	1	20081120	G	2720	3985001007	CONTROL UNIT    			BOMBDR	DHC8  	DHC8402     	1390042	NM  	PWC   	150   	PW150A      	 	EA  					RUDDER	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			4779 								(CAN) WHILE PERFORMING TASK 27-21-28-710-801 OPS TEST OF THE RUDDER SHUT-OFF VALVES, NR1 RUDDER SHUT-OFF VALVE FAILED TO	 CLOSE WHEN SELECTED OFF.  THE FLIGHT CONTROL ELECTRONIC CONTROL UNIT (FCECU) WAS REPLACED. THE TASK WAS PERFORMED AND P	ASSED THE TEST. THE FCECU WAS TESTED IAW AMM 27-00-01.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20090102		NM  	2009	1	2	CA081126002      	1	20081116	G	5230		DOOR            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					CARGO	NOT CLOSED      	W				A				UNSCHED LANDING         				W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AIR TURNBACK: AFTER T/O FUSELAGE DOOR WARNING LIGHT CAME ON. AFT CARGO DOOR INDICATION.  ON INSP AFTER LANDING IT 	WAS NOTICED THE THE AFT CARGO DOOR HANDLE WAS POPPED OUT. THE DOOR WAS CLOSED BUT NOT LOCKED.  AFT CARGO DOOR WAS FUNCTI	ONED AND CLOSED AND LOCKED.  SUSPECT THAT THE GROUND CREW DID NOT FULLY PUSH THE HANDLE INTO THE CORRECT POSITION.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20090102		NM  	2009	1	2	CA081126003      	1	20081124	G	5270		SENSOR          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					DOOR LOCK	OUT OF RIG      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AIR TURNBACK: FUSELAGE DOOR WARNING LIGHT IN FLIGHT.  RIGGED EMERGENCY EXIT DOOR PROXIMITY SENSOR EDRCLLK IAW AMM 	52-71-01. INDUCTANCE 8.600MH.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20090102			2009	1	2	CA081126005      	4	20081104	G	3457	S67157520	ANTENNA         			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	03047	GL  					NR 2 GPS	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			CA											(CAN) FLIGHT CREW REPORTED NR 2 FMS DRIFTED 8NM AT END OF THE LEG.  NR 2 GPS ANTENNA REPLACED AND TESTED SERVICEABLE IAW	 34-54-01.					2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
	20090102		NM  	2009	1	2	CA081126006      	1	20081010	G	2910	82920010263	LINE            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA			6726 								(CAN) DURING CRUISE FLIGHT SEVERAL DROPS OF HYD FLUID WERE DISCOVERED COMING FROM THE RT OVERHEAD CEILING. SOME FLUID FE	LL ON THE PASSENGERS IN THE AREA. NO INJURIES REPORTED.  NO EMERGENCY ACTION/PROCEDURES CONDUCTED.  AFTER AN UNEVENTFUL 	LANDING MX DETERMINED THE LEAK TO BE FROM A HYD TUBE FITTING.  THE TUBE WAS REPAIRED AND THE ACFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090102			2009	1	2	CA081126007      	4	20081021	G	3100	7014300901	DISPLAY         			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	03047	GL  					NR 4	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) RE-OCCURRING DEFECT 2008/10/21 -FLIGHT CREW REPORTED NR 4 DISPLAY UNIT FLICKED ON START-UP. FAULT COULD NOT BE DUP	LICATED AND WAS SWAPPED TO NR4 POSITION FOR TROUBLESHOOTING PURPOSES.  2008/10/22 -FLIGHT CREW REPORTED NR3 DISPLAY UNIT	 FAILED AT THE TOP OF DESCENT. NR 3 DISPLAY UNIT DEFERRED IAW MEL.  2008/10/24 -NR 3 DISPLAY UNIT REPLACED WITH REPAIRED	 UNIT FROM MFG AND CHECKED SERVICEABLE IAW AMM 34.  2008/10/30 -MX REPORTED NR 3 DISPLAY UNIT STARTING FLASHING INTERMIT	TENT WHITE DIAMONDS AND BLACK SCREEN DURING EXTENDED OPERATION. NR 3 DISPLAY UNIT DEFERRED IAW MEL. RE-OCCURRING DEFECT 	FORM GENERATED.  TEAR DOWN REPORT OF THIS UNIT IDENTIFIED THIS AS BEING THE REASON FOR REMOVAL FROM PREVIOUS AIRCRAFT.  	2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
	20090102		WP  	2009	1	2	CA081126008      	1	20081121	G	2435	14924HTH	CASE            			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					STARTER GEN	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			41   								(CAN) STARTER CASING CRACKED.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20090102		NE  	2009	1	2	CA081127001      	1	20081103	G	6320	S613520670043	HOUSING         			SKRSKY	S61   	S61N        	8142104	NE  										M/R GEARBOX	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACK FOUND ON THE FRONT/RT SIDE OF LWR HSG  REPAIR TO LWR HSG CARRIED OUT IAW RDC NO: P-RH07-038 H1E-02.  THIS AR	EA OF THE HSG IS ALWAYS HIGHLY SCRUTANIZED DURING NDT.					2	G	7	2 	4U				1H15    					 
	20090102		NE  	2009	1	2	CA081127002      	1	20081103	G	6230		BEARING         			SKRSKY	S61   	S61A        	814210C	NE  										MAST	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) S61MGB S/N: A14-J-10-79-1119 SUPPLIED, HAD A INDICATION ON THE MGB BEING CONTAMINATED WITH METAL. REMOVED THE MGB 	FROM THE ACFT, AND RETURNED IT TO HELI-ONE TSN: 15634:00 TSO: 772:29 HELI-ONE DISASSEMBLED THE MGB TO FIND THAT THE MAST	 DUPLEX BRG P/N:SB1357-103 ,S/N: J0359 WAS THE CAUSE OF THE CONTAMINATION.  REPLACEMENT OF BRG REQUIRED. MAST DUPLEX BRG	 P/N:SB1357-103 ,S/N: J0359 COMPANY SQID NR08-07990.			2	G	7	2 	4U				H2EA    					 
	20090102		NE  	2009	1	2	CA081127003      	1	20081030	G	6230		GUIDE           			SKRSKY	S76   	S76A        	8143006	NE  										SWASHPLATE	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MGB PN: 76351-09600-043 S/N:A231-00085 FOLLOWING INSP OF SWASHPLATE GUIDE PN:76351-09029-101,SN:A028-00343 FROM AB	OVE MENTIONED MGB,THE MEASUREMENT TAKEN AT RADIUS (J ) (REF:SA4047-76-7-8,CHG.9) INDICATES BELOW MINIMUM REQ`D RADIUS OF	.040 INCH.  IAW O/H MANUAL REF,  SWASHPLATE GUIDES ARE AMONG THE LIST OF ITEMS CLASSIFIED AS FLIGHT SAFETY PARTS. PART H	AS BEEN TAGGED REJECTED AS THIS MINIMUM .040 INCH RADIUS IS CONSIDERED A CRITICAL CHARACTERISITIC. RETURN TO VENDOR FOR 	WARRANTY (THIS PART HAS A TIME LIFE OF 20,000 HRS AND HAS ONLY BEEN IN SERVICE FOR ONE MGB O/H OF 3242.7 HRS, SEE MGB LO	G CARDS)  MOST LIKELY MACHINED INCORRECTLY DURING MFG PROCESS.  SQID NR 08-07896.	1	G	7	2 	3U				H1NE    					 
	20090102		NE  	2009	1	2	CA081127004      	1	20080911	G	6230	SB3354102	CONE            			SKRSKY	S76   	S76         	8143010	NE  										M/R GEARBOX BRG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSPECTION OF CAGE SHAKE ON TAPERED ROLLER BRGS PN: SB3354-102 WAS DIMENSIONALLY INSPECTED IAW (SA4047-76-7-8 CHAN	GE 9, 31/MARCH/2006 IAW PARA. 2-52A) AND DETERMINED TO EXCEED AVERAGE MAXIMUM ALLOWABLE CAGE SHAKE LIMITS (.017 INCH) PR	IOR TO INSTALLATION ON MGB PN: 76351-09600-044 SN:A231-00184.  RETURN TO VENDOR FOR WARRANTY. UNSERVICEABLE BRG CONE RET	URNED TO VENDOR AWAITING WARRANTY RMA NR.  (COMPANY SQID NR 08-06654)			1	G	7	2 	3U				H1NE    					 
	20090102		NE  	2009	1	2	CA081127005      	3	20081112	G	6114	E6468	HUB             			BEECH 	56    	56TC        	1152736	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				2209 							(CAN) PROPELLER CAME IN FOR SHIFTED PRELOAD PLATES. HUB DID NOT SEEM TO SEAL (MATE) PROPERLY. THERE WERE HEAVY WEAR MARK	S ON THE CENTER SECTION OF THE MATING SURFACES ONLY. TEFLON WAS WORN THROUGH ON ALL (4) BLADES. ONE OTBD BRG RACE WAS BA	DLY CHIPPED AND SHOWED SIGNS OF CRACKING.				1	L	7	2 	3O				3A16    		5	C	P10NE	 
	20090102		NE  	2009	1	2	CA081127007      	1	20080708	G	6320	7635109626	SHAFT           			SKRSKY	S76   	S76         	8143010	NE  										M/R GEARBOX	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MGB PN:76351-09600-044 SN:A231-00044 IN FOR OVERHAUL. FOLLOWING CLEANING AND INSP OF NEW SPLINE SHAFT, CORROSION W	AS FOUND AT INNER AND OUTER SPLINES.  ALL REMAINING SPLINES SHAFTS (QTY:6) PULLED FROM STOCK AND INSPECTED, NO EVIDENCE 	OF CORROSION FOUND.  CORROSION PITTING FOUND ON NEW SPLINE SHAFT PULLED FROM STOCK.  RETURN TO VENDOR FOR FULL WARRANTY 	 COMPANY SQID NR 08-05027.			1	G	7	2 	3U				H1NE    					 
	20090102		NE  	2009	1	2	CA081127008      	1	20080620	G	6320	7635109058102	PINION GEAR     			SKRSKY	S76   	S76         	8143010	NE  										M/R GEARBOX	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION PITTING FOUND ON BORE ID OF (2) HELICAL PINIONS  HSI (P.A.P) MGB PN:76351-09500-044 SN:A081-00196 REC`D 	FOR O/H. PRIOR TO ASSY INSP OF NEW CUSTOMER SUPPLIED HELICAL PINIONS (X2), REVEALED CORROSION PITTING IN BORE ID OF BOTH	 PINIONS AT AREA OF FWD ROLLER PATHWAY. COMPANY SQID NR08-04520.				1	G	7	2 	3U				H1NE    					 
	20090102		NE  	2009	1	2	CA081127009      	1	20080611	G	6320	7635109028105	SHAFT           			SKRSKY	S76   	S76         	8143010	NE  										M/R GEARBOX	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION FOUND ON NEW QUILL SHAFT MAIN GEARBOX O/H PN:76351-09500-044, SN:A081-00110 FOLLOWING CLEANING AND INSPE	CTION OF NEW QUILL SHAFT (P/N,S/N LISTED BELOW), MULTIPLE CORROSION PITTING CLUSTERS FOUND ON INTERNAL SPLINES AND ID OF	 PART.				1	G	7	2 	3U				H1NE    					 
	20090102			2009	1	2	CA081127010      	1	20080611	G	6320	7635109028105	SHAFT           																	M/R GEARBOX	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) EXCESSIVE CORROSION FOUND ON NEW QUILL SHAFT. MAIN GEARBOX O/H PN:76351-09500-044, SN:A081-00058 DURING CLEAN-UP A	ND INSP OF NEW QUILL SHAFT (PN, SN MENTIONED BELOW) MULTIPLE CORROSION PITTING CLUSTERS FOUND ON INTERNAL SPLINES AND ID	 OF PART.  RETURN TO VENDOR FOR FULL WARRANTY UNSERVICEABLE QUILL SHAFT RETURN TO VENDOR AWAITING WARRANTY RMA NR  COMPA	NY SQID NR 08-04306.																 
	20090102		NE  	2009	1	2	CA081127011      	1	20080606	G	6320	SB3202A2	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  										M/R GEARBOX	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PERFORMED CAGE SHAKE ON NEW BRGS IAW MFG ACFT ENGINEERING INSTRUCTION EI NR E76-702-35-1601. RESULTS FAILED INSP R	ETURN TO VENDOR FOR WARRANTY. UNSERVICEABLE BRG RETURN TO VENDOR AWAITING WARRANTY RMA NR COMPANY SQID NR 08-04194.					1	G	7	2 	3U				H1NE    					 
	20090102		NE  	2009	1	2	CA081127012      	1	20080417	G	6320	7635109008056	HOUSING         			SKRSKY	S76   	S76A        	8143006	NE  										M/R GEARBOX	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GEARBOX REMOVED FOR EXCESSIVE CORROSION AROUND OIL FILTER HSG FITTING. MAIN GEARBOX RECEIVED AT HELI-ONE FOR REPAI	R AT TT:10961:18 HRS. TSO:2969:48 HRS. FLUID ADAPTER (FITTING) REMOVED FROM LWR HSG OIL FILTER AREA AND CORROSION WAS CL	EANED/REMOVED TO ALLOW FOR INSPECTION.  EXTENSIVE CORROSION WAS FOUND AT FLUID ADAPTER PORT AND LOCK RING AREA BEYOND MA	XIMUM REPAIRABLE LIMITS IAW REF:SA4047- 76-7-8,CHG.9-31MAR2006.  REPLACE UNSERVICEABLE LOWER HOUSING P/N:76351-09008-056	 S/N:C065-00098 (T.T: UNK) WITH NEW/OVERHAULED EQUIPPED WITH NEW VERSION FLUID ADAPTER P/N:RFSK9812-13. MOST LIKELY INSU	FFICIENT SURFACE PROTECTION AT DAMAGED AREA.	1	G	7	2 	3U				H1NE    					 
	20090102		NE  	2009	1	2	CA081127013      	1	20080320	G	6320	SB2151107	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  											UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GEARBOX MAKING METAL TSN:2969:43 HRS. GEARBOX RECIEVED FOR PREMATURE OVERHAUL DUE TO METAL CONTAMINATION.  DURING 	INSP PROCESS , RT SPUR PINION ALIGNMENT ROLLER BRG SB2151-107 S/N:2659 (LOCATED AT UPPER HSG COUNTERBORE) WAS FOUND TO B	E BREAKING UP AT OUTER RACE ROLLER PATHWAY. FOLLOWING COMPLETION OF GB INSP THIS BRG WAS CONSIDERED AS THE SOURCE FOR TH	E METAL CONTAMINATION.  REPLACE BRG DURING OVERHAUL.			1	G	7	2 	3U				H1NE    					 
	20090102		NE  	2009	1	2	CA081128001      	2	20081125	G	7250	PW120A	TURBINE         			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2 ENGINE	FAILED          	W				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			CA			27846	17199							(CAN) PRIOR TO TAKEOFF, THE CREW FELT A THUD AND GRINDING NOISE FROM THE NR 2 ENGINE AT 70 PERCENT TORQUE. THE ENGINE WA	S IMMEDIATELY SHUTDOWN, BUT BY THE TIME THE TORQUE REDUCED TO ZERO PSI AND THE ITT OF THE ENG REACHED UP TO 1200 DEGREE 	CELSIUS. ENG WAS IMMEDIATELY SHUTDOWN AND TAKEOFF WAS ABANDONED. ON RETURN AT THE RAMP, BROKEN PIECES OF BLADES OF PWR T	URBINE WERE FOUND IN THE TAIL EXHAUST PIPE. ALL PARAMETERS OF BOTH ENGINES WERE WITHIN LIMIT. AS SOON AS THE TAKEOFF ROL	L INITIATED AND PWR WAS ADVANCED THROUGH 70 PERCENT TORQUE, A THUD AND GRINDING NOISE WAS HEARD FROM RT SIDE (NR 2 ENG) 	AND ACFT STARTED SWINGING TO THE RT. IMMEDIATELY, THE TAKEOFF WAS REJECTED AND WHILE LOWERING THE POWER LEVERS THE TORQU	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090102		NE  	2009	1	2	CA081128002      	1	20081103	G	6320	S613723053102	BEVEL GEAR      			SKRSKY	S61   	S61A        	814210C	NE  										M/R GEARBOX	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA				770  							(CAN) BROKEN GEAR TOOTH FOUND IN FILTER REPAIR-BROKEN GEAR TOOTH FOUND IN FILTER OF S61 MGB SN: A14-215. MGB WAS REMOVED	 FROM ACFT HS-HTA AND REURNED TO HELI-ONE TO BE REPAIRED TSN: 31804:41 TSO: 769:56 DISASSY DONE AT HELI-ONE TO FIND THAT	 THE INPUT BEVEL GEAR PN: S6137-23053-102 SN: E128-00271WAS THE DAMAGED PART. INPUT BEVEL GEAR PN: S6137-23053-102 SN: E	128-00271.  COMPANY SQID NR 08-08045.			2	G	7	2 	4U				H2EA    					 
	20090102		NE  	2009	1	2	CA081128003      	1	20081127	G	6320		GEARBOX         			SKRSKY	S76   	S76         	8143010	NE  										MAIN ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MGB CHIP LIGHT INDICATION MGB PN:76351-09600-044,SN:A231-00107 REC`D AT HELI-ONE FOR REPAIR. TSN:8638:39 TSO:2516:	54 FOLLOWING DISASSEMBLY AND INSPECTION OF MGB, RT OUTPUT ALIGNMENT BRG WAS IDENTIFIED AS THE CAUSE FOR METAL GENERATION	 WITH HEAVY SPALLING EVIDENT AT ROLLER PATHWAY OF OUTER RACE.  FLUSH MGB AND REPLACE DISCREPANT BEARING.  COMPANY SQID N	R 08-8606.			1	G	7	2 	3U				H1NE    					 
	20090102		NE  	2009	1	2	CA081128004      	1	20081127	G	6320	SB2151107	BEARING         			SKRSKY	S76   	S76         	8143010	NE  										M/R GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2037 								(CAN) MGB CHIP LIGHT INDICATIONS MGB P/N:76351-09600-044 S/N:A231-00299 REC`D AT HELI-ONE FOR REPAIR. TSN:2037:48 HRS. F	OLLOWING DISASSY AND INSP OF MGB THE RT OUTPUT ALIGNMENT BRG WAS FOUND TO BE THE CAUSE FOR THE METAL GENERATION WITH HEA	VY SPALLING AT ROLLER PATHWAY OF BRG OUTER RACE.  ADDITIONAL BRS INDICATE INITIAL STAGES OF SPALLING. REPLACE WITH SERVI	CEABLE BRS.  COMPANY SQID NR 08-08605.			1	G	7	2 	3U				H1NE    					 
	20090102			2009	1	2	CA081128005      	4	20081127	G	3120	285T08551	FDAS            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					COCKPIT	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ON CRUISE THE F/A REPORTED A STRONG ODOR IN THE CABIN, PILOT CONFIRMED THE STRONG SMELL AND DIVERTED FLIGHT TO BAS	E AND DECLARE AN EMERGENCY LANDING. AFTER MX INVESTIGATION, FOUND THE FDAS "FLIGHT DECK ACCESS SYS" AT FAULT.  ELECTRICA	L ODOR COMING FROM THIS COMPONENT.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090102		EA  	2009	1	2	CA081128006      	2	20081126	G	8530		VALVE SEAT      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1452 							(CAN) INTAKE VALVE STAYING OPEN, INTAKE VALVE AND SEAT WORN.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
	20090102		EA  	2009	1	2	CA081129001      	1	20081125	G	5610	NP1393229	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			9278 								(CAN) IN FLIGHT LT SIDE WINDOW SHATTERED. FLIGHT DIVERTED MX REPLACED SIDE WINDOW.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090102		EA  	2009	1	2	CA081129003      	1	20081122	G	3260		WARNING LIGHT   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					MLG	ILLUMINATED     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, LANDING GEAR DID NOT RETRACT WHEN SELECTED UP. LANDING GEAR LIGHT REMAINED GREEN. FLT CREW ALSO REP	ORTED INBD ANTI-SKID (C) AND PARK BRAKE SOV (C) MSG. ALL MSGS CLEARED WHEN GEAR SELECTED DOWN. ACFT RETURNED TO DEPARTUR	E AIRPORT AND LANDED WITHOUT FURTHER INCIDENT.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090102		EA  	2009	1	2	CA081129005      	1	20081116	G	2150	GG670950093	ACM             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5B1   	30052	NE  					LEFT	SEIZED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			5579 								(CAN) AFTER LANDING AND TAXI TO GATE, FLT CREW REPORTED SMOKE STARTED COMING FROM VENTS IN COCKPIT. CREW ELECTED TO STOP	 SHORT OF THE GATE AND EVACUATE THE ACFT. ACFT WAS EVACUATED WITHOUT INCIDENT.  MX INSPECTED ACFT AND FOUND THAT THE LT 	ACM HAD SEIZED. NO OTHER DEFECTS WERE NOTED. LT PACK WAS DEFERRED IAW THE MEL AND ACFT RETURNED TO SERVICE.  17 NOV 08: 	MX REMOVED AND REPLACED THE LT ACM AND OPS CHECKED. NO FURTHER DEFECTS NOTED. LT PACK REMOVED FROM DEFERRAL AND ACFT RET	URNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20090102		NM  	2009	1	2	CA081201001      	1	20081128	G	2510	412310416	SEAT BACK       			EMB   	ERJ190	ERJ190100IGW	3260408	NM  	GE    	CF34  	CF3410E5A1  	30022	NE  					COCKPIT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ATTACH SCREWS HOLDING SEAT BACK BRACKET TO SEAT ARM ARE LOOSE, THE BRACKET ATTACHES THE SEAT BACK TO THE ARM. 	THE SCREWS ARE 0.5 INCHES IN LENGTH, THE SWIVEL BRACKET ATTACH POINT WAS ALSO LOOSE. REF: 4/MM 41402003, IPL 25-22-90 PA	GE 10044 FIGURE 7 ITEMS 5 & 10. CHAIR PN ARE414140003-105, 41414003-111,41414003-113,41404003-103 & 41404003-105.				2	L	7	2 	4F	4	F	RT	A57NM   	E00070EN				 
	20090102		CE  	2009	1	2	CA081201002      	1	20081201	G	3340	0713035	SWITCH          			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					LANDING LIGHT	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LANDING LIGHT SWITCH MAY BE ORIGINAL (8865 HRS) DETENTS BECAME "STICKY" AND NOT AS POSITIVE AS NORMAL. SWITCH FUNC	TION DID NOT FAIL.  INSP REVEALED PWR SUPPLY WIRE END AND LUG ON SWITCH OVERHEATED. DISASSY SHOWED LUG CONTACT RIVET DET	ERIORATED AS WELL AS MYCARTA TYPE BOARD MATERIAL DISINTEGRATING DUE TO HEAT DAMAGE AROUND THE RIVET.  MFG REQUIRES NEWER	 STYLE (1970 AND NEWER) LANDING LIGHT SWITCHES TO BE REPLACED EVERY 5 YEARS THIS OLDER STYLE SWITCH THOUGH LIKELY ABLE T	O CARRY MORE CURRENT SHOULD BE INSPECTED VISUALLY ANNUALLY TO DETERMINE IF OVERHEATING IS AN ISSUE.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20090203		CE  	2009	2	3	CA081201003      	1	20081009	G	3597	P108	CONNECTOR       			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					O2 SYSTEM	MISINSTALLED    	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) PASSENGER O2 MASK WOULD NOT DEPLOY WHEN TESTED.  SYSTEM TROUBLESHOT AND FOUND CONNECTOR P108 WAS NOT INSTALLED COR	RECTLY.  CONNECTOR REMOVED, INSPECTED AND REINSTALLED .O2 MASK FUNCTION CHECKED SERVICEABLE IAW AMM 35.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
	20090102			2009	1	2	CA081201004      	1	20081201	G	8011		BOLT            																	STARTER	MISSING         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			498  	498  							(CAN) STARTER CASE THROUGH BOLTS. BOLTS HAVE LOOSENED OFF TO THE POINT OF CAUSING ELECTRICAL SHORTING WITHIN THE STARTER	 DUE TO THE HALVES BEING LOOSE FROM EACH OTHER. ONE BOLT COMPLETELY MISSING. SPARKS AND ARCING VISUALLY OBSERVED AT BEND	IX HSG DURING STARTER OPERATION.																	 
	20090102		WP  	2009	1	2	CA081201005      	2	20081130	G	7200	31037505	GASKET          								GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24   								(CAN) THIS ENG WAS NOTED TO HAVE A OIL LEAK COMING FROM THE BOTTOM OF THE DIAPHRAGM AT THE 2 BOTTOM BOLT HOLES CLOSEST T	O THE CHIP DETECTOR. THE GASKET WAS NOTED TO BE STICKING OUT AND NOT SEALING PROPER. UPON FURTHER INVESTIGATION THE OLD 	STYLE GASKETS PN 3103750-1/-3/-4 WERE CHANGED UP TO A 3103750-5 TO PREVENT THIS ISSUE. REF: SB TPE331-72-2084 FOR THE UP	GRADED GASKETS. THE 3103750-5 GASKET WAS INSTALLED ONLY 23.5 HRS PRIOR TO THIS OIL LEAK AT A REPAIR. THE CASE BOLTS WERE	 CHECKED AND WERE AT THERE PROPER TORQUE.							4	T			E4WE				 
	20090102		CE  	2009	1	2	CA081201006      	1	20081201	G	5310	NAS1473A3K	DOME NUT        			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	03047	GL  					WINDSHIELD POST	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE REPLACEMENT OF THE RT WINDSHIELD, DUE TO A BROKEN OUTER PANE, HEAVY CORROSION WAS NOTED COMING OUT OF T	HE DOME NUTS. THE WINDSHIELD IS INSTALLED FROM THE OUTSIDE AND THE SCREWS ARE HELD IN PLACE BY THESE DOME NUTS THAT RIVE	TED IN PLACE AROUND THE PERIMETER OF THE FRAME. EACH DOME NUT WAS BOROSCOPED AND FOUND THAT A MAJORITY WERE SPLIT OR CRU	MBLED DUE TO CORROSION. ALL DOME NUTS WERE REPLACED AND THE WINDSHIELD RE-INSTALLED.			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
	20090102		CE  	2009	1	2	CA081201007      	1	20081128	G	2720	04115264	RUDDER BAR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	RT RUDDER	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10660								(CAN) SCREWS ATTACHING CENTER CONTROL CONSOLE COVER PN 0413463-5 WERE TOO LONG AND CHAFING IN TO THE RT SIDE OF THE RUDD	ER PEDAL TORQUE TUBE.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
	20090102		NM  	2009	1	2	CA081201008      	1	20080919	G	6320	B7936S	CHIP DETECTOR   			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47M     	03013	GL  					TRANSMISSION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			800  								(CAN) BOTH TEDESCO B7936S CHIP DETECTOR BASES FOUND CRACKED AT BASE OF O-RING FLANGE. CAUSED BY OVERTORQUE DURING AN EAR	LIER INSTALLATION. CRACKS NOT VISIBLE UNTIL CHIP DETECTORS WERE REMOVED TO DRAIN TRANSMISSION OIL.					1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
	20090102		NM  	2009	1	2	CA081201009      	1	20081128	G	5302	500N34247	ANGLE           			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47M     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			800  								(CAN) FUSELAGE ANGLE FOUND CRACKED DURING A TAILBOOM INSPECTION. PART IS NOT READILY VISIBLE OR A PLACE OF INTEREST DURI	NG INSPECTIONS AND MAY HAVE GONE SOME TIME AS CRACKED. PART IS TO BE REPLACED BEFORE FURTHER FLIGHT.					1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
	20090203		SW  	2009	2	3	CA081201010      	1	20080901	G	2910		HOSE            			BELL  	206   	206B        	1181511	SW  										HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UPON ENGINE SHUTDOWN WALK-AROUND, PILOT REPORTED A TRANSMISSION OIL LEAK ON MACHINE.  LEAK INSPECTED AND FOUND TO 	BE FROM THE MAIN HYDRAULIC PUMP HOSE.  HOSE HAD CHAFED THROUGH ON A MS21919WDG CLAMP HOLDING IT DOWN TO THE TOP DECK OF 	A/C.  WDG CLAMP SERIES IS NOT DESIGNED FOR USE AROUND OILS AND THIS IS BELIEVED TO HAVE CAUSE THE RUBBER CUSHION ON THE 	CLAMP TO DETERIORATE AGAINST THE STAINLESS STEEL BRAIDED HOSE AND CAUSE A METAL ON METAL CONTACT THAT WENT UNDISCOVERED 	UNTIL HOSE FAILURE.  WDG CLAMP AND HOSE ASSY WERE SUBSEQUENTLY REPLACED.		1	G	7	1 	3U				H2SW    					 
	20090204		SW  	2009	2	4	CA081201011      	1	20081001	G	6320	206031554003	SPINDLE         	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TRANSMISSION	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TRANSMISSION MOUNTS REMOVED DUE TO BEARING WEAR.  UPON FURTHER INSP, SPINDLE ALSO FOUND DAMAGED IN LOCATION OF WAS	HER P/N 206-030-507-001.  HARD WASHER MOVEMENT DUE TO BEARING WEAR HAD WORN INTO THE RADII OF THE SPINDLE MOUNTING AREA.	  SPINDLE SCRAPED.  SPINDLE HARDNESS NOT TESTED.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20090102		NM  	2009	1	2	CA081201012      	1	20081129	G	3251	651781412	ACTUATOR        			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					STEERING UNIT	WORN            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) A "CLUNK" IN THE NOSE WHEEL STEERING TILLER WAS REPORTED. BOTH STEERING ACTUATOR ROD ENDS WERE FOUND PULLING OUT O	F THE PISTONS. BOTH STEERING ACTUATORS WERE REPLACED. A/C RETURNED TO SERVICE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20090102			2009	1	2	CA081202001      	1	20081201	G	3244	301003530	TIRE            																	MLG	BULGED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) A BULGE WAS NOTICED ON THE TIRE DURING A PRE-FLIGHT INSP. SUBSEQUENT INSP UPON REMOVAL REVEALED A RIP IN THE INNER	 TIRE CARCASS.																		 
	20090102		NM  	2009	1	2	CA081202002      	1	20081129	G	3250	C247360011	STEERING SYS    			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					NLG	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			33128								(CAN) NW STEERING SWING TO THE LT DURING TO ROLL AT APPROX 100 KTS. NEEDED FULL RUDDER AND RT BRAKE TO MAINTAIN CENTERLI	NE. STEERING CONTROL UNIT 6GC REPLACED IAW MM S/N H0714.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
	20090102		NE  	2009	1	2	CA081202003      	2	20081106	G	7250	311074102	RETAINING RING  								PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2760 	2760 							(CAN) ENGINE WAS RECEIVED FOR INVESTIGATION/REPAIR DUE TO SHIFTING OF CT SHROUD SEGMENTS. THE CT SHROUD SEGMENT-RETAININ	G RING WAS OF POST SB 1627 CONFIGURATION AND THE CT SHROUD SEGMENTS (P/N 3035673CL12) POST SB 1628. DURING INVESTIGATION	, HEAVY RUB SPOTS WERE NOTED ON QTY. 1-CT SHROUD SEGMENT AND ALL THE CT BLADES. THE CT SHROUD SEGMENTS RETAINING RING WA	S FOUND DISENGAGED FROM THE RETAINING CAVITY OF CT SHROUD HSG, CAUSING LOOSENING AND DROOPING OF CT SHROUD SEGMENT. THIS	 RESULTED IN HEAVY RUB BETWEEN THE CT BLADES AND SHROUD SEGMENT. THE CT TIP CLEARANCES WERE INCREASED TO APPROX 0.048 IN	CH, WHICH ADVERSELY AFFECTED ENGINE PERFORMANCE. NO CURLING/BOWING OF CT SHROUD SEGMENTS WAS OBSERVED. NO OVER HEATING/B						3	T			E4EA				 
	20090204		EU  	2009	2	4	CA081202004      	1	20081113	G	6710	350A27035106	CONTROL TUBE    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	60053	NE  					COLLECTIVE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14378								(CAN) EVERY 12 YEARS THE HELICOPTER GOES INTO THE SHOP FOR A MAJOR INSPECTION AS PART OF THE INSP, IS A HARDNESS TEST ON	 THE COLLECTIVE CONTROL TUBE.  THE TUBE IS TESTED AND IT FAILED THE HARDNESS TEST.  THE HARDNESS TEST REQUIRED IS 230 HV	-5 KG LOAD.  THE AVERAGE LOAD FOR THIS COLLECTIVE TUBE WAS 168.1 HV, (FAILED THE HARDNESS TEST).				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
	20090102		CE  	2009	1	2	CA081203001      	1	20081120	G	2840	100380006119	PROBE           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	RT AUX TANK	SEPARATED       	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) DURING A 3RD PHASE 600 HR INSP, A SNAG WAS CREATED TO FIX A DISCREPANCY IN THE RT FUEL QUANTITY INDICATING SYS. TH	E RT FUEL TANK READING WAS 300 LBS LOW.  MAINT INSPECTED SYS AND ISOLATED THE PROBLEM TO THE RT AUX FUEL TANK PROBE. UPO	N A CLOSER INSP IT WAS DISCOVERED THAT THE PROBE HSG AT SEPARATED FROM THE SENDING UNIT. THE PLASTIC RIVETS HAD SHEARED.	 THE PARTS WERE RECOVERED FROM THE AUX TANK AND WERE ALL ACCOUNTED FOR. A NEW SERVICEABLE UNIT WAS INSTALLED AND THE SYS	 WAS TESTED SERVICEABLE.		2	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P56GL	 
	20090106		NE  	2009	1	6	CA081203002      	2	20081125	G	7200		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					RIGHT	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL WITH PASSENGERS ON BOARD POWER WAS ADVANCED THROUGH 70 PERCENT TORQUE. A THUD AND GRINDING NOISE W	AS HEARD FROM THE RT SIDE. TAKEOFF WAS ABORTED AND AC RETURNED TO THE GATE.  ENG TO BE REMOVED AND SENT FOR INVESTIGATIO	N.  MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20090106		EA  	2009	1	6	CA081203003      	2	20081125	G	7200		ENGINE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  						MALFUNCTIONED   	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKE OFF OIL MIST IN CABIN WAS DETECTED. THE ACFT IMMEDIATELY TURNED BACK, DECLARED AN EMERGENCY, AN	D LANDED. THE LOCAL AIRWORTHINESS AUTHORITIES ARE INVESTIGATING THE EVENT. POST FLIGHT INSP REVEALED OIL IN THE VICINITY	 OF THE P2.2 BLEED VALVE. INSP AND BORESCOPE SHOWS LP COMPRESSOR AND BLEED VALVES WET. NO EVIDENCE OF DISTRESSED COMPONE	NTS. EMU DATA REQUESTED. ENGINE BEING REMOVED FOR INVESTIGATION AT MFG. UPDATES WILL BE PROVIDED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20090106			2009	1	6	CA081203004      	1	20081118	G	6420	S611033406101	SPINDLE         		S61TRH      															TAIL ROTOR	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			3464 	1747 							(CAN) S61 TAIL ROTOR SPINDLE FAILED NITAL ETCH INSP IAW SB61B10-18J  S/N`S K071-00144, K071-00132, K071-00137.																			 
	20090107		EA  	2009	1	7	CA081203005      	2	20080502	G	7250		TURBINE         			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					RT ENGINE	DAMAGED         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											(CAN) ACFT CRASHED UNDER UNKNOWN CIRCUMSTANCES. DURING THE FLT, THE PILOT RADIOED THAT HE HAD A LOSS OF PWR FROM ONE ENG	 FOLLOWED BY A "MAYDAY" CALL, APPROX 14 MIN LATER, DURING WHICH HE SAID THE SECOND ENGINE STOPPED OPERATING. THE ACFT WA	S EQUIPPED WITH A FDR AND CVR. EXAMINATION OF ENGINES, REVEALED THE LT ENGINE DISPLAYED ROTATIONAL SIGNATURES CHARACTERI	STIC OF THE ENGINE DEVELOPING POWER AT IMPACT. NO PRE-IMPACT ANOMALIES EVIDENT. THE RT ENGINE DISPLAYED EVIDENCE OF PRE-	IMPACT DISTRESS CONSISTING OF THE FRACTURE AND RELEASE OF COMPRESSOR TURBINE (CT) BLADE MATERIAL DUE TO CONTACT WITH A P	ROTRUDING CT BLADE SHROUD SEGMENT. THE CT DISK, VANE AND SHROUD ASSY WAS REQUESTED TO BE RETURNED TO MFG FOR DETAILED EX	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20090106			2009	1	6	CA081203006      	1	20081202	G	6420	S611033406	SPINDLE         																	TAIL ROTOR	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1748 	1747 							(CAN) S61 TAIL ROTOR SPINDLE FAILED INITIAL ETCH INSP IAW SB61B10-18J  S/N`S K071-00394, K071-00392.																			 
	20090102		NE  	2009	1	2	CA081203007      	2	20081126	G	7200		ENGINE          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       	 	NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB AT FL60, THE CREW NOTICED A LOW ENGINE OIL PRESSURE LIGHT, FOLLOWED BY A POPPING NOISE. THE ENG WAS S	HUTDOWN AND THE ACFT WAS DIVERTED BACK TO BASE. GROUND INSP FOUND THE TURBOMACHINE CHIP DETECTOR COVERED WITH METAL SHAV	INGS AND THE LP AND HP ROTORS INCAPABLE OF ROTATION. THE ENG HAD RECENTLY UNDERGONE A HOT SECTION INSP. MFG WILL CONTINU	E INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
	20090102		NE  	2009	1	2	CA081203008      	2	20081128	G	7323		GASKET          			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					OVRSPD GOVERNOR	TORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AT TOP OF CLIMB, OIL PRESSURE FLUCTUATION WAS REPORTED FOLLOWED BY LOW OIL PRESSURE INDICATION. THE ENGINE WAS SHU	TDOWN BY THE PILOT. ON RETURN TO GATE, THE ENG COWL WAS FOUND COVERED WITH OIL. OVERSPEED GOVERNOR GASKET FOUND DETERIOR	ATED. GASKET WAS REPLACED.				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
	20090102		NE  	2009	1	2	CA081203009      	2	20081125	G	7321	7898422009L6	EEC             			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED SHUTTING ENGINE DOWN IN FLIGHT DUE TO EXCESSIVE TORQUE FLUCTUATIONS. EEC WAS REPLACED AND DEFECT RE	CTIFIED. THE SUSPECT EEC HAS BEEN SENT FOR INVESTIGATION. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT C	AUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20090102		NE  	2009	1	2	CA081203010      	2	20081027	G	7297		WIRE HARNESS    			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				R	F		PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         		CR	CRUISE         	1			CA											(CAN) THE ENG EXPERIENCED REPEATED EVENTS OF TORQUE FLUCTUATIONS BETWEEN THE 20TH AND 24TH OF OCTOBER FOR WHICH TROUBLES	HOOTING HAD BEEN DONE. ON OCT. 27, THE PROBLEM RE-APPEARED AND WAS ACCOMPANIED BY NO RESPONSE TO THROTTLE MOVEMENTS. THE	 ENGINE WAS SHUTDOWN AND RE-STARTED IN MANUAL MODE WITH NO FURTHER PROBLEMS TILL THE FLIGHT ENDED. FURTHER TROUBLESHOOTI	NG LED TO THE REPLACEMENT OF THE FUEL CONTROL AND ENGINE WIRING HARNESS, WHICH HAVE BEEN SENT FOR INVESTIGATION. MFG WIL	L CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
	20090102		NM  	2009	1	2	CA081203011      	1	20081202	G	2710	85711569001	BRACKET         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	AILERON CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			42293								(CAN) LT AILERON INPUT BRACKET FOUND CRACKED.  LT AILERON QUADRANT BRACKET REMOVED P/N 85711569-001.  POST S/B 8-57-27 Q	UADRANT BRACKET TO BE INSTALLED.  NEW BRACKET IS IN SHEET METAL SHOP.  REMOVED AND REPLACED NEW LT AILERON QUADRANT BRAC	KET IAW SB 8-57-27. LT WING AILERON TERMINAL QUADRANT,  PREVIOUSLY REMOVED FOR SHEET METAL ACCESS, INSTALLATION COMPLETE	D AS IAW AMM 27-12-31 TOTHE END OF STEP 12.  INDEPENDENT INSP CARRIED OUT ON DEFECT 814228. M7109 FUNCTION TEST 1.C. COM	PLETED FOR THOSE PORTIONS OF THE SYS THAT HAVE BEEN DISTURBED AND FOUND TO WORK NORMALLY M7128.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090102		WP  	2009	1	2	CA081203012      	1	20081126	G	6120	6506196	VALVE           			CVAC  	580   	580         	2422806	WP  										PROP PITCH LOCK	FAILED          	W				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) IN FLIGHT, CREW EXPERIENCED A FAILURE OF THE NR 2 ENG PITCH LOCK VALVE. ENGINE WAS E-HANDLED AND AC LANDED WITHOUT	 INCIDENT. MAINT REPLACED THE NR 2 PITCH LOCK VALVE AND ACFT RETURNED TO SERVICE.					2	L	7	2 	4T			RT	        					 
	20090102		EA  	2009	1	2	CA081204001      	1	20081202	G	2820	CN6273003001	PIPE            			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C5     	30050	NE  					FUEL FLOW	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			9796 	9796 							(CAN) MX FOUND NR1 ENGINE MOTIVE FLOW PIPE CHAFED LEAKING FUEL. PIPE WAS REPLACED, ENGINE RUNS AND LEAK CHECKS COMPLETED	 SATISFACTORY. CAUSE OF CHAFING COULD NOT BE CONFIRMED. IT WAS REPORTED THAT THE NEAREST DRAIN LINE WAS AT LEAST .5 INCH	 AWAY AND ALL SEEMED PROPERLY SECURED.				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20090102		NM  	2009	1	2	CA081204002      	1	20081108	G	2497		WIRE            			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ALTERNATOR	DAMAGED         	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) NR1 AND NR2 AC GEN ANNUNCIATIONS ILLUMINATED DURING TAXI. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE FOLLOWI	NG DISCREPANCY HAD OCCURED.  FOUND WIRE 2421-10002FILB-1 AND WIRE 2421-2000IGI2A-1 WORN THROUGH AND SHORTED AT STA YH59:	00 ON LT WING REAR SPAR.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090102		EU  	2009	1	2	CA081204003      	1	20081204	G	2710	04820203	SENSOR          			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	LT AILERON	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FDR CORRELATION CHECK REVEALED LT AILERON ROLL SENSOR UNSERVICEABLE.  SENSOR INSPECTED.  OPERATING CABLE FRAYED AN	D BINDING. SENSOR REPLACED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20090102		NE  	2009	1	2	CA081204005      	3	20081204	G	6111	SFA13MIROASK112	BLADE           			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF5       	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				6717 							(CAN) LEADING EDGE NICKEL SHEATH VISUALLY INSPECTED AND A CRACK NOTED. IF PRESSURE APPLIED TO BLADED CRACK BECAME MORE N	OTICEABLE. BLADE REMOVED FROM SERVICE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
	20090102		NM  	2009	1	2	CA081204006      	1	20081203	G	3397		WIRE            			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	CABIN LIGHT	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			42386								(CAN) SPARKS/SMOKE FROM SIDEWALL LIGHT 1C, BALLAST CONFIRMED THE SOURCE. CREW DROPPED PSU PANEL TO FUND THE SOURCE AND C	ONFIRM SHORTING OF THE FORE/AFT WIRES TO THE AFT JUNCTION BOX.  WIRING REPAIRED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090204		EA  	2009	2	4	CA081204007      	1	20081202	G	3234		SHAFT           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					MLG HANDLE	WORN            	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING MX OPERATION OF THE LANDING GEAR MANUAL RELEASE HANDLE IT STUCK IN THE RELEASE POSITION.  MX TROUBLESHOOTIN	G FOUND THE RELEASE HANDLE SHAFT BINDING DUE TO INTERNAL WEAR AND SLIGHTLY BENT.  RELEASE HANDLE ASSY WAS REPLACED IAW A	MM 32-34-01.  ACF TT 14745 HOURS, 123110 CYCLES.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081229		SW  	2008	12	29	CA081204008      	1	20081127	G	5210	4744	HINGE PIN       			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  	MCAULY	1A200	1A200*      	GL  	PAX DOOR	RUSTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AN ATTEMPT TO REMOVE THE ENTRANCE DOOR USING THE EMERGENCY EXIT HANDLE FOUND THAT THE SYS HAD BECOME SEIZED.   UPO	N CLOSER INSP, IT WAS FOUND THAT THE HINGE PIN (DISPITE PERIODIC LUBING) HAD BECOME RUSTED TO THE AIRFRAME PIN TABS. THE	 DOOR CONTINUED TO OPEN AND CLOSE PROPER USING THE NORMAL SYS. THE ONLY SYS THAT FAILED IS THE JETTISON PORTION OF THE S	YS. THE MM DOES NOT CALL FOR LUBBING OR FUNCTION CHECKING THIS SYS. IT HAS BEEN APPROXIMATELY 2000 HRS SINCE THE LAST RE	CORDED REMOVAL OF THE DOOR.		1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
	20081219		CE  	2008	12	19	CA081204009      	1	20081201	G	7820	175400125	MUFFLER         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			799  								(CAN) WHILE CARRYING OUT AD CF90-03R2 A SMALL LEAK WAS NOTED AT THE TOP OF THE EXHAUST PIPE JUNCTION WITH THE MUFFLER BO	DY.  THIS IS A COMMON PLACE FOR THESE MUFFLERS TO FAIL.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081219		CE  	2008	12	19	CA081204010      	1	20081201	G	7820	175400122	MUFFLER         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1611 								(CAN) DURING PREFLIGHT INSPECTION, A 2" CRACK IN THE END OF TAILPIPE WAS NOTED, RUNNING PARALLEL TO THE PIPE AXIS. THE C	RACK APPEARS TO BE AT THE EDGE OF A HOT SPOT CAUSED BY THE WAY THE EXHAUST GASES FLOW OUT OF THE PIPE AND MAY HAVE BEEN 	A RESULT OF THERMAL STRESSES SET UP BY UNEVEN HEATING.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081222		NM  	2008	12	22	CA081204011      	1	20081129	G	2931	7G773	PRESSURE SWITCH 			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) NR 2 EDP AMBER LIGHT CAME ON AT 30 KTS. DURING TAKE-OFF ROLL.  ABORTED TAKE-OFF.  PRESS WAS NORMAL ON THE INDICATO	R, BUT THE NR 2 EDP AMBER CAUTION LIGHT IS ON. TR128.  CONNECTOR ON PRESSURE SWITCH CLEANED.  NR 2 SYSTEM HYD PRESSURE S	WITCH REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090204		EA  	2009	2	4	CA081204012      	1	20081202	G	5610	NP139321003	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, RT (F/O) WINDSHIELD SHATTERED, WITH NO LOSS OF PRESSURIZATION.  CAPTAIN DESCENDED AND DECLARED AN E	MERGENCY LANDING RT WINDSHIELD (P/N OFF: NP139321-003) CHANGED IAW AMM 56-11-01.					2	L	7	2 	4F			RT	A21EA   					 
	20090204		NE  	2009	2	4	CA081204013      	2	20081127	G	7261	GE6087T04P0	SCREEN          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					SCAV PUMP	OBSTRUCTED      	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			21013								(CAN) IFSD EN ROUTE FROM PHL - PIT.  LOSS OF ENGINE OIL PRESSURE AT FLIGHT FL340.  LEFT ENGINE RED OIL PRESSURE CAS MESS	AGE ILLUMINATED.  OIL PRESSURE READ 23 PSI PRIOR TO ENGINE SHUTDOWN.  OIL TEMP WAS NORMAL PRIOR TO ENGINE SHUTDOWN.  AIR	CRAFT WAS DIVERTED MADE AN UNEVENTFUL LANDING AT PIT.  INSPECTION BY MAINTENANCE REVEALED COKING AROUND THE SCREEN.  LUB	E PUMP WAS REMOVED AND REPLACED IAW TO 70-21-01.  AIRCRAFT RETURNED TO SERVICE WITH NORMAL OPERATION.  (TC NR 2008120401	3)		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081219		NE  	2008	12	19	CA081205001      	2	20080723	G	7200		ENGINE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2	DAMAGED         	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CA				9400 							(CAN) AN ACFT RETURNED TO BASE DUE TO ENGINE NR 2 FIRE WARNING LIGHT ILLUMINATE.  ENGINE FOUND DAMAGED AND REMOVED FOR I	NVESTIGATION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20081229			2008	12	29	CA081205002      	4	20081123	G	3400	8221577202	DISPLAY         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					MFD 1	INOPERATIVE     	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			CA											(CAN) 30 MINUTES PRIOR TO LANDING, THE PILOT PRIMARY FLIGHT DISPLAY(PFD 1) WENT BLANK. THEN IAW AFM (SECTION 05-15-1) TH	E CREW SELECTED THE REVERSION MODE TO HAVE THE MULTIFUNCTION DISPLAY (MFD 1) IN COMPRESSED MODE, AT THAT TIME THE MFD 1 	ALSO WENT BLANK. THE CREW RESELECTED REVERSION TO NORMAL, BOTH DISPLAY RETUNED TO NORMAL. APPROXIMATELY 10 MINUTES LATER	, THE PFD 1 BLANK AGAIN AND OPERATED ON AND OFF EVERY 2- 3 MINUTES UNTIL LANDING. CONDITION WAS NO LONGER PRESENT AFTER 	FLIGHT AND REVERSION SYS WORKED NORMALLY. WIRING VERIFICATION DONE NO ANOMALY NOTED. AFD (PFD 1 POSITION) REPLACED IAW A	MM 31-61-00. THE MFD 1 (P/N: 822-1917-202 S/N: 2NKRG) WAS ALSO REPLACED BUT A PRECAUTIONARY MEASURE . ACFT RETUNED TO SE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20081222		EA  	2008	12	22	CA081205003      	1	20081204	G	5720		SUPPORT BRACKET 			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT WING AILERON INPUT QUADRANT SUPPORT BRACKETS AT YW414.00 CRACKED.  QUADRANT SUPPORT BRACKETS REPLACED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20090203		SW  	2009	2	3	CA081205004      	1	20081126	G	7603	C8102415	CONTROL CABLE   			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					POWER LEVER	BROKEN          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) DURING TAXI, CREW SELECTED SPEEDS HIGH & APPLIED POWER.  AS POSITIVE TORQUES WERE CALLED TROUGH ABOUT 1200FT/LBS, 	A SNAP WAS HEARD & THE LT POWER LEVER ADVANCED FORWARD WITH NO FURTHER ENGINE POWER INCREASE.  TAKEOFF ABORTED & CREW SL	OWLY REDUCED POWER TO FLIGHT IDLE.  LT ENGINE DID NOT RESPOND TO FURTHER POSITIVE POWER LEVER INPUTS BUT WOULD RESPOND W	HEN REDUCED TO FLT IDLE.  ACFT TAXIED BACK TO APRON & SHUTDOWN.  MX DETERMINED LT ENGINE POWER LEVER CABLE SECTION FROM 	POWER LEVER QUADRANT TO WING ROOT HAD BROKEN.  NO DEFINITIVE CAUSE FOR BREAK DETERMINED BUT IT WAS AT THE POINT WHERE PR	OPER ROUTING OF CABLE REQUIRES A SIGNIFICANT BEND IN CABLE ASSY.  CABLE REPLACED & ACFT RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20081229		NM  	2008	12	29	CA081205006      	1	20081202	G	3240	244300	STATOR          	BFGOODRICH  		BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					BRAKE ASSY	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PUSHBACK ON C-FCJF EXCESSIVE FORCE WAS REQUIRED TO MOVE ACFT AND DETERMINED NR2 MAIN WHEEL WAS DEFLATED. AC	FT PULLED BACK TO GATE FOR INVESTIGATION.  MAINT WAS UNABLE TO REMOVE NR2 WHEEL. AFTER SEVERAL EFFORTS WITHOUT SUCCESS I	T WAS DECIDED THE TIRE AND POSSIBLY THE WHEEL WOULD HAVE TO BE CUTOFF.  AFTER CUTTING A SECTION OF THE TIRE OFF IT WAS D	ETERMINED A PIECE OF THE BRAKE STATOR HAD BROKEN OFF AND PENETRATED THE WHEEL HUB AS THE ACFT WAS TOWED DEFLATING THE TI	RE AND MAKING IT IMPOSSIBLE TO REMOVE WHEEL. THE BROKEN PIECE OF THE STATOR WAS REMOVED ALLOWING REMOVAL OF THE WHEEL.  	 WHEEL AND BRAKE ASSY REPLACED.	2	L	7	3 	4F	4	F		A3WE    	E2EA				 
	20081222		CE  	2008	12	22	CA081205007      	1	20081204	G	3710	5100106377	LINE            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	VACUUM SYS	CORRODED        	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			5291 								(CAN) UPON REACHING CRUISE FLIGHT AND ACTIVATING AIRFRAME PNEUMATIC DE-ICE SYSTEM, THE BOOTS WOULD REMAIN PARTIALLY TO M	OSTLY INFLATED.  THIS PROBLEM WOULD NOT DUPLICATE ON A GROUND RUN.   THE VACUUM LINE TO THE FLOW VALVES WAS INSPECTED AN	D A LINE ASSEMBLY TO THE TAIL FLOW VALVE WAS FOUND CORRODED WHERE IT PASSED OVER AN ENVIRONMENTAL DUCT AT APPROX. MID CA	BIN.  THE LINE ASSEMBLY WAS REPAIRED.   THE ACFT WAS GROUND RUN AND FLOWN TO CRUISE ALTITUDE TO MAX. CABIN PRESSURE DIFF	ERENTIAL, AND THE PNEUMATIC DE-ICE SYSTEM FUNCTIONED PROPERLY.		1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
	20081229		SW  	2008	12	29	CA081205008      	1	20081204	G	5610	HYLZ88821	WINDSHIELD      			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	29073	NE  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE LT WINDSHIELD SHATTERED. MX WAS DISPATCHED TO REPLACE THE WINDSHIELD. THE TEMP CONTROLLER WAS FOUN	D TO BE DEFECTIVE ALSO.  TEMP CONTROLLER REPLACED ALONG WITH WINDSHIELD AND ACFT RETURNED TO SERVICE.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
	20081219		EA  	2008	12	19	CA081207001      	2	20081202	G	7414	106006169	MAGNETO         								LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA				302  							(CAN) AFTER START MAG CHECK PERFORMED AND LT MAG FAILED.  MX WAS NOTIFIED AND WHEN MAG WAS LOOKED AT FOUND THAT THE BREA	KER POINT WIRES HAD VIBRATED OFF.  WIRES REPAIRED AND REINSTALLED.										3	O			E295				 
	20081219		CE  	2008	12	19	CA081208001      	1	20081119	G	3222	SK1759	FORK            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	NOSE GEAR	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			15146	15146							(CAN) ON ROLL OUT FROM LANDING NOSE WHEEL BROKE OFF.  ACFT SLID APPROX. 400` ON NOSE AND CAME TO A STOP.  APPARENT CAUSE	 METAL FATIGUE OF NOSE WHEEL FORK.  TSB HAS SECURED FAULTY PARTS AND INVESTIGATING FURTHER.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20081222		NM  	2008	12	22	CA081208002      	1	20081207	G	3231	483023	SEQUENCE VALVE  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					LT MLG DOOR	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA				1398 							(CAN) FLIGHT CREW REPORT: LT MAIN AMBER GEAR DOOR LIGHT FAILED TO EXTINGUISH ON GEAR RETRACTION (VISUALLY OPEN). ALT EXT	ENSION PERFORMED.  REPLACED LT MLG SSV IAW 32-31-41					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20081222		SO  	2008	12	22	CA081208005      	1	20081208	G	8120		BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					TURBOCHARGER	FAILED          	W				A	D			UNSCHED LANDING         	RETURN TO BLOCK         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA				36   							(CAN) SHORTLY AFTER TAKE-OFF THE PILOT HEARD A "BANG" FROM THE RT ENGINE AND NOTICED A LOSS OF MANIFOLD PRESSURE.  HE TH	EN RETURNED TO THE AIRPORT WITH NO PROBLEMS ENROUTE.  MX FOUND THE TURBO CHARGER SHAFT BEARING HAD FAILED.  THE TURBO CH	ARGER WAS REPLACED, OIL SUMP CLEANED, OIL FILTER REPLACED AND GROUND RUN ACCEPTABLE.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20090204		EU  	2009	2	4	CA081208007      	1	20081201	G	2435	23085024	STARTER GEN     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 1	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				54   							(CAN) PILOT REPORTED WAS NR 1 GENERATOR WENT OFF LINE PRIOR TO TAKEOFF.  WAS UNABLE TO RESET RETURNED TO BLOCKS.  NR 1 G	ENERATOR REPLACED AND GROUND RUN PERFORMED, ALL FOUND SATISFACTORY. (TC NR  20081208007)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20090205		CE  	2009	2	5	CA081208008      	1	20081208	G	2435	200SGL119Q2	STARTER GEN     			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  		FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				110  							(CAN) GENERATOR FAILED IN FLIGHT 12 MILES FROM YWG ENROUTE TO YQT.  AIRCRAFT RETURNED TO YWG (TC NR 20081208008).						1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
	20090205		NM  	2009	2	5	CA081208009      	1	20081201	G	5751		BRACKET         			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE INSPECTION BOTH THE LT AND RT AILERON QUADRANT SUPPORT BRACKETS WERE FOUND CRACKED.  PART NUMBE	RS INCLUDED, LT END PIECE P/N 85711570-101, RT END PIECE P/N 85711570-102, LT BOTTOM PLATE P/N 85711572-101, RT BOTTOM P	LATE 85711572-102, OF NOTE WHEN THE RT END PIECE WAS REMOVED THERE APPEARED TO BE EVIDENCE OF AN APPARENT PREVIOUS WELD 	REPAIR OF UNKNOWN ORIGIN.  A CHECK OF THE AIRCRAFT MAINTENANCE HISTORY COULD NOT FIND A RECORD OF SUCH A REPAIR.  ALL CR	ACKED BRACKETS WERE REPLACED.  (TC NR 20081208009)		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20081222			2008	12	22	CA081208011      	1	20081126	G	7830	9007M60G46	COWLING         								GE    	CF6   	CF650C2     	30018	NE  					THRUST REVERSER	DELAMINATED     	W				E				ENGINE SHUTDOWN         				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		DE	DESCENT        	1			CA											(CAN) ON DESCENT INTO YYC, WITH POWER LEVERS AT IDLE, THE ACFT SHUDDERED MOMENTARILY.  THE NR 2 THRUST REVERSER UNLOCK L	IGHT ILLUMINATED AND IN-FLIGHT SHUT DOWN OF NR 2 ENGINE WAS CARRIED OUT.  THE ACFT LANDED WITHOUT INCIDENT AND AN INSPEC	TION WAS CARRIED OUT ON NR 2 ENGINE.  NR 2 ENGINE RT TRANSLATING COWL WAS FOUND DELAMINATED WITH A SECTION OF THE COWL M	ISSING.  THE COWL WAS REPLACED, FUNCTION CHECKED AND THE ACFT RETURNED TO SERVICE.								4	F			E23EA				 
	20090203		EA  	2009	2	3	CA081209005      	1	20081208	G	5711	215003268	SPAR CAP        			CNDAIR	CL215 	CL2151A10   	1900320	EA  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4895 								(CAN) WHILE PERFORMING AD 92-26R1 NO DEFECTS WERE FOUND DURING ULTRASONIC INSPECTION OF REQUIRED INSPECTION AREA.  DUE T	O PREVIOUS CONCERNS (3) WITH FINDING CRACKS OUTSIDE OF INSPECTION AREA FURTHER INVESTIGATION WAS PERFORMED.  CRACKS WERE	 FOUND IN LOWER SPAR CAP, LOWER WING SKIN AND BOTH REINFORCING STRAPS.				2	H	7	2 	4R			RT	A14EA   					 
	20081222		SW  	2008	12	22	CA081209006      	1	20080611	G	6300	206040015103	DRIVE SHAFT     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R DRIVE	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) ON DESCENT PILOT SMELLED BURNING GREASE.  AFTER LANDING AND POST FLIGHT INSPECTION FOUND GREASE THROWN FROM DRIVES	HAFT COUPLING. DRIVESHAFT WAS REPLACED AND FOUND ISOLATION MOUNT TO BE WEAK.  REPLACED ISOLATION MOUNT AND PROBLEM WENT 	AWAY.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
	20081222		CE  	2008	12	22	CA081210001      	1	20081108	G	3245	5005	TUBE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					MLG TIRE	TORN            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE NOSE TIRE INNER TUBE HAD 195 HRS SINCE NEW.  IT WAS FOUND RIPPED. NO HARD LANDING WAS REPORTED.  THE INSIDE OF	 THE TIRE WAS FOUND FREE OF ANY DEFECTS.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081222		CE  	2008	12	22	CA081210002      	1	20081208	G	3245	5005	TUBE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					NLG TIRE	TORN            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE NOSE WHEEL TIRE INNER TUBE HAD 220 HRS SINCE NEW.  IT WAS FOUND TORN ON THE SIDE WALL.  NO HARD LANDING WAS RE	PORTED.  THE INSIDE OF THE TIRE WAS FOUND FREE OF DEFECTS.  THIS TO ME IS AN OBVIOUS MANUFACTURING PROBLEM.  IT HAPPENED	 ON TAXI FROM THE RUNWAY AFTER NORMAL LANDING.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
	20081222		SO  	2008	12	22	CA081210003      	1	20081208	G	3245	5005	TUBE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					NLG TIRE	TORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			391  								(CAN) THE NOSE WHEEL TIRE INNER TUBE WAS FOUND TORN.  THE ACFT SAT OVER NIGHT.  THE INNER TUBE HAD 391 HRS SINCE NEW.  T	HE NOSE TIRE WAS INSP, NO DEFECTS FOUND.					1	L	7	1 	3O	3	O		2A13    	E274				 
	20090203		GL  	2009	2	3	CA081210004      	1	20081209	G	2421	A3579101	GENERATOR       			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  					APU	FIRE            	W				O				OTHER                   				A	B	J	FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	DE	DESCENT        	1			CA											(CAN) AFTER APU START AT FL100 JUST BEFORE APU GEN ON LINE APU FIRE CAS MESSAGE POSTED.  PILOTS ARM APU BOTTLE MESSAGE D	ISAPPEARED.  PILOTS SHUTDOWN APU AND LAND A/C SAFELY.  IN AFT EQUIPMENT BAY PILOTS NOTED AN ODOR OF BURNED WIRE.  AFTER 	INSPECTION OF APU GENERATOR FOUND GENERATOR ON FIRE.  FIRE WENT OUT VIA COOLING DUCT TO EDUCATOR SENSING ELEMENT OF APU 	FIRE DETECTION SYSTEM.  APU DOOR SHOWING SIGNS OF FIRE.			2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
	20081222		NM  	2008	12	22	CA081210005      	1	20081209	G	3213	654611635	CYLINDER        			BOEING	737   	737232      	1384475	NM  	PWA   	JT8   	JT8D17      	52049	NE  					STRUT	WORN            	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			37952	16636							(CAN) RT MLG LOST FLUID.  DURING ATTEMPTED SEAL CHANGE, THE INNER CYLINDER OF THE GEAR HAD A 6" BY 2" PIECE OF CHROME MI	SSING FROM THE INNER CYLINDER.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
	20090203		CE  	2009	2	3	CA081210006      	1	20081208	G	5220	115430100661A	SKIN            			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					EMERGENCY EXIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9902 								(CAN) WHEN COMPLYING WITH SPECIAL INSPECTION "ESCAPE HATCHES AND ASSOCIATED AREAS", A CRACK WAS FOUND AT THE LOWER FORWA	RD CORNER OF THE BONDED RT EMERGENCY EXIT DOOR SKIN, EXACTLY AS PICTURED IN THE MAINTENANCE MANUAL.  REPLACED SKIN ASSEM	BLY WITH NEW.  CRACKS ARE DIFFICULT TO DETECT DUE TO FILLER USED BY THE MANUFACTURER TO BLEND THE RADIUS AFTER FITTING T	HE SKIN.  OUR INSPECTION TSK IS AMENDED TO INDICATE THE INTERIOR PANEL IS TO BE REMOVED AND INSPECTED FROM THE INSIDE.  	HIGH TIME/HIGH CYCLE B300 OF OUR FLEET OF FIVE AIRCRAFT.		2	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20081229		NE  	2008	12	29	CA081210008      	2	20081204	G	7250	FW45914	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				5094 							(CAN) SURGE/IFSD/ENGINE SHUTDOWN IN FLIGHT WITH TGT CLIMBING THROUGH 1100 C.   BOROSCOPE OF ENGINE 13299 TODAY FOUND THA	T 2 OFF HPT STAGE 1 BLADES SUFFERED FROM A BELOW-PLATFORM FAILURE. THE 2 FAILED BLADES ARE SEPARATED BY 28 BLADES. THE A	IRFOILS ON ALL OF THE REMAINING BLADES HAVE BEEN KNOCKED OFF ABOVE THE PLATFORM.				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
	20081222		NE  	2008	12	22	CA081210009      	2	20081201	G	7200		ENGINE          			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	120   	PW120       	 	NE  						ODOR            	W				E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE PILOTS NOTICED OIL ODOR AND MIST IN THE CABIN.  THEY TURNED THE AIR BLEED FROM THE ENGINE OFF A	ND THE MIST AND ODOR DISAPPEARED.  SOON AFTER, OIL PRESSURE FLUCTUATIONS AND THEN A DROP IN PRESSURE OCCURRED.  THE PILO	TS SHUT DOWN THE ENGINE AND PERFORMED A SINGLE ENGINE LANDING.  GROUND INSPECTION FOUND LOW OIL LEVEL, BOROSCOPE INSPECT	ION OF THE AIR INLET WAS MADE AND REVEALED OIL LEAK FROM C OR D FLANGE AND THE REAR INLET CASE IS FLOODED WITH OIL.  THE	 ENGINE WILL BE REMOVED.  MANUFACTURER WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.		2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
	20081229		NE  	2008	12	29	CA081210010      	2	20081127	G	7200		ENGINE          			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  						POWER LOSS      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB AFTER T/O, ENGINE POWER LOSS OCCURRED (AT APPROX 300 FT ALTITUDE). THE ENGINE WAS SECURED AND A TURNB	ACK INITIATED. THE ACFT MADE A SINGLE ENGINE LANDING. POST EVENT INSP FOUND FRACTURED HP BLADES. MFG WILL CONTINUE INVES	TIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
	20090203		EA  	2009	2	3	CA081210011      	2	20081210	G	7200		ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					NR 1	SHUTDOWN        	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) NR 1 ENGINE SHUTDOWN CARRIED OUT AFTER TAKEOFF.  HERE IS THE DEFECT ENTERED BY THE FLIGHT CREW "LT PROP RPM ONLY G	OES TO 1500 RPM ON TAKEOFF AS POWER REDUCED RPM DROPS".  THE INCIDENT IS UNDER INVESTIGATION.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
	20090203		EU  	2009	2	3	CA081210012      	1	20081208	G	5530	313108	BRACKET         			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9341 								(CAN)  FOUND CRACK IN BRACKET LOCATED ON THE FORWARD SIDE OF THE VERTICAL STAB ATTACH FITTING AT FS 521.75.  THREE CRACK	S EXTEND FROM THE RIGHT OUTBOARD ATTACHMENT BOLT HOLE.  THE ATTACHING BOLTS RUNS HORIZONTALLY FWD AND AFT THROUGH THE RU	DDER STOP BRACKET, VERTICAL STAB ATTACH FITTING, AND THROUGH THE BRACKET (P/N: 313108) WHICH IS CRACKED.  REFERENCE IPC:	 53-40-00 FIG 1 (SHEET 2) PAGE 1, PART SHOWN DIRECTLY BELOW ITEM 32.			2	M	7	2 	4F	4	F		A2SW    	E6WE				 
	20081222		NE  	2008	12	22	CA081210013      	2	20081128	G	7414	BL600646201	MAGNETO         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					ENGINE	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAGNETO FOUND U/S.						1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20081229		EA  	2008	12	29	CA081211002      	3	20080116	G	6111	W69EK763	PROPELLER       			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	TIP OF BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			354  								(CAN) PRIOR TO A TRAINING FLIGHT WITH A STUDENT A WALK AROUND WAS PERFORMED ON THE ACFT WHERE IT WAS NOTED THAT ONE OF T	HE PROPELLER BLADE LEADING EDGE TIPS HAD AN INDICATION OF POSSIBLE ROCK CHIP DAMAGE OF APPROXIMATELY .2500 INCH IN LENGT	H AND LESS THAN A .0625 INCH IN DEPTH.  IT SHOULD ALSO BE NOTED THAT THE PREVIOUS CREW HAD REPORTED A SLIGHT ENGINE VIBR	ATION AT 1700 RPM. UPON INSP BY AN AME IT WAS DETERMINED THAT IN FACT THERE WAS A SLIGHT NICK POSSIBLY CAUSED BY A SMALL	 ROCK. UPON FURTHER INVESTIGATION A CRACK WAS FOUND THAT WAS LOCATED AT THE MIDPOINT OF THE BLADE AT THE VERY TIP AND EX	TENDED INWARD APPROX 2 INCHES. BY APPLYING PRESSURE TO EITHER OPPOSING SIDES OF THE BLADE TIP THE CRACK BECAME VERY APPA	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20081229		EA  	2008	12	29	CA081211003      	3	20081110	G	6111	W69EK763T	PROPELLER       			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	TIP OF BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			331  								(CAN) IN BETWEEN AND PRIOR TO A TRAINING FLIGHT THE PILOT AND STUDENT CONDUCTED A WALK AROUND WHERE IT WAS NOTICED THAT 	ON THE NR1 BLADE TIP THERE APPEARED TO BE A CRACK EMANATING FROM THE CENTER OF THE BLADE TIP WHICH EXTENDED INWARD TOWAR	DS THE ROOT. AN AME CONDUCTED A VISUAL INSPECTION UNDER 10X MAGNIFICATION AND VERIFIED THAT A CRACK EXISTED FROM THE CEN	TER OF THE NR1 BLADE TIP AND EXTENDED APPROX 2 INCHES INWARD TRAVELLING TOWARDS THE BLADE ROOT. THE AIRCRAFT WAS IMMEDIA	TELY REMOVED FROM SERVICE WHERE A NEW PROPELLER ASSEMBLY WAS INSTALLED.		1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
	20090203		NM  	2009	2	3	CA081211004      	1	20081203	G	5310	85312397101	BRACKET         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	WINDOW	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING THE ACCOMPLISHMENT OF TASK 5310/06C, WINDSHIELD AND SIDE WINDOW LOWER SILL JOINT TO SIDE POST, THE BRACKET 	CONNECTED TO UNDERSIDE OF THE LOWER SILL TO THE SIDE POST (RIGHT SIDE) WAS FOUND TO HAVE A 2 1/2 INCH CRACK IN IT.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090206		EA  	2009	2	6	CA081211005      	1	20081204	G	5330	21530023	SKIN            			CNDAIR	CL215 	CL2156B11215	       	EA  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A MX INSPECTION, AN EMPLOYEE FOUND A CRACK ON THE TOP SKIN FS 388 RSTR 9. DWG 215-30023-175 AOM 53-30-00-10	3 REV A.					2	H	7	2 	4T			RT	A14EA   					 
	20081222		CE  	2008	12	22	CA081212002      	1	20081205	G	2421		BEARING         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ALTERNATOR	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA				16   							(CAN) IN CRUISE PILOT NOTICED SPARKS COMING FROM RT ENGINE.  UPON EXAMINATION ON GROUND BY MX, ALTERNATOR OUTER BRG. FAI	LED.  SHAFT DEFORMED FROM HEAT.  FAILURE OF CRANKSHAFT ALTERNATOR DRIVE GEAR CAUSED MAJOR INTERNAL ENGINE DAMAGE.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
	20090203		NE  	2009	2	3	CA081212003      	2	20081212	G	7320	J2009P03	PLUG            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					MFC	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE CHECK, A FUEL LEAK WAS DISCOVERED COMING FROM THE NR 2 ENGINE MFC.  UPON FURTHER INVESTIGATION A 	PLUG WAS FOUND LOOSE.  THE PLUG WAS REMOVED, THE O-RING REPLACED AND THE PLUG RE-INSTALLED.  A LEAK CHECK WAS CARRIED OU	T WITH NO LEAKS NOTED IPC REF IS 73-11-00, FIG. 5-380.  A RECORDS CHECK WAS CARRIED OUT AND NO PREVIOUS WORK WAS NOTED I	N THIS AREA.  THIS PLUG IS NORMALLY NOT TOUCHED IN SERVICE, IT WOULD NORMALLY ONLY BE LOOKED AT DURING OVERHAUL OR BENCH	 CHECK.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		CE  	2009	2	3	CA081212004      	1	20081209	G	3244	301401311	TIRE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110N   	29062	NE  					MLG	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			184  								(CAN) DEFECT IN SIDEWALL CAUSED SIGNIFCANT LOSS OF PRESSURE.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
	20090203		NE  	2009	2	3	CA081212005      	3	20081212	G	6111	6607122666	BLADE           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	NR 2	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			38984	4641 							(CAN) THE PROP IN QUESTION WAS REMOVED FOR DISASSEMBLY TO BE SENT FOR DELAMINATION BEYOND LIMITS TO THE MANUFACTURER.  W	HEN THE PROP ASSEMBLY WAS DISASSEMBLED, A RADIAL CRACK WAS DISCOVERED IN NR 2 BLADE MEASURING IN EXCESS OF 6 INCHES IN T	HE HUB OF THE BLADE S/N: SF340-132/234.  IT WAS DISCOVERED VISUALLY AND HAS SUBSEQUENTLY BEEN SENT FOR REPAIR TO THE MAN	UFACTURER.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
	20090203		NE  	2009	2	3	CA081212006      	2	20081209	G	7210	310838801	WASHER          	PWC         		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  					NR 9 BEARING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 2 ENGINE RGB METAL CHIP FOUND ON CHIP DETECTOR.  DETERMINED TO BE NON-ALLOWABLE CATEGORY 1 DEBRIS, IDENTIFIABLE	 FRAGMENT.  ALSO WASHER WAS CRACKED ENGINE S/N 123037 RGB S/N 123124  DEBRIS IDENTIFIED AS NR 9 BEARING KEY TAB WASHER T	AB. IN CONSULTATION WITH MANUFACTURER THE COMPONENT WAS GIVEN A 10 HOUR REINSPECT, .10 HOUR, REINSPECT COMPLETED WITH NO	 FURTHER ANOMALIES.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20090203			2009	2	3	CA081212007      	2	20081027	G	7414	4372	STOP PIN        																	MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			764  								(CAN) EXCESSIVE WEAR WAS NOTED ON IMPULSE COUPLING STOP PIN.																			 
	20090206			2009	2	6	CA081212008      	2	20081212	G	7414	4372	STOP PIN        																	MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			328  								(CAN) EXCESSIVE WEAR WAS NOTED ON IMPULSE COUPLING STOP PIN.																			 
	20090203		CE  	2009	2	3	CA081212010      	1	20081209	G	3260		WARNING LIGHT   			BEECH 	200   	200BEECH    	1152920	CE  										MLG	UNKNOWN         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ON DEC 9TH, RETURNING FROM KGEG TO CYYC - ON TAKEOFF, WHEN THE GEAR WAS RETRACTED, THE FLIGHT CREW NOTICED THE "RE	D" GEAR LIGHTS WERE INDICATING THAT THE GEAR WAS NOT FULLY RETRACTED.  FLIGHT CREW CYCLED THE GEAR ONCE MORE AND ON THAT	 ATTEMPT WERE ABLE TO CONFIRM THAT THE GEAR WAS LOCKING DOWN, BUT ONCE BROUGHT UP THE RED LIGHTS DID NOT GO OUT.  THE FL	IGHT CREW DID A VISUAL INSPECTION OF EACH MAIN GEAR WHEEL AND CONFIRMED THAT THE MAIN WHEELS WERE INDEED UP.  AT ALTITUD	E, THE FLIGHT CREW CYCLED THE GEAR ONCE MORE AND THE LIGHTS WENT OUT INTERMITTENTLY, BUT SHORTLY AFTER STARTED TO COME O	N AGAIN.  THE FLIGHT CREW MAINTAINED THE GEAR EXTENSION SPEED OF 181KTS FOR THE REMAINDER OF THE FLIGHT.  OTHER THAN HAV	1	L	7	2 	4T				A24CE   					 
	20090203		CE  	2009	2	3	CA081212011      	1	20081204	G	8000	C2925010105	SWITCH          			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	STARTER	UNSERVICEABLE   	W				O				OTHER                   				M	B	H	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	NR	NOT REPORTED   	1			CA											(CAN) HAD STARTER FAILURES WHERE THEY SEIZED AND OVERHEATED.  INVESTIGATION REVEALED THAT IF PILOT AGGRESSIVELY ROTATED 	KEY IN CLOCKWISE DIRECTION THAT KEY WOULD JAM AND LEAVE SWITCH IN THE START POSITION.  THIS WOULD CAUSE THE STARTER TO R	EMAIN ENGAGED UNTIL IT SMOKED.  REPLACED SWITCH WITH NEW, ALL CORRECT.				1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
	20090203		EU  	2009	2	3	CA081212013      	2	20081006	G	7210		SPLINE          	ROTAX       							ROTAX 	912   	ROTAX912F3  	 	EU  					PROP SHAFT	CHIPPED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1465 	44   							(CAN) METAL CHIP FOUND ON MAGNETIC PLUG DURING SERVICING.  TRACED TO GEARBOX.  GEARBOX REMOVED AND CHIP WAS FOUND TO BE 	FROM TOP SPLINE OF THE PROPSHAFT JUST ABOVE THE RING HALF.  POSSIBLE CAUSE, COULD BE FROM A "STEP" WORN IN FROM RING HAL	F.  IF RING HALF WAS INSTALLED WITH THIS STEP RESTING ON THE RING SURFACE IT COULD CAUSE A STRESS POINT.  THERE IS A SLI	GHT CORRESPONDING WEAR MARK 180 DEGREES FORM THE CHIP THAT INDICATES THE CHIP IS RELATED TO THE PREV RING HALF LOCATION.	  PROPSHAFT HAD PASSED NDT 44.5 HRS PRIOR (OVERHAUL).  AREA COULD HAVE BEEN UNDER HIGH LOAD DUE TO STEP WORN INTO SPLINE	.  PROPSHAFT REPLACED.  INCLUDE INSPECTION FOR THIS TYPE OF WEAR IN FUTURE WORK.						3	O			E00051EN				 
	20090206			2009	2	6	CA081212015      	4	20081117	G	2562	97A256000000	ELT             																	CABIN	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) A NR OF INSTANCES OF UNCOMMANDED TRANSMISSIONS HAVE OCCURRED ON 406MHZ ELTS INSTALLED ON OUR ACFT.																			 
	20090203		NM  	2009	2	3	CA081214001      	1	20081213	G	2820	8SC0764	CHECK VALVE     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					FUEL SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING THE UNSCHEDULED REMOVAL OF THE NR 2 ENGINE FUEL FLOW TRANSMITTER, RESIDUAL AIRFRAME FUEL WOULD NOT STOP FLO	WING.  FURTHER INVESTIGATION REVEALED THE RIGHT WING FUEL TANK "MOTIVE FLOW CHECK VALVE" STUCK OPEN.  MOTIVE FLOW CHECK 	VALVE REMOVED AND REPLACED AS PER AMM 28-11-11.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20090203			2009	2	3	CA081215003      	4	20081209	G	6113	05503214	SPINNER         			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			148  								(CAN) CRACKS PERPENDICULAR TO TOP OF PROP BOLT HOLES BARELY VISIBLE TO THE NAKED EYE, CONFIRMED WITH LPI.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20090203		EA  	2009	2	3	CA081215009      	1	20081210	G	2750	855D10011	BPSU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			11166								(CAN) DURING FINAL SEGMENT OF CLIMB, THE FLT CREW RECEIVED A FLAP FAIL MSG ON EICAS.  THE FLAPS WERE AT ZERO AND WERE IN	DICATING ZERO AT THE TIME.  THE QRH WAS FOLLOWED AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE CHECKED FECU FOR	 FAULT CODES AND FOUND CODES FOR RT BPSU, FECU AND WIRING FOR RT BPSU.  THE SYSTEM WAS RESET, THE FLAPS WERE OPS CHECKED	 AND NO FURTHER DEFECTS NOTED.  AIRCRAFT RETURNED TO SERVICE.  IN CRUISE FLIGHT, THE FLT CREW RECEIVED A FLAP FAIL MSG. 	 THE FLIGHT CONTROL SYNOPTIC PAGE INDICATED THE FLAPS WERE OUTLINED IN YELLOW SHOWING ZERO DEGREES OF EXTENSION.  THE AI	RCRAFT LANDED BACK WITHOUT INCIDENT.  MAINTENANCE PULLED FECU CODES (SEE ATTACHED) WHICH INDICATED R BPSU OR WIRING.  TH	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		SW  	2009	2	3	CA081216001      	1	20081110	G	5311	206033107117	FRAME           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REMOVAL OF AFT CABIN HAT RACK ASSY RT FRAME ASSY WAS FOUND CRACKED.  FRAME ASSY WAS REMOVED AND REPLACED NEW.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20090203		SW  	2009	2	3	CA081216002      	1	20081110	G	5311	206033302031	FRAME           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REMOVAL OF BELL INSTALLED HEATER ASSY.  A VISUAL INSPECTION WAS COMPLETED OF THE AREA`S SURROUNDING STRUCTURE	.  THE LT AFT FRAME ASSY WAS FOUND CRACKED BEYOND LIMITS.  THE CRACK WAS NOTED TO PROTRUDE FROM A RIVET HOLE ACROSS THE 	FACE OF THE FRAME.  FRAME ASSY WAS REMOVED AND REPLACED NEW.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20090203		EA  	2009	2	3	CA081216003      	2	20081211	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  						MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3823 							(CAN) PILOTS HEARD A GRINDING SOUND FROM THE EXHAUST STACK WHEN PUTTING ON THE PROP TIE`S AFTER A FLIGHT.  MAINTENANCE C	ONFIRMED THE SOUND AND UPON REMOVING A EXHAUST STACK TO INVESTIGATE THEY VISUALLY CONFIRMED THAT THERE APPEARED TO BE A 	PIECE OF METAL CONTACTING THE NR 2 POWER TURBINE.  POWER SECTION WAS REMOVED AND REPLACED AND IS IN AT STANDARD AERO WIN	NIPEG FOR FURTHER INVESTIGATION AND REPAIR. TSO 3823.0, CSO 2033 (TTSN AND TCSN UNAVAILABLE AS LOG BOOKS ARE AT OVERHAUL	 FACILITY).		1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20090203		SW  	2009	2	3	CA081216004      	1	20081214	G	5610	2719442004	WINDSHIELD      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					COCKPIT	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				3686 							(CAN) DURING TAXI AS THE CREW TURNED INTO A 35 KNOT HEADWIND THE FIRST OFFICER WINDSHIELD SHATTERED.  THE WINDSHEILD HEA	T WAS SELECTED TO LOW AND THE OUTSIDE AIR TEMPERATURE WAS -36 DEGREES CELCIUS.  MAINTENANCE REPLACED THE WINDSHIELD IN A	CCORDANCE WITH THE AMM AND WAS RELEASED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20090203		EA  	2009	2	3	CA081216005      	1	20081212	G	2750		FCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) FLAPS FAILED AT 3 DEGREES ON APPROACH.  NORMAL LANDING FOLLOWED.  CREW ABLE TO RESET SYSTEM ON THE GROUND AND FLIG	HT CONTINUED UNDER MEL.  SECOND FLAP FAILURE ON AIRCRAFT 107 IN AS MANY FLIGHTS.  FLAPS FAILED AT 23 DEGREES INBOUND.  N	ORMAL LANDING OCCURRED.  MX RECTIFICATION TO FOLLOW ALL ACTUATORS REPLACED, RT BPSU REPLACED, LT NR 3 FLAP FLEX DRIVE RE	PLACED, RT NR 1AND NR 4 FLAP FLEX DRIVES REPLACED.  A/C THEN HAD TEST FLIGHT AND HAD ANOTHER FAILURE AT 38 DEGREES EXTEN	SION.  FLAP ELECTRONIC CONTROL UNIT AND FLAP PDU REPLACED AND A/C TEST FLIGHT WAS SUCCESSFUL.  A/C RETURNED TO SERVICE D	EC 18,2008.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		NE  	2009	2	3	CA081217001      	2	20081213	G	7230		COMPRESSOR      			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2 ENGINE	FOD             	W				C				ABORTED TAKEOFF         				C	A		F.O.D.                    	FLAME/FIRE                		TO	TAKEOFF        	1			CA		CFJLB	43057								(CAN) AIRCRAFT WAS ON TAKEOFF ROLL WHEN THE PILOTS HEARD A LOUD BANG FROM ENGINE NR 2 & EXPERIENCED A YAW TO THE RIGHT A	S THEY APPROACHED 110 KNOTS.  THE PILOTS THROTTLED BACK, ABORTED THE TAKEOFF, TAXIED BACK TO THE RAMP AND SHUTDOWN THE E	NGINES.   PASSENGERS OBSERVED FLAMES EXPEL FROM NR 2 ENGINE INLET AND EXHAUST WHEN THE BANG OCCURRED.  CONDUCTED AN INIT	IAL VISUAL INSPECTION AND FOUND PART OF A RUBBER SEAL MISSING AND DETACHED FROM THE C2 INLET GUIDE VANE.  THERE IS NO DA	MAGE TO THE C1, C2 OR T4.  REQUESTED AN EXTERNAL A BORESCOPE INSPECTION TO DETERMINE IF THERE IS DAMAGE TO THE INTERNAL 	PART OF ENGINE.   NO EVIDENCE OF FOD INGESTION.	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
	20090203		EA  	2009	2	3	CA081217002      	1	20081216	G	3230		LANDING GEAR    			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C5     	30050	NE  					LEFT	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) LANDED WITHOUT LT MLG NOT FULLY EXTENDED.  THE FLT CREW ATTEMPTED TO EXTEND GEAR, BUT NEVER GOT A LT MLG GREEN DOW	N AND LOCKED INDICATION.  THEY CYCLED THE GEAR 3 TIMES, BUT STILL WERE UNABLE TO GET GOOD INDICATION.  THEY PERFORMED A 	MANUAL EXTENSION AND AGAIN DID NOT GET THE GEAR TO EXTEND.  AC LANDED ON RT MLG ON TOUCH DOWN AND COMPLETED ITS LANDING 	W/THE LT WING HITTING THE RUNWAY.			2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20090203		EA  	2009	2	3	CA081217003      	1	20081216	G	2120	601R95655	DUCT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					CABIN AIR	FAILED          	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE PILOT NOTICED THE AIRCRAFT CABIN ALTITUDE WAS CLIMBING SO HE INITIATED AN EMERGENCY DESCENT.  HE	 THEN HEARD A LOUD POP/BANG THAT SOUNDED LIKE IT CAME FROM THE AFT OF THE AIRCRAFT.  NOT TO LONG AFTER THAT ALL THE OXYG	EN MASKS DEPLOYED IN THE CABIN.  THE AIRCRAFT ALSO HAD A MEL FOR THE RIGHT PACK PRIOR TO THE FLIGHT  THE CAPITAN DID NOT	 DECLARE AN EMERGENCY AND THE PLANE LANDED WITHOUT INCIDENT.  MX FOUND A SUPPLY DUCT COMING FROM THE LEFT PACK GOING BEH	IND THE APU INTO THE AFT PRESSURE BULKHEAD BLOWN.  THEY ARE ORDERING PARTS AND WILL REPAIR ACCORDINGLY 17- O2 GENERATORS	 WERE ACTIVATED.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		EA  	2009	2	3	CA081217004      	1	20081213	G	3260		PROXIMITY SENSOR			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					MLG	OUT OF ADJUST   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			19856								(CAN) ON TAKEOFF WHEN THE LANDING GEAR WAS SELECTED UP, THE EICAS DISPLAYED "GEAR DISAGREE" MSG FOLLOWED BY "NOSE GEAR D	OOR" MSG.  THE QRH WAS FOLLOWED AND THE GEAR WAS LOWERED AND THE MESSAGE CLEARED.  THE AIRCRAFT RETURNED AND PERFORMED A	 LOW PASS SO THE TOWER COULD VERIFY ALL GEAR DOWN.  THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.   THE AIRCRAFT WAS THE	N FERRIED WITH GEAR DOWN AND PINNED.  MAINTENANCE READJUSTED THE PROX SENSOR TARGET FOR PROX SENSOR PS14GA (NOSE GEAR EX	TEND/CENTER PROX SENSOR) AND THE SYSTEM CHECKED NORMAL. AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		NE  	2009	2	3	CA081217005      	2	20081210	G	7261		SCREEN          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					RT ENG OIL	CONTAMINATED    	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) FLT CREW REPORTED R ENGINE OIL PRESS (W) MSG AT CRUISE.  WARNING PERSISTED AT POWER SETTINGS ABOVE IDLE.  COMPLIED	 WITH QRH AND DIVERTED TO PHL.  ENGINE REMAINED AT IDLE DURING THE 40 MIN FLIGHT TO PHL.  LOWEST OIL PRESSURE SHOWN WAS 	24 PSI.  AIRCRAFT LANDED IN PHL WITHOUT FURTHER INCIDENT.  MAINTENANCE REMOVED RT LUBE/SCAVENGE PUMP AND FOUND SCREENS C	OKED UP CAUSING RESTRICTION.  CLEANED SCREENS IN ACCORDANCE WITH EO 8/016/479 AND REINSTALLED PUMP IN ACCORDANCE WITH AM	M 79-21-01.  OPS CHECKS CARRIED OUT AND NO FURTHER DEFECTS NOTED.  AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		CE  	2009	2	3	CA081217006      	1	20081215	G	3240	61702935	CONTROL CABLE   			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					PARKING BREAK	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			516  	516  							(CAN) THE CRIMP THAT RETAINS THE CABLE SHEATH TO THE CABLE ATTACH POINT FAILED ALLOWING THE SHEATH TO MOVE CAUSING THE P	ARK BRAKE TO NOT RELEASE.  THIS CABLE IS POST SB 550-32-50.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
	20090203		CE  	2009	2	3	CA081217007      	1	20081206	G	2750	MS250261	LIMIT SWITCH    			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					TE FLAPS	FAILED          	W				G	A			O2 MASK DEPLOYED        	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, JUST BEFORE 10000 FT, CREW NOTICED ODOR OF ELECTRICAL SMOKE IN COCKPIT.  AS ACFT LEVELED OFF AT 1000	0 FT, CABIN CREW INFORMED FLT CREW OF AN ODOR OF SMOKE CABIN.  DONNED O2 MASKS, NOTIFIED ATC & INFORMED THEM OF SMOKE IN	 COCKPIT & RECEIVED A CLEARANCE TO PROCEED TO THE NEAREST AIRPORT.  WHILE DOING THE BEFORE LANDING CHECKLIST THE FLAPS W	OULDN`T EXTEND,  A FLAPLESS LANDING COMPLETED WITHOUT FURTHER INCIDENT.  POST FLT INSP FOUND FLAP CIRCUIT BREAKER POPPED	 & FLAPS RETRACTED HARD AGAINST THEIR STOPS.  IT IS SUSPECTED THE UP LIMIT SWITCH FAILED ALLOWING SYSTEM TO THINK THAT T	HE FLAPS WERE NOT ALL THE WAY UP.   MOTOR OVERHEATED BEFORE TRIPPING THE CIRCUIT BREAKER, CAUSING THE ELECTRICAL SMOKE O	1	L	7	2 	3T	4	T		A14CE   	E4EA				 
	20090203		SW  	2009	2	3	CA081217008      	1	20081201	G	5302	206020113215A	TAIL BOOM       			BELL  	407   	407         	1182206	SW  											DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORE ASSEMBLY 206-020-113-215A BONDED IN VERTICAL FINS ASSEMBLIES 206-020-113-233 FOUND WITH VOIDS IN THE ADHESIVE	 AT THE LOWER PORTION OF THE FIN NEAR THE TAILROTOR SKID ATTACHMENT POINT.					1	G	7	1 	3U			O	H2SW    					 
	20090203		NM  	2009	2	3	CA081217011      	1	20081215	G	5610	NP15790113	WINDSHIELD      			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			16661								(CAN) DURING CLIMB LT WINDSHIELD CRACKED.  AIRCRAFT RETURNED TO DESTINATION AIRPORT.  UNEVENTFUL LANDING.  MAINTENANCE R	EPLACED THE DAMAGED WINDSHIELD AND THE AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090203		EU  	2009	2	3	CA081217012      	1	20081217	G	3213	4321012188	BEARING         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG STRUT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6340 								(CAN) RIGHT MAIN LANDING GEAR SHOCK ABSORBER STRUT LOWER BEARING WORN AND LOOSE INTERNALLY.  REPLACED WITH NEW.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
	20090203		EU  	2009	2	3	CA081217013      	1	20081208	G	7930		OIL SYSTEM      			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  					ENGINE	LOW PRESSURE    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, THE PILOT NOTICED A LOW OIL PRESSURE INDICATION.  THE ENGINE WAS SHUTDOWN AND THE FLIGHT RE	TURNED TO ORIGIN FOR AN UNEVENTFUL SINGLE ENGINE LANDING.  GROUND INSPECTION REVEALED A POSSIBLE FRACTURED TOWERSHAFT.  	WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20090203		NE  	2009	2	3	CA081217014      	2	20081208	G	7200		ENGINE          			FOKKER	F27   	F27MK500    	4990629	EU  	PWA   	PWA120	PW125B      	 	NE  						MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING T/O CLIMB, THE ENGINE OUT LIGHT CAME ON AND THE CREW ELECTED TO SHUT THE ENGINE DOWN AND RETURN TO THE POIN	T OF DEPARTURE FOR AN UNEVENTFUL SINGLE LANDING.  GROUND INSPECTION SHOWED OIL FILTER BYPASS INDICATORS ACTIVATED AND ME	TAL WAS FOUND ON THE CHIP DETECTORS.  A RECOMMENDATION TO REMOVE THE ENGINE HAS BEEN MADE.				2	H	7	2 	4T	4	T		A817    	E20NE				 
	20090203		SW  	2009	2	3	CA081217015      	1	20081210	G	6320		HOUSING         			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					M/R GEARBOX	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, OIL PRESSURE WAS LOST ON THE COMBINING GEARBOX AND THE PILOT PERFORMED AN UNSCHEDULED LANDING OFF B	ASE.  THE HELO HAD TO BE TRANSPORTED BACK ON A TRUCK.  INSPECTION OF THE ENGINE REVEALED A CRACK IN THE GEARBOX HOUSING 	FROM WHICH THE OIL ESCAPED.  THE GEARBOX WILL BE REMOVED AND FORWARDED TO P&WC FOR INVESTIGATION.  UPDATES WILL BE PROVI	DED IN DUE COURSE.			1	G	7	2 	4U	4	U		H4SW    	E22EA				 
	20090203		SW  	2009	2	3	CA081217016      	1	20081212	G	2435	M2040AC2	BEARING         	BFGOODRICH  		SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					STARTER GEN	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				822  							(CAN) STARTER GENERATOR FAILED IN FLIGHT CAUSING THE RT GEN FAIL LIGHT TO ILLUMINATE.  UPON LANDING AND INSPECTION BY MA	INTENANCE THE GENERATOR WAS FOUND TO HAVE DAMAGE RELATED TO COMPONENT FAILURE.  THE GENERATOR WAS REPLACED AND SENT TO P	ERIMETER`S OVERHAUL FACILITY.  THE TEARDOWN REPORT INDICATES FAILURE OF BOTH GENERATOR BEARINGS (PN M2040AC-2).  GENERAT	OR WAS LAST INSPECTED AT 487.6 HOURS IN ACCORDANCE WITH THE MANUFACTURERS CMM SINCE LAST OVERHAUL AND PASSED THE INSPECT	ION AND WAS RETURNED TO SERVICE.  AT 822.4 THE BEARINGS FAILED CAUSING THE GENERATOR SYSTEM FAILURE.  BOTH THE STATOR AN	D ARMATURE ASSY WERE DAMAGED BEYOND REPAIR.  NO DEFINITIVE CAUSE CAN BE DETERMINED.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20090203		GL  	2009	2	3	CA081218001      	1	20081208	G	5512		SKIN            			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5400 								(CAN) DURING ROUTINE MAINTENANCE, A 1 1/2 INCH LONG CRACK WAS NOTICED IN THE LEADING EDGE OF THE HORIZONTAL STABILIZER. 	 TAP TESTING INDICATED POSSIBLE DELAMINATION, SO THE STABILIZER WAS REMOVED FROM AIRCRAFT AND SENT TO COMPOSITE REPAIR S	HOP (XU AVIATION) FOR FURTHER EVALUATION AND REPAIR.				1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
	20090203			2009	2	3	CA081218003      	4	20081216	G	3160	8221917202	DISPLAY         			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					COCKPIT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) IN CRUISE FL 380, 3.5 HOURS IN FLIGHT, THE MFD NR 2 LOWER WINDOW STARTED TO CYCLE BETWEEN THE DIFFERENT FORMATS (P	POS, PLAN, TCAS ECT) AT FEW SECONDS INTERVAL WITH UNDEFINED SYMBOLS/TEXT LINE (HIEROGLYPH).  AT THAT TIME THE PFDS 1 AND	 2, MFD 1 SHOWED NORMAL INFORMATION.  THEN, THE COMS AND NAVS ACTUAL AND PRE SELECTED FREQUENCIES, WOULD HAVE DIGITS CHA	NGING ON THEIR OWN, SOMETIMES THE FREQUENCIES WOULD BE GREEN OR AMBER ON BOTH CDUS TUNING PAGE AND MFDS RADIO MENUS.  TH	E NAVS TUNING MODE WOULD BE CHANGING BY THEMSELVES BETWEEN AUTO/MAN.  SUBSEQUENTLY, THE COMMUNICATION WITH BOTH VHF COMS	 WAS NO LONGER POSSIBLE WITH AIR TRAFFIC CONTROL.  ONBOARD SATELLITE AIRPHONE WAS USE.  THE FLIGHT WAS REDIRECTED TO A C	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		SO  	2009	2	3	CA081218004      	1	20081201	G	3245		TUBE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					TIRE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA			391  								(CAN) WHEN THE AIRCRAFT LANDED IT WAS DISCOVERED THAT THE NOSEWHEEL WAS FLAT.  INSPECTION DID NOT REVEAL A DIRECT CAUSE 	FOR THE TUBE TO FAIL.  THERE WERE SEVERAL SEVERE WEATHER CHECK CRACKS IN THE TUBE WHEN THE TIRE WAS DISASSEMBLED.  THE C	OMPANY IS INSTALLING A PROCEDURE FOR INSPECTING NEW TUBES BEFORE INSTALL AS WELL AS PROPER WHEEL BUILD UP PROCEDURES.  T	HE COMPANY IS ALSO IMPLEMENTING A 12 MONTH INSPECTION AND REPLACEMENT SCHEDULE FOR THE NOSEWHEELS ON THE NAVAJO AIRCRAFT	.		1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20090203		EA  	2009	2	3	CA081218005      	1	20081217	G	2752		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) FLAP FAIL ON APPROACH.  WHEN FLAPS SELECTED THE FLAPS DID NOT MOVE FROM ZERO DEGREES.  FLAPLESS APPROACH AND LANDI	NG CARRIED OUT WITHOUT FURTHER INCIDENT.  ACFT FERRIED FOR FLAP REPAIR.  ALL FLAP ACTUATORS REPLACED, RT NR 1 FLAP DRIVE	 ASSY REPLACED DUE TO DAMAGED CORE, RT NR 2 AND NR 3 DRIVE CABLES FOUND WITH MOISTURE CONTAMINATION-CORE AND CASINGS CLE	ANED AND RELUBED.  LT NR 1 FLAP DRIVE FOUND WITH MOISTURE CONTAMINATION-CLEANED AND RELUBED.  LT NR 5 FLAP DRIVE DEFORME	D BEYOND LIMITS.  REPLACED FLAP POWER DRIVE UNIT.  ACFT TEST FLOWN SUCCESSFULLY AND RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		SW  	2009	2	3	CA081218006      	1	20081217	G	7931	8974072	BYPASS VALVE    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					OIL FILTER	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) THE CREW REPORTED THAT ONE TIRE HAD BLOWN DUE TO FROZEN BRAKES.  AN AME WAS SENT TO CHANGE THE WHEEL AND FLY BACK 	TO THE BASE WITH THE AIRCRAFT.  UPON RETURN TO BASE, A LARGE OIL LEAK WAS NOTED COMING FROM THE NR 2 ENGINE.  IT WAS EVE	NTUALLY DETERMINED BY MAINTENANCE STAFF TO BE THE OIL FILTER BYPASS PIN.  THE PIN POPS OUT IF THE OIL SYSTEM BECOMES CON	TAMINATED.  THE PIN WAS NOT EXTENDED, HOWEVER, IT WAS LEAKING OIL.  THE OIL LEAK WAS INITIALLY THOUGHT TO BE AN STARTER 	GENERATOR OIL SEAL, DUE TO THE VOLUME OF OIL LEAKED THROUGHOUT THE ENGINE COMPARTMENT.  A SECOND GROUND RUN DISCOVERED T	HE LEAK FROM THE BYPASS PIN AREA.  PRELIMINARY REPORT, THE DEFECT IS BEING REPAIRED NOW.  UNKNOWN TSO ON THE PART, HOWEV	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
	20090203			2009	2	3	CA081222007      	4	20081219	G	2350	164ZS01Y	AUDIO PANEL     			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					COCKPIT	MALFUNCTIONED   	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			6069 	6069 							(CAN) DURING THE BASIC INSPECTION WITH AIRCRAFT POWER ON, FUMES AND LIGHT SMOKE WHERE NOTICED IN THE COCKPIT.  AFTER INS	PECTION THE AUDIO WARNING PANEL BOX WAS FOUND TO BE THE CAUSE.  THE AUDIO WARNING PANEL BOX WAS REPLACED WITH A REPAIRED	 SERVICEABLE UNIT FROM DASSAULT AND TESTED SERVICEABLE P/N 164ZS01Y S/N 202.  REMOVED AND S/N 175, INSTALLED.				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
	20090203		SW  	2009	2	3	CA081222008      	1	20081208	G	6730	222382001101	SERVO           			BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  						UNKNOWN         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) SOLID RESISTANCE FELT WITH AFT CYCLIC MOVEMENT DURING OPERATIONS WITH FORCE TRIM ON & UTILIZING CYCLIC TRIM RELEAS	E SWITCH.  ON FIRST OCCURRENCE RESISTANCE RELEASED WITH A FIRM BUMP & FAULTY LT CYCLIC TRIM RELEASE SWITCH SUSPECTED HOW	EVER WITH SECOND OCCURRENCE SWITCHING FORCE TRIM OFF HAD NO EFFECT & RESISTANCE ONCE AGAIN RELEASED WITH A FIRM BUMP AFT	ER SEVERAL SECONDS.  ALL THE MAIN ROTOR CONTROLS WERE INSPECTED FOR FREEDOM OF MOVEMENT & TRAVEL, NO DEFECTS NOTED.  A G	PU FOR HYD SYSTEM ATTACHED & SYSTEM 1 & 2 CHECKED.  NO DEFECTS.  WHEN CYCLIC MOVED FOR & AFT WHEN POWERED BY ONLY 1 HYD 	SYSTEM NOTICED THAT CYCLIC STICK SEEMED TO BE MOTORED (DRIVEN) FOR & AFT BY SERVO ACTUATOR.  SERVO HAD 23.8 HOURS SINCE 	1	G	7	2 	3U	3	U		H9SW    	E5NE				 
	20090203		NM  	2009	2	3	CA081222009      	1	20081218	G	2421	31708001A	GENERATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1 AC	MALFUNCTIONED   	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA			26071	1768 							(CAN) SHORTLY AFTER TAKE OFF, THE FLIGHT CREW RECEIVED "NR 1 AC GEN" AND "NR 2 AC GEN" CAUTION LIGHTS.  SYSTEMS WERE RES	ET AND NR 2 AC GENERATOR RETURNED ON LINE.  DECISION WAS MADE TO RETURN AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT	.  THE NR 1 AC GENERATOR WAS REPLACED AND THE PHASE A AND C WIRES LOCATED UNDER THE RT FLAP BETWEEN THE NACELLE AND THE 	FUSELAGE WERE REPAIRED.  BOTH WIRES WERE SHORTED DUE TO CHAFING.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090203		CE  	2009	2	3	CA081222010      	1	20081221	G	5610	10138402523	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			4500 								(CAN) WINDSHIELD CRACKED AFTER TAKEOFF, CRACKS EMANATED VERTICALLY FROM THE BOTTOM INBOARD EDGE.  UNIT TTSN 4500 HOURS.						2	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20090203		NE  	2009	2	3	CA081223001      	2	20081219	G	7230	311194301	BEARING         								PWA   	118   	PW118       	 	NE  					NR 3	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NR 3 BEARING FAILURE FOUND AT DISASSEMBLY.											4	T			E20NE				 
	20090203		NE  	2009	2	3	CA081223002      	2	20081217	G	7200	MS945226	BEARING         								PWA   	PW120 	PW123       	 	NE  					ENGINE	SEIZED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ENGINE BEARING SEIZED.											4	T			E20NE				 
	20090203			2009	2	3	CA081223004      	4	20081221	G	3460	4082499902	COMPUTER        			BOEING	737   	737800*     	       	NM  										FLIGHT CONTROL	MALFUNCTIONED   	W				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) CREW REPORT STABILIZER LIGHT CAME ON.  ATC INFORMED AND CREW BROKE OFF APPROACH AND DETERMINED THAT THERE WAS NO S	TABILIZER TRIM.  AIRCRAFT RETURNED TO AIRPORT AND CONDUCTED A SAFE LANDING.  MAINTENANCE TROUBLESHOT REPORTED SNAG AND F	OUND FAULT APPEARED TO LIE WITH THE FLIGHT CONTROL COMPUTER.  UNIT REPLACED AND SYSTEM CHECKED SERVICEABLE.  AIRCRAFT RE	TURNED TO SERVICE.			2	L	7	2 	4F			RT	A16WE   					 
	20090203		EA  	2009	2	3	CA081223005      	1	20081208	G	5531	215221182	RIB             			CNDAIR	CL215 	CL2156B11215	       	EA  	PWA   	PW120 	PW123       	 	NE  					VERTICAL STAB	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACK 35 MM LONG ON RIB OF VERTICAL STAB AT WL 396.						2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
	20090203		GL  	2009	2	3	CA081223007      	1	20081123	G	7921	AE7010101H0114	HOSE            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					OIL COOLER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			577  								(CAN) AIRCRAFT WAS ON A REGULAR TRAINING FLIGHT WHEN THE CREW NOTICED THAT THE OIL PRESSURE INDICATION HAD FALLEN OUT OF	 THE GREEN ARC AND REMAINED LOW UNTIL THE AIRCRAFT WAS ABLE TO RETURN TO BASE.  ONCE THE AIRCRAFT HAD RETURNED AND WAS I	NSPECTED MY MAINTENANCE, IT WAS DETERMINED THAT THERE WAS A SIGNIFICANT OIL LEAK.  FURTHER INVESTIGATION REVEALED THAT T	HE OIL COOLER HOSE HAD A PUNCTURE AND THAT WAS THE LIKELY CAUSE OF THE FAILURE.  THE ENGINE WAS REMOVED AND SENT OUT FOR	 BULK INSPECTION.  A REPLACEMENT ENGINE WAS INSTALLED ALONG WITH NEW OIL COOLER HOSES.  THE FAULTY HOSE WAS INSPECTED, T	ESTED AND RETURNED TO THE MANUFACTURER FOR ANALYSIS.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
	20090203		NE  	2009	2	3	CA081223008      	2	20081223	G	7414	22021081806	BEARING         			ROBSIN	R44   	R44RAVENII  	7640122	WP  	LYC   	O540  	IO540AE1A5  	41530	NE  					MAGNETO	LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			474  								(CAN) MAG RECEIVED FOR 500 HR INSPECTION, ROTATING MAGNET SHAFT SPUN BEFORE DISASSEMBLY TO INSPECT BEARING CONDITION & P	RELOAD.  NO END PLAY OR ROUGHNESS FELT, WHEN MAG WAS DISASSEMBLED, DISCOVERED THAT AT O/H IN SEPT 2007.  NO GREASE HAD B	EEN PACKED INTO BEARINGS.  BEARINGS WERE LUBRICATED BY OIL THAT EACH BEARING IS PACKAGED WITH WHEN NEW.  ONLY OTHER SOUR	CE OF LUBRICATION WAS A SMALL AMOUNT OF OIL THAT HAD LEAKED INTO MAG PAST OIL SEAL.  LACK OF LUBRICATION COULD CAUSE MAG	NETO & ENGINE FAILURE, EVEN THOUGH BEARINGS DID NOT APPEAR DAMAGED THEY WERE REPLACED,  MAG WAS RETURNED TO SERVICE.  		1	G	7	1 	3O	3	O		H11NM   	1E4				 
	20090203		EA  	2009	2	3	CA081229001      	1	20081225	G	5610	04093H1031	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			10575	10575							(CAN) DURING CLIMB, THE RT WINDSHIELD CRACKED LIMITING THE FIRST OFFICER VIEW.  AN EMERGENCY WAS DECLARED, THE AIRCRAFT 	RETURNED AND LANDED WITHOUT FURTHER INCIDENT.  AT THIS TIME, NO IMPACT WERE REPORTED BY THE FLIGHT CREW.  VISUAL INSPECT	ION OF THE WINDSHIELD INDICATES THAT THE EXTERNAL AND INTERNAL LAYERS ARE CRACKED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		GL  	2009	2	3	CA081229003      	2	20081224	G	7323	23070101	GOVERNOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA				1419 							(CAN) PILOT ENCOUNTERED HIGH SIDE GOVERNOR FAILURE.  TORQUE INCREASED FROM 85 TO 100 PERCENT DURING CLIMB WITH NO COLLEC	TIVE INPUT.  NR/N2 INCREASED TO 110 PERCENT AND THROTTLE WAS ROLLED TO IDLE WITH NO INITIAL EFFECT.  NR/N2 THEN DROPPED 	TO 90 PERCENT.  A DESCENT AND SHORT RUN-ON LANDING WAS MADE USING MANUAL THROTTLE MOVEMENTS.  NO DAMAGE OCCURRED.  REPLA	CEMENT OF GOVERNOR CURED PROBLEM AFTER TROUBLESHOOTING IN ACCORDANCE WITH ROLLS ROYCE 250 C30P MM.  REMOVED GOVERNOR WIL	L BE SENT TO REPAIR STATION FOR INSPECTION.		1	G	7	1 	3U	3	U		H2SW    	E1GL				 
	20090203		EA  	2009	2	3	CA081229004      	1	20081226	G	5210	601R317047	HANDLE          			CNDAIR	CL600 	CL600*      	1900302	EA  	GE    	CF34  	CF348C5     	30050	NE  					PAX DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10811	10811							(CAN) WHEN GROUND CREW ATTEMPTED TO OPEN AIRCRAFT FOR MORNING DEPARTURE, OUTER DOOR HANDLE SNAPPED OFF IN HIS HAND.  MAI	NTENANCE INSPECTED AND REPLACED MAIN CABIN DOOR HANDLE ASSEMBLY AND FUNCTION CHECKED AS PER MANUFACTURERS MAINTENANCE MA	NUAL.  AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E00063EN				 
	20090203		NE  	2009	2	3	CA081231001      	2	20081229	G	7200		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1	OVERTORQUED     	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE CREW OBSERVED AN OVERTORQUE ON THE NR 1 ENGINE, THE POWER LEVER WAS REDUCED AND THE ENGINE STABIL	IZED AROUND 93 PERCENT OF TORQUE BEFORE RAISING AGAIN.  DECISION WAS MADE TO PERFORM AN INFLIGHT SHUTDOWN.   THE CREW DE	CLARED AN EMERGENCY, RETURNED TO THE AIRPORT AND LANDED WITHOUT FURTHER INCIDENT.  IT IS UNKNOWN AT THIS TIME WHAT HAS C	AUSED THE ENGINE OVERTORQUE.  THE ENGINE IS BEING REPLACED AND WILL BE SHIPPED TO AN OVERHAUL FACILITY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090203		NE  	2009	2	3	CA081231002      	2	20081231	G	7414	GE5298	DRIVE GEAR      	BOSCH       							PWA   	R985  	R985AN14B   	52008	NE  					MAGNETO	WORN            	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				778  							(CAN) ON INSPECTION MAGNETO WAS FOUND TO HAVE ERATIC TIMING ON DRIVE GEAR PART NUMBER GE5298, LOOSE ON SHAFT AND EXCESSI	VE WEAR ON KY11-14 - KEY WOODRUFF FOR DRIVE GEAR.										3	R			5E1				 
	20090203		CE  	2009	2	3	CA081231003      	1	20081221	G	5610	10138402524	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) WINDSHIELD CRACKED AS AIRCRAFT CLIMBED OUT OF YYC.  AIRCRAFT RETURNED TO YYC.  MAINTENANCE REPLACED WINDSHIELD AND	 RETURNED AIRCRAFT TO SERVICE.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20090203		CE  	2009	2	3	CA081231004      	1	20081221	G	5610	10138402523	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER START PILOT NOTED THAT THE WINDSHEILD WAS CRACKED.  ENGINES WERE SHUT DOWN AND MAINTENANCE REPLACED THE WIND	SHEILD AND RETURNED THE AIRCRAFT TO SERVICE.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20090203		EA  	2009	2	3	CA090102002      	1	20081224	G	2750		FLAP SYSTEM     			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B      	30069	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE FLAP FAILED TO EXTEND AND THE AIRCRAFT DIVERTED WHERE THEY LANDED WITH THE FLAPS UP.  UPON INSPECT	ION FOUND THE FLAPS WOULD NOT MOVE AND WERE IN ASYMMETRIC CONDITION.  BOTH THE LT AND RT BDU WERE REPLACED AND THE FLAP 	SYSTEM TESTED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		CE  	2009	2	3	CA090102004      	1	20081231	G	5310	97430000149	DOOR FRAME      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					BS 201	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6727 								(CAN) WHILE CARRYING OUT SPECIAL INSPECTION, INSPECT ESCAPE HATCHES AND ASSOCIATED CLOSURE AREA.  FOUND THE RT AFT EMERG	ENCY EXIT CROSS TIE CRACKED THROUGH AT FS 201.775, AFT RT ESCAPE HATCH FRAME.  THERE WERE TWO RIVETS SHEARED OFF IN THE 	SAME AREA AND THE .125 INCH THICK PIECE HAD BUCKLED.  NO ADDITIONAL DAMAGE WAS NOTED IN THE FUSELAGE.  THIS WAS THE FIRS	T 1000 LANDING REPETITIVE INSPECTION AFTER THE INITIAL 5000 LANDING INSPECTION.  PART WILL BE REPLACED WITH FACTORY NEW 	PART.		2	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20090203		CE  	2009	2	3	CA090105001      	1	20081208	G	3210		STRUCTURE       			CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A4M     	41514	EA  					MLG	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			15   								(CAN) WORN ATTACH HOLE, CAUSING FORE AND AFT MOVEMENT OF THE WHEEL.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
	20090203		CE  	2009	2	3	CA090105002      	1	20081224	G	5610	50420066103	WINDOW          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	COCKPIT	FAILED          	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			O			OTHER                     			CR	CRUISE         	1			CA			15865								(CAN) AT 16000 FT LEVEL CRUISE, WINDOW FAILURE OCCURRED, COMPLETE WINDOW FAILED LEAVING ONLY APPROX 2 INCHES OF WINDOW A	TTACHED TO AIRFRAME  WINDOW SEAL STAYED ATTACHED TO AIRFRAME.  CRAZING, PITS AND SCRATCHES REMOVED FROM WINDOW FEB 10, 2	000, WINDOW MEASURED AFTER  REPAIR.  .304-.321, COMPLETED BY AVGLASS USA.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA	 
	20090203		EA  	2009	2	3	CA090105006      	1	20081231	G	2750	865D1007	DRIVE UNIT      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			14963	14963							(CAN) THIS AIRCRAFT WAS UNDER A FERRY PERMIT TO YYC FOR A BROKEN OUTER DOOR HANDLE.  THE FLAPS WHERE AT 8 DEGREES BEFORE	 DEPARTURE.  AFTER TAKEOFF THE FLAP FAIL MESSAGE WAS POSTED WITH FLAPS STILL AT 8 DEGREES.  THE PILOT RETURNED TO YZF DU	E TO INSUFFICIENT FUEL TO REACH YYC WITH FLAPS AT 8 DEGREES.  THE AIRCRAFT IS GOING TO FERRY TO YYC WITH FLAPS SET AT 8 	DEGREES.  FLAP POWER DRIVE UNIT REPLACED AND FLAP SYSTEM CHECKED SERVICEABLE.  A/C RETURNED TO SERVICE (RESOLVED ON W/O:	 174456 TASKCARD: NR-00002) DEFECT NR 819812.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		NM  	2009	2	3	CA090105007      	1	20081220	G	6120	699018002	PCU             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NO 1 ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) POWERPLANT INDICATION ON ED NR 1 TRU AND AC GEN ZERO INDICATION WHILE TAXIING.  ACTION TAKEN AT MNL, RETRIEVE FAUL	T CODE 388 AND 1504 AND CLEARED POWERPLANT MESSAGE.  PEC REPLACED.  PERFORMED FAULT CODE ISOLATION AND OPERATIONAL CHECK	 OF RADIO ALTIMETER AND FAULT ISOLATION ON POWERPLANT ELECTRONIC UNIT (PEC).  PERFORMED ENGINE RUN-UP FOUND SATISFACTORY	 IN ACCORDANCE WITH Q400 TASK 77-31-00-810-805, 61-20-07-810-815, 32-61-00-710-801.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
	20090203		CE  	2009	2	3	CA090105008      	1	20081224	G	5540		ATTACH BRACKET  			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	RUDDER WEIGHT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10742								(CAN) RUDDER BALANCE WEIGHT EXCEEDED MAY ALLOWABLE WEIGHT OF 4.38 LBS PLUS .25 LBS BY 1.5 LBS WEIGHT WAS ADDED TO BALANC	E WEIGHT FOLLOWING PAINTING OF RUDDER.  EXCESSIVE WEIGHT CAUSED ATTACH POINTS TO FAIL ALLOWING THE BALANCE WEIGHT TO BE 	ABLE TO SHIFT IN SUCH A MANNER THAT COULD CAUSE FLIGHT CONTROL BLOCKAGE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
	20090203		EA  	2009	2	3	CA090105009      	1	20081229	G	2752	852D10019	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30068	NE  					TE FLAPS	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) FIRST FLIGHT OF THE DAY.  PILOTS WERE TAXIING AND SELECTED FLAPS TO 20 DEGREES AND THE FLAPS STAYED AT 0.  OAT -33	 DEGREES C.  ACFT FERRIED FOR REPAIR.  ALL FLAP ACTUATORS REPLACED WITH POST SB ACTUATORS, FLAP DRIVE LUBE TASK COMPLETE	D, RIGGING AND FUNCTION CHECKS COMPLETED, AND A/C SUCCESSFULLY TEST FLOWN AND RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		EA  	2009	2	3	CA090105012      	2	20081210	G	7200		ENGINE          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  						COKED           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE CREW OBSERVED A RAPID RISE IN ENGINE TEMPERATURE AND TORQUE WITH FLAMES COMING OUT THE RIGHT EN	GINE EXHAUST STACKS.  THE ENGINE THEN FLAMED OUT, THE FLIGHT WAS DIVERTED WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED	.  DISASSEMBLY OF THE ENGINE BY THE OPERATOR REVEALED A LARGE PIECE OF CARBON COMPLETELY BLOCKING ONE OF THE CT GUIDE VA	NE, CT BLADES HEAVILY ERODED AND HEAVY CARBON DEPOSITS ON THE COMBUSTION LINER.  WILL CONTINUE INVESTIGATING THE EVENT A	ND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.		1	L	7	2 	3T	4	T		A14CE   	E4EA				 
	20090204			2009	2	4	CA090105014      	1	20081217	G	6123		AUTOFEATHER SYS 								PWA   	PW120 	PW124B      	 	NE  						MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE ENGINE TORQUE DROPPED TO 22 PERCENT AND THEN ZERO.  THE ENGINE WAS SECURED AND THE A/C RETURNED T	O THE POINT OF DEPARTURE, WHERE A SINGLE ENGINE LANDING WAS PERFORMED.  POST FLIGHT TROUBLESHOOTING LED TO THE REPLACEME	NT OF THE AUTO FEATHER UNIT BEFORE THE ACFT WAS RETURNED TO SERVICE.  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE O	F ROOT CAUSE ONCE ESTABLISHED.								4	T			E2ONE				 
	20090204		WP  	2009	2	4	CA090106002      	1	20081223	G	3260		DOWNLOCK SWITCH 			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					MLG	OUT OF ADJUST   	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH, CREW EXPERIENCED A LT GEAR UNSAFE LIGHT.  AFTER DETERMINING THE GEAR TO BE DOWN, ACFT LANDED UNEVENTF	ULLY.  MAINTENANCE ADJUSTED THE DOWN LOCK SWITCH AND ACFT WAS RETURNED TO SERVICE					2	L	7	2 	4R	4	T		6A6     	E282				 
	20090206		SO  	2009	2	6	CA090107004      	1	20081223	G	5712	4042306	RIB             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MX, RIB P/N 40423-06, WHICH RUNS THROUGH THE LT WW, WAS FOUND CRACKED THROUGH AT THE NARROWEST PART OF THE 	RIB AT THE TOP CENTER OF THE WW. THE WING SKIN IMMEDIATELY ABOVE AND ATTACHED TO THE RIB ALSO HAD A SMALL CRACK WHICH CO	INCIDED WITH THE RIB CRACK.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
	20090206		EA  	2009	2	6	CA090107006      	1	20081229	G	5610		WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			13762								(CAN) CAPTAINS SIDE WINDOW SHATTERED IN FLIGHT.  FOLLOWED QRH, DIVERTED TO NEAREST AIRPORT AND LANDED WITHOUT FURTHER IN	CIDENT.   R&R CAPTAINS SIDE WINDSHIELD IAW AMM 56-11-01 AND CARRIED OUT LEAK CHECKS.  ACFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090206			2009	2	6	CA090107008      	4	20081226	G	3417	8220372445	ADC             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					NR 1	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			4396 								(CAN) JUST AFTER TAKEOFF, THE CREW RECEIVED RED FLAGS FOR THE CAPTAINS AIRSPEED, ALTIMETER AND VSI MOMENTARILY.  INDICAT	IONS RETURNED TO NORMAL SHORTLY AFTER. THE FLIGHT RETURNED TO THE DEPARTURE AIRFIELD AND LANDED WITHOUT FURTHER INCIDENT	.  MX R&R THE NR 1 ADC AND OPS CHECKED SERVICEABLE.  ACFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090206		EA  	2009	2	6	CA090107009      	1	20081222	G	2750		FLAP SYSTEM     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					TE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) FLT CREW REPORTED FLAP FAIL MSG WHILE ON APPROACH WHEN FLAPS SELECTED OUT OF 0 DEG.  QRH FOLLOWED AND LANDED WITH 	FLAPS AT 0 DEG WITH NORMAL BRAKING.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090206		EA  	2009	2	6	CA090107011      	1	20081219	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											(CAN)  EXPERIENCED FLAP FAILURE.   REPLACED BPSU.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		EA  	2009	2	3	CA090107014      	1	20081216	G	3020	5399001	ANTI-ICE VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  						FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA				12356							(CAN) FLT CREW REPORTED RIGHT COWL ANTI-ICE MESSAGE IN FLIGHT WITH ANTI-ICE SELECTED ON.  COMPLETED QRH AND MESSAGE PERS	ISTED.  DIVERTED AND LANDED WITHOUT FURTHER INCIDENT.  REMOVED AND REPLACED RIGHT COWL ANTI-ICE VALVE AND OPS CHECKED SE	RVICEABLE.  AIRCRAFT RETURNED TO SERVICE.  ANTI-ICE VALVE 5399-00-1 0186A FAILED RIGHT COWL 13148/12356 (VALVE TIMES).				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		EA  	2009	2	3	CA090107015      	1	20081215	G	4930	600970249	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  					APU FUEL SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			19855								(CAN) WHILE SERVICING APU MAINTENANCE NOTICED A FUEL SMELL.  OPENED PANEL AND RAN APU.  FOUND APU INLET BELLOWS RETAININ	G CLIP RIGHT SIDE SLID AFT AND CHAFED HOLE IN METERED FUEL LINE TO NOZZLES.  FUEL WAS DRIPPING ON IGNITER BOX.  REMOVED 	AND REPLACED FUEL LINE AND REPOSITIONED RETAINING CLIP AND PLACED SPIRAL WRAP ON FUEL LINE BEHIND CLIP.  AIRCRAFT RETURN	ED TO SERVICE.  FUEL LINE 600-97024-9 N/A CHAFED APU COMPARTMENT 20830/19855.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		EA  	2009	2	3	CA090107016      	1	20081022	G	4920	38004883	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	30070	NE  						SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			CA				20144							(CAN) FLT CREW REPORTED SMOKE IN FLIGHT DECK AFTER LANDING.  SMOKE DISSIPATED AFTER PACKS SELECTED OFF, APU 3800488-3 P-	601 19506/20144 (APU TIMES).					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
	20090203		EU  	2009	2	3	CA090108002      	1	20081229	G	3260	A254210012	UPLOCK          			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2*    	 	GL  					NLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA			59564								(CAN) IN DESCENT TO LGW, FLIGHT CREW REPORTED, L/G NOSE WHEEL UNSAFE INDICATION.  PERFORMED L/G GRAVITY EXTENT ION.  NLG	 UPLOCK ASSY WAS REPLACED AND OPERATIONAL CHECK WAS CARRIED OUT SERVICEABLE.  AS SAFETY PRECAUTION, BOTH NOSE LANDING GE	AR DOOR SEQUENCE VALVE WERE REPLACED.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
	20090203		SW  	2009	2	3	CA090108003      	1	20081226	G	5310		DOOR FRAME      			BBAVIA	7     	7AC         	2110102	SW  										FUSELAGE	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2508 								(CAN) DOOR TUBE RUSTED THROUGH LOWER END, REPLACED.						1	H	7	1 	3O				A759    					 
	20090203		NM  	2009	2	3	CA090109002      	1	20081214	G	7930	8D1437	PRESSURE SWITCH 			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  		MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) NR 1 ENG OIL PRESS WARNING LIGHT ILLUMINATION IN FLIGHT, ENGINE SHUTDOWN IN ACCORDANCE WITH QRH/AFM, AIRCRAFT RETU	RNED TO DEPARTURE AIRPORT AND LANDED SAFELY.  MAINTENANCE DETERMINED NR 1 OIL PRESSURE SWITCH FAILED.  SWITCH REMOVED AN	D REPLACED.  ENGINE RUNS CARRIED OUT, OPERATION SATISFACTORY.  AIRCRAFT RETURNED TO SERVICE.  SWITCH MANUFACTURER (CUSTO	M CONTROL SENSORS) NOT IN THE DROP DOWN LIST.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090204		CE  	2009	2	4	CA090112004      	1	20081214	G	2823	C2915030101	SELECTOR        			CESSNA	206   	U206D       	2073342	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FUEL SYSTEM	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			10851	10851							(CAN) FUEL SELECTOR CLOSED DUE TO FLEX HOSES IN ENGINE COMPARTMENT BEING REPLACED.  AFTER HOSES INSTALLATION FUEL SELECT	OR OPEN TO CHECK FOR LEAKS, FUEL LEAK FOUND ON BELLY.  FUEL SELECTOR WAS LEAKING ON THE TOP, SOURCE OF LEAK SHAFT ON THE	 TOP.  SELECTOR WAS ORIGINAL INSTALLATION (1969).  UNIT REPLACED WITH NEW UNIT FROM CESSNA.  NO FURTHER LEAKS. (TC NR 20	090112004)			1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P3EA	 
	20090205		SO  	2009	2	5	CA090112008      	2	20081031	G	7414		GASKET          	BENDIX      		PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					MAGNETO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				23   							(CAN) ENGINE INSPECTED FOR OIL LEAK AT REAR ACCESSORY SECTION, FOUND OIL COMING FROM RIGHT MAGNETO ATTACH GASKET.  MAGNE	TO REMOVED, GASKET AND ENGINE MATING SURFACE INSPECTED OK.  MOUNTING FLANGE ON MAGNETO INSPECTED AND FOUND CRACKED IN AR	EA WHERE BOTH HOLD DOWN CLAMPS MAKE CONTACT, FLANGE WAS ON THE VERGE OF BREAKING OFF COMPLETELY WHICH WOULD RESULT IN MA	GNETO FAILURE AND POSSIBLE COMPLETE ENGINE OIL LOSS.  LEFT MAGNETO REMOVED FOR INSPECTION, FOUND SATISFACTORY.  AIRCRAFT	 OWNER REPORTED THAT LEFT MAGNETO WAS REPLACED FOR SAME REASON ABOUT 50 HOURS EARLIER.  SUSPECT CAUSE OF CRACKING FLANGE	S IS FROM OVERTORQUING HOLD DOWN CLAMP NUTS.  (TC NR 20090112008)	1	L	7	1 	3O	3	O		2A13    	E9CE				 
	20090206		CE  	2009	2	6	CA090116004      	1	20081229	G	7500		MOTOR           			CESSNA	500   	560CESSNA   	2076750	CE  	PWC   	545   	PW545B      		NE  					HBV TORQUE	FAILED          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								654577883			(CAN) THE CREW REPORTED VIBRATION ON RT ENGINE AND THE EEC REVERTED TO MANUAL MODE. THEY OBSERVED A SUDDEN RISE IN ENGIN	E TEMPERATURE AND ELECTED TO SHUT IT DOWN BEFORE MAKING A SINGLE ENGINE LANDING. REPLACED THE BLEED-OFF VALVE AND TORQUE	 MOTOR BEFORE THE ACFT WAS RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
	20090206		NE  	2009	2	6	CA090116006      	2	20081224	G	7250		TURBINE BLADES  			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	120   	PW123D      	52152	NE  					ENGINE	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, AT FL68, THE ENGINE LOST POWER.  IT WAS SHUT DOWN AND SECURED AND THE ACFT RETURNED TO THE POINT OF 	DEPARTURE WHERE A SINGLE ENGINE LANDING WAS ACCOMPLISHED.  GROUND INSPECTION FOUND THAT THE PROPELLER WOULD NOT ROTATE A	ND POWER TURBINE BLADES WERE FRACTURED. P&WC WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLI	SHED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
	20090206		NE  	2009	2	6	CA090116007      	2	20081222	G	7200		ENGINE          			AEROSP	ATR72 	ATR72       	       	EU  	PWA   	PW120 	PW127       	 	NE  						POWER LOSS      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE ENGINE TORQUE AND TEMPERATURE INCREASED UNCOMMANDED.  CREW REDUCED POWER BUT THE ENGINE DID NOT	 RESPOND AND WAS SHUT DOWN AND SECURED.  A SINGLE ENGINE LANDING WAS ACCOMPLISHED AT THE POINT OF ORIGIN.  THE ENGINE WI	LL BE REMOVED AND INVESTIGATED.				2	H	7	2 	4T	4	T	RT	        	E20NE				 
	20090206		NE  	2009	2	6	CA090116008      	2	20081229	G	7200		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  		MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE CREW NOTED A RAPID INCREASE IN FUEL FLOW, FOLLOWED BY A RAPID RISE IN TEMPERATURE AND TORQUE ON 	THE LT ENGINE. THE ENGINE DID NOT RESPOND TO POWER LEVER MOVEMENTS AND AN UNCOMMANDED IFSD OCCURRED.  A SINGLE ENGINE LA	NDING WAS MADE AT THE POINT OF DEPARTURE. GROUND INSPECTION FOUND METAL PARTICLES IN THE OIL TANK.  THE ENGINE WILL BE R	EMOVED.  WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
	20090206		GL  	2009	2	6	CA090119011      	1	20081228	G	2421	A3579101	GENERATOR       			BOMBDR	BD100 	BD1001A10   	1390044	GL  	HNYWL 	AS907 	AS90711A    	33908	WP  						FAULTED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			CA											(CAN) ACFT ARRIVED WITH RT GEN FAULT. RT COWL OPEN, FOUND GEN DAMAGED AND DISLODGED OUT FROM IT`S EXHAUST HOUSING. SHAFT	 DIDN`T SHEARED. THE BACK MATING PLATE AT THE GEARBOX ASSY SLIGHTLY CHAFED DUE TO IN CONTACT WITH GEN SHAFT. LMM AS907-1	-1A CHAP 72-61-01, FIG 801,PG 802, ITEM 170)				2	L	7	2 	4F	4	F	RT	T00005NY	E00010LA				 
2008032500060	20080325	00060	NM  	2008	3	25	CO1Y200800001    	1	20080307	G	5340	ARB71701	SUPPORT FITTING 			DOUG  	MD11  	MD11F       	3023600	NM  										MLG DOOR	CORRODED        	B			CO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	725BC					48503				AT LT MLG AND DOORS, FOUND BOLTS LOWER AND UPPER WITH PLI LOOSE ON LT FRAME SUPPORT.						2	L	7	3 	4F			RT	A22WE   					 
2008041400015	20080414	00015	NM  	2008	4	14	CO1Y200800002    	1	20080327	G	5510		STRUCTURE       			DOUG  	MD11  	MD11F       	3023600	NM  										ZONE 400	CORRODED        	B			CO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	725BC					48503				AT HORIZONTAL STABILIZER CTR SECTION, FOUND CORROSION INSIDE BARREL NUT HOLE NR 36 LT HORIZ STAB.						2	L	7	3 	4F			RT	A22WE   					 
2008042800318	20080428	00318	NM  	2008	4	28	CO1Y200800003    	1	20080114	G	5755	ARC44231	HINGE BRACKET   			DOUG  	MD11  	MD11        	3023602	NM  										LT SPOILER	WORN            	B			CO1Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	725BC					48503				LT SPOILER NR1 FOUND WITH PLAY.						2	L	7	3 	4F			RT	A22WE   					 
2008022500008	20080225	00008	NE  	2008	2	25	CRSCW1R075K      	1	20080221	G	6410	7610105017045	SPAR            	SKRSKY      		SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6*        	52043	EA  					T/R BLADE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	780P	2905 			A11602002X	760359				DURING A ROUTINE INSP, A SLIGHT, OCCASIONAL CLICK WAS HEARD WHILE FLEXING TAIL ROTOR BLADE. BLADE ASSY (P/N 76101-05501-	042, S/N A245-00153) WAS REMOVED FOR PRECAUTIONARY MEASURES AND SENT FOR INSP/EVALUATION. UPON DISASSEMBLY AND INSP, SPA	R WAS FOUND TO HAVE CRACKS COMING FROM ELIPITICAL PLUG AREA. SPAR WAS SUBSEQUENTLY CHANGED, BLADE INSPECTED AND RETURNED	 TO SERVICABLE CONDITION. SCRAPED SPAR TOTAL TIME WAS 2905.8 HOURS. THIS IS THE SECOND SPAR WE HAD CRACKED.			1	G	7	2 	4U	3	T		H1NE    	E2NE				 
2008020400104	20080204	00104	CE  	2008	2	4	CWQR200801       	1	20080129	G	5330	651201026	SKIN            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					FUSELAGE	CRACKED         	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	839QS					5600690				DURING A PHASE 1-4 INSPECTION THE TECHNICIAN NOTICED A SMALL CRACK IN THE PAINT UNDER THE RT ENGINE PYLON. REMOVED THE P	AINT AND FOUND A 1.5 INCH CRACK. STARTING AT THE FWD BOTTOM CUT OUT FOR THE FWD SUPPORT BEAM. APPEARS THAT THERE WAS NOT	 ENOUGH CLEARANCE IN THE TAILCONE SKIN FOR THE MOVEMENT OF THE ENGINE BEAM WHEN THE AIRCRAFT WAS MANUFACTURED.  SUBMITTE	D TO MFG ENGINEERING FOR REPAIR.			2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
	20080909		CE  	2008	9	9	CWQR200808       	1	20080821	G	5320	661503517	SUPPORT BRACKET 			CESSNA	560   	560XL       	2076702	CE  										FUSELAGE	CRACKED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	679QS					5605279				DURING A PHASE 1-4 INSP, FOUND THE SUPPORT BRACKET CRACKED, CRACK IS LOCATED IN THE SUPPORT BRACKET FOR THE ECU, THE CRA	CK INTERSECTS A HOLE FOR THE NUTPLATE THAT ATTACHES ONE OF THE ECU MOUNTING BOLTS. SERVICE CONDITION REPORT HAS BEEN FIL	ED WITH MFG UNDER SCR# 376154.				2	L	7	2 	4F			RT	A22CE   					 
	20081001		CE  	2008	10	1	CWQR200809       	1	20080821	G	5320	661503515	SUPPORT BRACKET 			CESSNA	560   	560XL       	2076702	CE  										FUSELAGE	CRACKED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	679QS					5605279				DURING A PHASE 104 INSPECTION, FOUND THE SUPPORT BRACKET CRACKED.  CRACK IS ABOUT 1.5 INCHES LONG AND IS CENTERED AT THE	 ATTACH POINT FOR THE VALVE.  SERVICE CONDITION REPORT HAS BEEN FILED WITH MFG UNDER SCR NR 376160. (K)					2	L	7	2 	4F			RT	A22CE   					 
2008031300048	20080313	00048	SO  	2008	3	13	DAL26220220      	1	20080218	G	4910	1159AC30551103	DUCT            			GULSTM	G1159 	GIV         	3980115	SO  										APU INLET	CRACKED         	E			CLWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	589HM	6464 				1153				A 9 INCH CRACK IN THE APU INLET DUCK (TITANIUM).						2	L	7	2 	4F			RT	A12EA   					 
2008031700252	20080317	00252	EU  	2008	3	17	DJSR20080125     	1	20080125	G	3610	32156321	PRESSURE VALVE  			AMD   	FALC20	FALCON20C5  	2730107	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					BLEED AIR SYS	MALFUNCTIONED   	B			DJSA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	23	531FL	15   				113				NR 1 BLEED OVERHEAT LIGHT ILLUMINATED PASSING 15,000 WITH CORRESPONDING CABIN PRESSURE FLUCTUATIONS.						2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
2008031000343	20080310	00343	EU  	2008	3	10	DJSR20080205     	1	20080205	G	5610	MY20268109	WINDSHIELD      			AMD   	FALCON	FALCON20    	2730103	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	CRAZED          	D			DJSR	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	23	541FL	3    				48				F/O`S WINDSHIELD OUTER PANE CRAZED OBSTRUCTING F/O`S VISION.  (K)						2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
2008032000021	20080320	00021	EU  	2008	3	20	DJSR20080226     	1	20080226	G	3231		MECHANISM       			AMD   	FALC20	FALCON      	2720302	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					NLG DOOR	ICED            	B			DJSA	A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			GL	23	521FL	15493				68				NOSE GEAR DOOR WOULD NOT CLOSE IN FLIGHT.						2	L	7	2 	4F	4	F		A7EU    	E6WE				 
2008042800344	20080428	00344		2008	4	28	DJSR20080417     	4	20080417	G	3417	065008206	AIR DATA MODULE 			AMD   	FALC20	FALCON20C5  	2730107	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	MALFUNCTIONED   	B			DJSA	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	23	511FL		68   			122				ALTIMETER SYSTEMS SHOWING MISCOMPARE (EXCEEDING 50 FT AT 5000 FT).						2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
2008012200089	20080122	00089	WP  	2008	1	22	DSC4331DL6292    	2	20080110	G	7210	31022811	RETAINER SEAL   								GARRTT	TPE331	TPE33110R   	0517	WP  					ENGINE	CRACKED         	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	15							P37369C			NO GEARCASE NEGATIVE PRESSURE INDICATED DURING ENGINE TEST STAND FUNCTIONAL TESTING.  TROUBLESHOOTING FOUND CRACKS IN SE	AL RETAINER.  SUBJECT RETAINER IS MADE WITH ALUMINUM. OLDER PN 693905-10 IS MADE WITH STEEL.  SB 72-0224 AUTHORIZED INST	ALLATION OF ALUMINUM RETAINER.									4	T			E4WE				 
	20080603		EU  	2008	6	3	DT1R200800001    	1	20080508	G	2700	1090020477	LEVER           			AGUSTA	A109  	A109S       	0260103	EU  										YAW TRIM SYSTEM	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	167JC	40   				22067				OPENED THE ACCESS PANEL UNDER THE CO-PILOT'S SEAT, FOUND THE YAW TRIM LEVER (PN 109-0020-47-7 NSN) DETACHED FROM THE YAW	 TRIM MOTOR SHAFT.  NO DAMAGE NOTED TO THE MOTOR SHAFT.  THE LEVER WAS INTACT BUT DAMAGED AT THE POINT WHERE IT CONTACTS	 THE SHAFT, BUT HAD THE CORRECT HARDWARE AND COTTER PIN INSTALLED.  THE APPLICABLE PUSH-ROD END (ATTACHED TO THE LEVER) 	WAS ALSO LOOSE.  INSPECTED AND RETORQUED THE ROD-END.  REPLACED AND TORQUED THE LEVER, REINSTALLED TO THE YAW TRIM MOTOR	 SHAFT, AND COMPLETED OPERATIONAL CHECK WITH NO DEFECTS NOTED.		1	G	7	1 	3U			RT	H7EU    					 
	20080828		NM  	2008	8	28	DU4R2008238      	1	20080822	G	5322		SHEAR TIE       			DOUG  	MD80  	MD83        	3023681	NM  										FS 148 L22L	DAMAGED         	B			DU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	874GA					49643				ACFT ARRIVED, WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE.  (S)						2	L	7	2 	4F			RT	        					 
	20080828		NM  	2008	8	28	DU4R2008238A     	1	20080822	G	5330		SKIN            			DOUG  	MD80  	MD83        	3023681	NM  										FS 148 L22L	DAMAGED         	B			DU4R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SO	15	874GA					49643				ACFT ARRIVED, WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE.  (S)						2	L	7	2 	4F			RT	        					 
	20081201		NM  	2008	12	1	DU4R2008263      	1	20081124	G	5315	36726	FLOORBEAM       			BOEING	737   	7378Q8      	13844BX	NM  										FUSELAGE	CORRODED        	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	171LF					30637				FOUND CORROSION IN AFT PIT ON TOP SURFACE OF FLOORBEAM AT BS 787 TO BS 847 RBL 16.						2	L	7	2 	4F			RT	A16WE   					 
	20090105		NM  	2009	1	5	DU4R2008273      	1	20081213	G	5314		KEELBEAM        			BOEING	757   	75723APF    	1384966	NM  										BS 956	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION AT TIMCO-LCQ, LAKE CITY, FL FOUND KEEL BEAM LOWER SURFACE CORSS BRACE HAS CORROSION AT BS 95	6S/O 318002   N/R #35360					2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008274      	1	20081213	G	5314		KEELBEAM        			BOEING	757   	75723APF    	1384966	NM  										BS 1040	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND KEELBEAM LOWER SURFACE CROSS BRACE HAS CORROSION AT BS 1040.						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008275      	1	20081216	G	5730		SKIN            			BOEING	757   	75723APF    	1384966	NM  										LT WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND LT WING HAD CORROSION IN UPPER SKIN AT ALL VORTEX GENERATORS						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008276      	1	20081216	G	5330		SKIN            			BOEING	757   	75723APF    	1384966	NM  										BS 600-612	DENTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND 3 EA.  DENTS IN LOWER FWD FUSELAGE BELOW MLG DOOR SCUFF PLATE BS 600-612.						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008277      	1	20081216	G	5330		SKIN            			BOEING	757   	75723APF    	1384966	NM  										BS 1125	DENTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND DENT IN EXT. FUSELAGE SKIN BS 1125, S-10L LAP SEAM.						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008278      	1	20081216	G	5330		SKIN            			BOEING	757   	75723APF    	1384966	NM  										BS 1364-1410	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND NUMEROUS CREASES IN EXT. FUSELAGE SKIN BS 1364 - 1410, S-26L TO S-26R						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008279      	1	20081217	G	5711		SPAR            			BOEING	757   	75723APF    	1384966	NM  										LT WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND CORROSION ON LT WING REAR SPAR BELOW LEFT AFT BOOST PUMP RSS 185.						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008280      	1	20081217	G	5314		KEELBEAM        			BOEING	757   	75723APF    	1384966	NM  										BS 996	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND CORROSION ON KEELBEAM LOWER SURFACE CROSS BRACE AT BS 996.						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008281      	1	20081216	G	5330		SKIN            			BOEING	757   	75723APF    	1384966	NM  										BS 1932-1936	CORRODED        	B				R				AUTOROTATION            				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND CORROSION ON EXT SKIN AROUND APU OIL FUEL DRAIN MAST RT APD ACCESS DOOR.						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008282      	1	20081217	G	5320		SUPPORT         			BOEING	757   	75723APF    	1384966	NM  										BS 1098	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND CORROSION ON WING TO BODY FAIRING SUPPORT ABOVE RT WING AT BS 1098.						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008283      	1	20081210	G	5320	148N31388000	STRAP           			BOEING	757   	75723APF    	1384966	NM  										ZONE 300	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION,  FOUND HEAVY CORROSION ON 2 EA. SUPPORT STRAPS REMOVED FROM BS 1825, B/O 0, RT SIDE TO HORI	Z STAB.					2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008284      	1	20081217	G	5711	112N100217	SPAR            			BOEING	757   	75723APF    	1384966	NM  										ZONE 500	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND CORROSION ON WEB, LT WING REAR SPAR, ABOVE LT AFT BOOST PUMP WS 188						2	L	7	2 	4F			RT	A2NM    					 
	20090105		NM  	2009	1	5	DU4R2008285      	1	20081228	G	5512		SKIN            			BOEING	757   	75723APF    	1384966	NM  										ZONE 900	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	868AN					24868				DURING SCHEDULED INSPECTION, FOUND CORROSION IN SEVERAL AREAS OF UPPER SURFACE SKINS ON LT HORIZONTAL STABILIZER.						2	L	7	2 	4F			RT	A2NM    					 
	20080828		NM  	2008	8	28	DUR42008238B     	1	20080822	G	5313		LONGERON        			DOUG  	MD80  	MD83        	3023681	NM  										FS 148 L22L	DAMAGED         	B			DU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	874GA					49643				ACFT ARRIVED WITH RAMP DAMAGE TO THE FUSELAGE SKIN AND STRUCTURE AT FS 148 LONGERON 22L, AND SHEAR TIE.  (S)						2	L	7	2 	4F			RT	        					 
2008050800097	20080508	00097	NM  	2008	5	8	DXTA200803018    	1	20080424	G	2613	RP16100	SENSOR          			AMD   	FALC50	FALCON2000  	2730170	NM  	PWC   	PW308 	PW308C      	52182	NE  					BLEED AIR SYS	INOPERATIVE     	E			DXTA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	07	223QS	430  				86				BLEED OVERHEAT LIGHT CAME ON 2 MIN AFTER TAKEOFF.  CHECKLIST ACCOMPLISHED AND CREW WAS UNABLE TO ISOLATE THE MALFUNCTION	.  FAULT CODE 404 AND 428.  BLEED OVERHEAT COMES ON WITH APU BLEED ON AND ENGINE OFF. REMOVED & REINSTALLED TEMP SENSOR 	L70HU. OPS & LEAK CHECKS GOOD IAW MM 36-70-00				2	L	7	2 	4F	4	F	RT	A50NM   	E00065EN				 
	20080715		CE  	2008	7	15	E812008F00000    	1	20080213	G	5320	50430043619	CHANNEL         			BEECH 	B300  	B300        	1159232	CE  										FUSELAGE	CRACKED         	B			E81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	37TD	6102 				FL25				INVESTIGATED PILOT COMPLAINT OF LOOSE FUSELAGE SKIN RIVETS AT CABIN DOOR HINGE AREA. FOUND FUSELAGE DOOR FRAME CHANNEL C	RACKED. CABIN DOOR DAMPER ACTION ALSO REPORTED AND FOUND TO BE WEAK. SUSPECT CAUSED BY CABIN DOOR "BOTTOMING OUT" EXCESS	IVELY HARD OR EXCESSIVE WEIGHT ON DOOR OVER REPEATED CYCLES. TECH/ INSPECTORS SHOULD  CHECK DOOR DAMPNER OPERATION AT SC	HEDULED PHASE INSPECTIONS AND CORRECT IF WEAK OPERATION NOTED.  EVIDENCE OF LOOSE HINGE AREA RIVETS SHOULD ALSO BE INVES	TIGATED FOR POSSIBLE CRACKED STRUCTURE UNDER THRESHOLD. (K)		2	L	7	2 	4T			RT	A24CE   					 
2008050800091	20080508	00091	NE  	2008	5	8	EY2R080424001    	3	20080424	G	6111	7826761	BEARING         			EMB   	120   	EMB120      	3260201	SO  						HAMSTD	14RF	14RF9       	NE  	BLADE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										(0087319) CRACKED RACE.						2	L	7	2 	4T			RT	A31SO   		6	C	P11NE	 
2008011400041	20080114	00041	EA  	2008	1	14	FAA010808001     	2	20080108	G	7200	MILH60001	BREATHER TUBE   			AYRES 	S2    	S2RT15NORMAL	0970105	SO  	PWA   	PT6   	PT6*        	52043	EA  					ENGINE	COLLAPSED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	2281A	7940 				T15034				ENGINE BREATHER HOSE SWELLED ON INSIDE FROM THE ORIGINAL 1INCH DIAMETER TO .3750 INCH DIAMETER FROM HOT OIL FUMES. THRUS	H ADDRESSED THE SAME PROBLEM ON THE MFG POWERED LINE. THIS IS NOT AN ISOLATED INCIDENT. THE CONDITION NOTED CAN ONLY BE 	FOUND AFTER HOSE REMOVAL. EXTERIOR OF HOSE LOOKS OK. SUGGEST A SCHEDULE OF REPLACEMENT EVERY 2000 HOURS.				1	L	7	1 	3T	3	T		A3SW    	E2NE				 
2008013100007	20080131	00007	EU  	2008	1	31	FAA011808001     	2	20080104	G	7321	CASC514	FUEL CONTROL    			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					ENGINE	INOPERATIVE     	C				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			EA	25	396U	4905 				1350	16820			ON APPROACH TO TTN THE AUTO THROTTLES DISENGAGED. THE RT LEVER KNOB WAS ONE KNOB AFT OF THE LT.  WHEN RT LEVER WAS ADVAN	CED FORWARD THE RT ENGINE DID NOT RESPOND TO THROTTLE MOVEMENT.					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2008013100008	20080131	00008	SO  	2008	1	31	FAA011808002     	1	20080110	G	7930		OIL SYSTEM      			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					ENGINE	LOW PRESSURE    	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			EA	17	396U	4905 				1350	16820			30 MINUTE INTO THE FLIGHT OIL PRESSURE DROPPED TO 7 PSI. NO ASSOCIATED CAS MESSAGE. OIL TEMP WAS SLIGHTLY HIGHER THAN LT	 ENGINE. FUEL TEMP WAS 19 DEGREES HIGHER THAN LT.  DURING DESCENT OIL PRESSURE CAME BACK TO 47 PSI.					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2008013100298	20080131	00298	CE  	2008	1	31	FAA012408001     	1	20080124	G	2710	556536118	CABLE           			CESSNA	500   	550         	2076604	CE  										AILERON	WORN            	B			N81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	338B					5501132				DURING A PHASE 5 IT WAS FOUND THAT THE AILERON CABLES WERE LOCATED IN THE WRONG GROVES OF THE FUSELAGE SECTOR, CAUSING G	ROOVES TO BE WORN INTO THE SECTOR BY THE CABLES. THERE IS A SPECIAL "NOTE" IN THE MAINTENANCE MANUAL 27-11-08 SECTION 7 	FOR THE AILERON LEFT WING CONTROL CABLE REMOVAL/INSTALLATION, STATING CABLES 8 AND 9 ROUTE AROUND THE SECTOR ASSEMBLY IN	 THE LOWER GROOVE.  THIS IS THE FIRST INSPECTION OF THIS SINCE THE AIRCRAFT WAS NEW AND THE IMPROPER ROUTING WAS DONE AT	 THE FACTORY.  CORRECTIVE ACTION WAS TO REPLACE THE PART.		1	L	7	2 	4F				A22CE   					 
2008031200003	20080312	00003	CE  	2008	3	12	FAA021208001     	1	20080212	G	2810		FUEL CAP        			CESSNA	172   	172         	2072402	CE  											DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15		4413 								LEFT FUEL GAUGE INDICATED 10 GAL. IN TANK AT ALL FUEL LEVELS. THE TANK WAS DRAINED AND ACCESS COVER REMOVED. THE FUEL CA	P RETAINING CHAIN WAS FOUND TO HAVE COME LOOSE ON THE TANK END "S" HOOK AND WRAPPED AROUND THE ARM ON THE FUEL LEVEL SEN	DING UNIT LOCKING IT AT A 10 GAL. INDICATION.				1	H	7	1 	3O			NT	3A12    					 
2008041400001	20080414	00001		2008	4	14	FAA030408001     	1	20080304	G	4990		PUMP            																	APU ENGINE	FAILED          	B				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	99		13599	1468 							2 APUS WERE REPORTED LOP AUTO SHUTDOWN. DISASSEMBLY OF THE ENGINES REVEALED LP ROLLER BEARING FAILURE. ONE OF THE ENGINE	'S BEARING DID NOT HAVE LUBRICATION AT ALL.  THE OIL PUMPS P/N 3880998-1 WERE ROUTED TO BENCH TEST AND LOW PERFORMANCE W	AS NOTED. DISASSEMBLY OF THE OIL PUMP REVEALED PORT PLATE P/N 3603681-1 HAD SIGNIFICANTLY WORN. IT ALLOWED THE PORT PLAT	E MOVE TO RESTRICT THE OIL INLET PORT AND OUTLET PORT AND CAUSED LOW PUMP PERFORMANCE. THE BEARING FAILURE WAS A CONSEQU	ENCE OF INSUFFICIENT OIL PRESSURE.															 
2008041400003	20080414	00003	CE  	2008	4	14	FAA031008001     	1	20080310	G	2497		WIRE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	ARCED           	B				B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	17	43SA	10256				5500086				PILOT REPORTED CB LABELED LT CB PANEL OPENED IN FLIGHT, PILOT BLEW THE GEAR DOWN AND INITIATED A FLYBY OF THE TOWER TO A	SSURE THE GEAR WAS DOWN. AC LANDED WITHOUT FURTHER INCIDENT.  MAINT INVESTIGATION REVEALED THAT THE CROSSOVER POWER WIRE	 FROM THE CO-PILOTS CB PANEL HAD RUBBED AND ARCED TO THE NUT AND COTTER KEY ATTACHING THE AILERON CABLE LINK FROM THE PI	LOTS CONTROL COLUMN TO THE OB LT FWD AILERON CABLE. THE WIRE WAS NOT PROPERLY ROUTED OR SECURED. THE WIRE LAYS UNDERNEAT	H THE AIR CONDITIONER DUCTING AND IS NOT VISIBLE WITH ONLY THE COCKPIT FLOORBOARDS REMOVED. THE WIRE SUPPLIES POWER FROM	 THE CO-PILOTS CB PANEL TO THE PILOTS CIRCUIT BREAKER PANEL BUSS THAT SUPPLIES POWER TO THE FOLLOWING BREAKERS ACM-2, W/	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2008040300042	20080403	00042	CE  	2008	4	3	FAA08222001      	1	20080222	G	2520	3037091BS	SEAT            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  						MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	800RC					258660				DURING PRE-FLIGHT INSPECTION IT WAS NOTED THAT NR2 RT SEATBACK WOULD NOT BREAK OVER AND FOLD FWD IAW PLACARD TO REMOVE E	SCAPE HATCH.  THIS CONDITION PREVENTS ESCAPE HATCH FROM BEING EASILY REMOVED.  FURTHER INVESTIGATION REVEALED THAT THE N	R2 RT SEAT HAD BEEN SWAPPED WITH THE NR1 LT SEAT.  SEATS ARE A DIFFERENT PN.  THIS APPARENTLY HAPPENED AT LAST MAJOR MAI	NT, QUITE SOME TIME AGO.  SEATS ARE A DIFFERENT PN, BUT WE COULD NOT FIND IN WRITING THAT SPECIFIED THIS INFORMATION NOR	 IS THERE A REQUIRED INSP TO CHECK FOR THIS CONDITION.  TALKS WITH MFG TECH INDICATE THAT THIS CONDITION IS FOUND FROM T	IME TO TIME.   ACCOMPLISH AN IMMEDIATE INSP TO VERIFY THAT THE CORRECT PN SEAT IS IN THE NR2 RT POSITION AND CORRECT ANY	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2008012900011	20080129	00011	CE  	2008	1	29	FAA20080118      	1	20080118	G	2752	505212234	ACTUATOR        			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ZONE 600	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	85TB					LJ833				RT OB FLAP ACTUATOR ASSY, PISTON TUBE CRACKED 100 PERCENT IN DEPTH, 100 PERCENT ENTIRE LENGTH OF TUBE.  CRACK RUNS PARAL	LEL TO TUBE .					1	L	7	2 	3T	4	T		3A20    	E4EA				 
2008040200027	20080402	00027	CE  	2008	4	2	FAA2008123001    	1	20080123	G	6120	5221220F	PILOT VALVE     	WOODWARD    		BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					PROP GOVERNOR	BROKEN          	B				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			EA	63	401BC		697  		00066	TH1668				PROPELLER WENT TO FEATHER IN FLIGHT AND WAS UNABLE TO UNFEATHER. AFTER RECEIVING THE GOVERNOR FOR INSPECTION IT WAS DISC	OVERED THAT THE BOTTOM END OF THE PILOT VALVE (P/N 5221-220) HAD BROKEN OFF AND WAS MISSING. IT WAS PRESUMED THAT IT EXI	TED THE BOTTOM END OF THE DRIVE GEAR AND ENTERED THE ENGINE SUMP. THE OPERATOR WAS NOTIFIED AND THE MISSING PIECE WAS RE	TRIEVED.			1	L	7	2 	3O	3	O		3A16    	E3SO				 
	20081217		CE  	2008	12	17	H51R08001        	1	20081203	G	2620	2MD31AX287G	SWITCH          			LEAR  	35    	31A         	5170531	CE  										EXTINGUISHERS	STICKING        	B			H51R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	03	420LJ	3052 				111				FAILURE OF SWITCH IN THE ENGINE FIRE PULL SWITCH ASSY.  AFTER ACCESSING THE FIRE PULL SWITCH ASSEMBLY TO VERIFY AIRWORTH	INESS DIRECTIVE 95-21-03, AMENDMENT 39-9388, APPLICABILITY, THE S4 MICROSWITCH FAILED IN THE CLOSED POSITION.  THE AIRWO	RTHINESS DIRECTIVE WAS ISSUED FOR THIS PROBLEM, BUT WAS NOT APPLICABLE TO THIS SWITCH BY S/N, SUSPECT ADDITIONAL LOTS MA	Y BE EFFECTED.  AFTER REASSEMBLY OF GLARESHIELD, FUNCTIONAL TESTS REVEALED THE MICROSWITCH HAD STUCK CLOSED, PREVENTING 	LT ENGINE BLEED AIR FROM WORKING.  VISUAL INSPECTION OF SWITCH SHOWS THE S4 MICROSWITCH ACTUATOR STUCK IN THE RECESSED P	OSITION.  SWITCH P/N 6608214-3, S/N 2280, F.T. DATE FEB '93, MANUFACTURE EATON P/N 865001-3  AD WAS FOR SWITCHES S/N 232	2	L	7	2 	4F			RT	A10CE   					 
2008040200037	20080402	00037		2008	4	2	HN8R200800001    	4	20080122	G	6122	6602263	CONTROL CABLE   			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					PROP GOVERNOR	BROKEN          	B			HN8R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CE	05	58102	298  				243008				PROPELLER GOVERNOR CONTROL CABLE BROKE WHILE AIRCRAFT WAS ON GROUND.						1	L	7	1 	3O	3	O		2A3     	1E10				 
2008040400003	20080404	00003	NM  	2008	4	4	IU6R232726       	1	20080306	G	2710	654484515	MANIFOLD        			BOEING	737   	737         	UTILSYS	NM  											BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		71885								FILTER BOWL BORE OF MANIFOLD BROKE OFF AT THE THREADS.						2	L	7	2 	4F			RT	A16WE   					 
	20080522			2008	5	22	LJER050608       	2	20080506	G	7414	10357424	BUSHING         		S4LSC200    	ROBSIN	R22   	R22BETA     	7640110	NM  										MAGNETO	LOOSE           	B			LJER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	7155W	531  	531  		E07DA122R	2759				ROTOR BUSHING DEBONDED AND LOOSE, CAUSED ROTOR AND GEAR PLAY.  MAGNETO FAILED.						1	G	7	1 	3O				H10WE   					 
2008050800025	20080508	00025	CE  	2008	5	8	LJER210408       	1	20080421	G	3233	12810016	HOUSING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					LT MLG ACTUATOR	CRACKED         	B			LJER	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			NM	09	9877B	594  				172RG1066				LANDING GEAR FAILED TO RETRACT.  LT MAIN ACTUATOR HOUSING CRACKED AT MOUNTING HOLE.						1	H	7	1 	3O	3	O		3A17    	E286				 
	20080715		CE  	2008	7	15	MT9R00000040     	1	20080530	G	7603	SL60061	POWER LEVER     			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					ENGINE CONTROL	BROKEN          	B			MT9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	1324G					208B0777				ENGINE CONTROL QUADRANT POWER LEVER SPRING STOP BROKEN. (K)						1	H	7	1 	3T	3	T		A37CE   	E2NE				 
2008041000237	20080410	00237	GL  	2008	4	10	MV1R200808061    	2	20080402	G	7210	6898785	SHAFT           	ALLSN       		SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR1 PTO GEAR	CRACKED         	B			MV1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	38	2822 	1058 		CAG90287	760087	CAE890282			OIL LEAK FROM OUTPUT SHAFT NR 1 ENGINE. INSPECTED AREA NO DEFECTS FOUND AT THAT TIME. REPLACED SHAFT SEAL. GROUND OPS AN	D LEAK CHECK GOOD. AFTER FLIGHT OIL LEAK RETURNED. ON GROUND RUN NO LEAK UNTIL ROTOR WAS RELEASED. OIL LEAK WAS AT OUTPU	T SHAFT. FOUND PTO OUTPUT SHAFT CRACKED. REMOVED ENGINE SENT TO ENGINE SHOP FOR INSPECTION AND REPAIR.				1	G	7	2 	3U	3	U		H1NE    	E1GL				 
	20080520		CE  	2008	5	20	MV1R200808136    	1	20080429	G	2121	1013841761	BLOWER          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ZONE 100	BURNED OUT      	B			MV1R	B	G	H	A	EMER. DESCENT           	O2 MASK DEPLOYED        	DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         	B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			EA	17	35	1486 	178  			BB88				DURING FLIGHT, SMOKE INITIATED FROM BEHIND INSTRUMENT PANEL CENTER BELOW. PROJECT POWER TERMINATED. ALL ELECTRICAL POWER	 NOT NECESSARY FOR FLIGHT, OFF. EMERGENCY LANDING, ON GROUND MAINT FOUND VENT BLOWER ASSY INOP AND BURNED.  BLOWER MEL'D	 AND FLOWN WITHOUT FURTHER INCIDENT.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
	20090106		NE  	2009	1	6	MV1R200808429    	1	20081217	G	6210	7615009100053	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DELAMINATED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	38	213  				S760087				DURING 3 YEAR MAIN ROTOR BLADE INSP FOUND DELAMINATION IN BLACK MAIN ROTOR BLADE ROOT END. DATA SENT TO MFG FOR EVALUATI	ON. TOTAL DELAMINATED AREA IS 1.472 SQUARE INCHES.					1	G	7	2 	3U				H1NE    					 
	20080717		CE  	2008	7	17	N772AF           	1	20080602	G	5540	10164001423	HINGE           			BEECH 	200   	B200        	1152922	CE  										RUDDER	CORRODED        	B			VIBR	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SO	13	772AF	5763 				BB1001				CENTER RUDDER HINGE FOUND TO HAVE EXCESSIVE CORROSION.						1	L	7	2 	4T				A24CE   					 
2008050800042	20080508	00042	CE  	2008	5	8	O7TR200800001    	1	20080311	G	8120	46C22924E	TURBOCHARGER    			CESSNA	182   	T182T       	2072738	CE  										ENGINE	FAILED          	B			O7TR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17										MAJOR TURBO FAILURE DUE TO SEPARATION OF TURBINE WHEEL HEAD FROM SHAFT.						1	H	7	1 	3O			NT	3A13    					 
	20081210		CE  	2008	12	10	OMKR2008-0002    	1	20081124	G	5100		UNKNOWN         			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  						UNKNOWN         	B			OMKR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	6197S					T20608875	L1311661E			NEW AIRCRAFT FROM FACTORY.  PERFORMED AD SEARCH DUE TO EXPORT REQUIREMENT DURING ANNUAL.  FOUND CESSNA SUPPLIED AD LIST 	DID NOT MATCH LYCOMING SUPPLIED LIST, AND CESSNA HAD CHANGED 8 AD SIGN-OFFS FROM LYCOMING.  CESSNA CONTACTED, AND SAID T	HEY HAD TO CHANGE LYCOMING'S LIST BECAUSE IT WAS IN ERROR.  LYCOMING CONTACTED WITH NO REPLY YET.  STRAIGHT FLIGHT PMI B	ROUGHT INTO LOOP, AND WANTED SDR FILLED OUT.  PMI WILL ALSO ACTION.  VERY SERIOUS IN NATURE AS LYCOMING SAYS THEY CHANGE	D NUMEROUS PARTS FOR AD COMPLIANCE, INCLUDING THE CRANKSHAFT, WHEN THESE AD'S DO NOT APPLY IN THE FIRST PLACE.  SUSPECT 	YOU WILL FIND LARGE RUN OF LYCOMING ENGINES WITH THIS SAME PROBLEM.  THESE ENGINES ARE NOT AIRWORTHY WITH FALSE AD LISTS	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
	20081210		CE  	2008	12	10	OMKR2008-0003    	1	20081124	G	5100		NONE            			CESSNA	208   	208B        	2073701	CE  											NONE            	B			OMKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	22430					208B2011				NEW ACFT FROM FACTORY.  PERFORMED AD SEARCH DUE TO EXPORT REQUIREMENT DURING ANNUAL.  FOUND NUMEROUS ADS SIGNED OFF AS C	OMPLIED WITH THAT WERE N/A TO ACFT.  MANY LISTED PARTS THAT WERE SUPPOSEDLY CHANGED.  CONTACTED CESSNA.  WAS ASKED WHY W	ITH SO MANY NEW ACFT BEING RELEASED, NO ONE ELSE WAS COMPLAINING.  AFTER SEVERAL PHONE CONVERSATIONS AND SEVERAL CORRECT	ED LISTS, FINALLY HAD AN ACCEPTABLE LIST.  2 ADS WERE NOT ACCOUNTED FOR AND HAD BEEN ISSUED PRIOR TO THE ACFT BORN-ON DA	TE.  STRAIGHT FLIGHT PMI BROUGHT INTO THE LOOP AND WANTED A SDR SUBMITTED.  HE IS ALSO WORKING.  EXPECT SERIES OF THESE 	CARAVANS TO HAVE SAME PROBLEM.  THESE ACFT ARE NOT AIRWORTHY WITH FALSE AD LISTS.	1	H	7	1 	3T				A37CE   					 
2008020400101	20080204	00101	EU  	2008	2	4	PAI52008S4818    	1	20080130	G	5540		STRUCTURE       			PIAGIO	P180  	P180        	6960204	EU  										RUDDER	CHAFED          	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	134SL	2797 				1100				DURING D-CHECK INSPECTION, FOUND RUDDER TORQUE CHAFED BY AFT FAIRING P/N 80-561004-401.						1	H	7	2 	3O			RT	A59EU   					 
2008022500009	20080225	00009	EU  	2008	2	25	PAI52008S4858    	1	20080212	G	5512		SKIN            			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6*        	52043	EA  					HORIZONTAL STAB	CRACKED         	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	138SL				5072	1103				DURING D-CHECK INSPECTION, FOUND CRACK 2.5 INCHES LONG IN HORIZONTAL STABILIZER LT LOWER COMPOSITE SKIN.  CRACK IS AT IB	 END OF LT HORIZONTAL STABILIZER, 5 INCHES AFT OF LEADING EDGE.					1	H	7	2 	3O	3	T	RT	A59EU   	E2NE				 
2008032800102	20080328	00102	CE  	2008	3	28	PAI52008S4877    	1	20080209	G	3220	07436062	SUPPORT FITTING 			CESSNA	182   	182T        	2072703	CE  										NLG	BROKEN          	B			PAI5	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	470P	719  				18281290				PILOT COMPLAINED OF NOSE WHEEL SHIMMY.  INSPECTION FOUND RIGHT-HAND SIDE OF NOSE GEAR LOWER SUPPORT FITTING BROKEN.						1	H	7	1 	3O			NT	3A13    					 
	20080602		NE  	2008	6	2	PJ6G20080147     	2	20080414	G	7200	310718501	GAS GENERATOR   			AIRTRC	AT802 	AT802       	0390305	SW  	PWC   	PT6   	PT6A67AG    	52211	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	ENGINE	ERODED          	D			PJ6G	O				OTHER                   				P			NO WARNING INDICATION     			AG	AGRICULTURE    	1			SW	11	627JP	566  	566  			8020238	PCERD0147			'C' FLANGE EROSION AT SCAVENGE TUBE OIL COUPLING WITH ASSOCIATED PARTIALLY SEVERED 'T' BOLT.						1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
	20090114		NM  	2009	1	14	R5KB20081220001  	1	20081220	G	5320		WEB             			BOEING	727   	727212      	138407G	NM  										BS 1213	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	727NK					21945				WEB CORRODED AT BS 1213 WL 177 RBL 5.						2	L	7	3 	4F				A3WE    					 
2008013100305	20080131	00305		2008	1	31	RC2R130L         	4	20080123	G	6122	5221220F	PILOT VALVE     		B210800REVJ 	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					GOVERNOR	BROKEN          	B				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			NE	03	401BC		697  		00066	TH1668				PROPELLER WENT TO FEATHER IN FLIGHT AND WAS UNABLE TO UNFEATHER. AFTER RECEIVING THE GOVERNOR FOR INSPECTION IT WAS DISC	OVERED THAT THE BOTTOM END OF THE PILOT VALVE (P/N 5221-220) HAD BROKEN OFF AND WAS MISSING. IT WAS PRESUMED THAT IT EXI	TED THE BOTTOM END OF THE DRIVE GEAR AND ENTERED THE ENGINE SUMP. THE OPERATOR WAS NOTIFIED AND THE MISSING PIECE WAS RE	TRIEVED.			1	L	7	2 	3O	3	O		3A16    	E5CE				 
2008041400040	20080414	00040	NM  	2008	4	14	RI3R200800001    	1	20080331	G	2840	403501	TSU             			BOEING	737   	737*        	       	NM  										INTERNAL	CONTAMINATED    	B			RI3R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SO	15										WHILE PERFORMING TROUBLESHOOTING AND REPAIR OF 4035-01 SERIES TRANSIENT SUPPRESSION UNITS (TSU) IAW COMPONENT MM 28-44-6	4, REV 2, DATED 20/04/2007, IT WAS DISCOVERED THAT VARIOUS UNITS (7 TOTAL) SHOWED EVIDENCE OF CONTAMINATION ON INTERIOR 	SURFACES FROM WHAT APPEARS TO BE MOISTURE INTRUSION THROUGH THE CASE SEALS.  AFFECTED UNITS HAVE BEEN PLACED IN QUARANTI	NE.  IMMEDIATELY NOTIFIED THE ORIGINAL EQUIPMENT MFG AND PRODUCTION AUTHORITY HOLDER, OF THE FINDINGS.  COORDINATING WIT	H  ENGINEERING AND QUALITY REPRESENTATIVES ON FURTHER ACTION AND FINAL DISPOSITION.  AFFECTED UNITS TO REMAIN IN QUARANT	INE UNTIL GUIDANCE IS RECEIVED. CONSULTED WITH FSDO, PMI.  RECOMMENDED ACTION:  SUBMIT SDR IAW 14 CFR PART 145.221 AND R	2	L	7	2 	4F			RT	A16WE   					 
2008041400103	20080414	00103	NM  	2008	4	14	RI3R200800002    	1	20080409	G	2840	403501	TSU             			BOEING	737   	737*        	       	NM  											CONTAMINATED    	B			RI3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15										WHILE PERFORMING PRELIMINARY INSPECTION AND TROUBLESHOOTING OF THE TRANSIENT SUPPRESSION UNIT (TSU) 4035-01, S/N 1308, I	T WAS DISCOVERED THAT THE UNIT SHOWED EVIDENCE OF INTERNAL CONTAMINATION.  THE CONTAMINATION APPEARS TO BE CAUSED BY MOI	STURE INGRESS INTO THE UNIT.  THE UNIT HAS BEEN PLACED IN QUARANTINE, AND PAH/OEM HAS BEEN NOTIFIED OF THE FINDING.				2	L	7	2 	4F			RT	A16WE   					 
2008040400008	20080404	00008	GL  	2008	4	4	SJ3R025859       	3	20080314	G	6110	D495	FORK            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER ASSY	CRACKED         	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05		2185 	1361 					HJ494		CRACK INDICATIONS FOUND DURING MAG PARTICLE INSPECTION.  CRACKS ARE LOCATED ON THE THIN SIDE OF ALL (4) FORK SLOTS RADI.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2008040200035	20080402	00035	NE  	2008	4	2	SJ3R080124001    	3	20080124	G	6110	B6545	CAM FOLLOWER    			BEECH 	1900  	1900D       	1154162	CE  	PWC   	PT6   	PT6A42A     	52043	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROP BLADE	BROKEN          	B			SJ3R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			GL	05								HJ1430		REMOVED DUE TO SUSPECTED INTERNAL HUB COMPONENT FAILURE.  BLADE S/N 4152 WAS FOUND TO ROTATE FREELY +/- 12.5 DEGREE POST	 FIRST GROUND RUN AFTER INSTALLATION.  INSPECTION AFTER DISASSEMBLY REVEALED ONE BROKEN B-6545 PITCH CHANGE KNOB CAM FOL	LOWER. THIS PART WAS INSTALLED NEW AT OVERHAUL AND FAILED ON FIRST GROUND RUN.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	5	C	P10NE	 
2008042300168	20080423	00168	NM  	2008	4	23	SROM2008001      	1	20080406	G	5350	654869089	SUPPORT         			BOEING	737   	737205      	1384456	NM  										LT MLG WW	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	39285				23466				LEFT HAND MAIN LANDING GEAR WHEEL WELL FAIRING SUPPORT GOUGED AT AFT OUTBOARD SIDE. REPAIRED LT MLG WHEEL WELL SUPPORT A	T AFT OUTBOARD SIDE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-476 AND ASI SOLUTIONS DRAWING 5350476-1	, REV IR, DATED MARCH 13, 2008.  REFERENCE NON-ROUTINE CARD 27, DATED 02/27/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300176	20080423	00176	NM  	2008	4	23	SROM2008002      	1	20080406	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4.  BLENDED AND FOUND CORROSION ON AFT GALLEY FLOORBEAM AT STA BS 98	0 RBL 4 TO BE BEYOND LIMITS.  REPAIRED AFT GALLEY FLOORBEAM AT STA BS 980 RBL 4 IN ACCORDANCE WITH BOEING 737 STRUCTURAL	 REPAIR MANUAL (SRM), 51-40-4.  REFERENCE NON-ROUTINE CARD 488, DATED 03/04/08.				2	L	7	2 	4F			RT	A16WE   					 
	20080714		NE  	2008	7	14	SROM20080023     	2	20080523	G	7200	JT8D17A	ENGINE          			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					NR 1	BIRD INGESTION  	C			SROM	E	L			ENGINE SHUTDOWN         	ABORTED APPROACH        			C	J	R	F.O.D.                    	WARNING INDICATION        	PARTIAL RPM/PWR LOSS      	AP	APPROACH       	1			AL	03	736BP	36699	2561 			23465	709500			INGESTED LARGE BIRD ON APPROACH TO AKU, SHUT-DOWN ENGINE AND COMPLETED MISSED APPROACH.  DIVERTED TO SCC AND MADE UNEVEN	TFUL LANDING.  REMOVED AND REPLACED NR 1 ENGINE.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
	20081126			2008	11	26	SROM20080024     	4	20080926	G	2565	D31355440	SLIDE           			BOEING	737   	737205      	1384456	NM  										R2 DOOR	INOPERATIVE     	I			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA					23466				DURING MINI EVACUATION DEMONSTRATION TRAINING SLIDE DEPLOYED BUT DID NOT INFLATE. WAITING ON TEAR DOWN REPORT FOR FINAL 	DISPOSITION.  11/20/08 FINAL DISPOSITION. TEARDOWN REPORT INDICATED NO FINDINGS.					2	L	7	2 	4F			RT	A16WE   					 
2008042300186	20080423	00186	NM  	2008	4	23	SROM2008003      	1	20080406	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CORROSION ON UPPER CAP OF FLOORBEAM AT STA BS 294.5 BETWEEN LBL 12 AND RBL 50.  CORROSION ON UPPER CAP OF FLOORBEAM AT S	TA BS 294.5 BETWEEN LBL 12 AND RBL 50 BLENDED BEYOND LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM)	, 53-10-1.  REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9.  REFERENCE NON-ROUTINE CARD 	494, DATED 03/04/08.			2	L	7	2 	4F			RT	A16WE   					 
2008042300171	20080423	00171	NM  	2008	4	23	SROM2008004      	1	20080406	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CORROSION FOUND ON FLOORBEAM STA BS 1016 BL 5 THRU BL 38 LEFT HAND.  CORROSION ON FLOORBEAM STA BS 1016 BL 5 THRU BL 28 	LEFT REMOVED AND FOUND TO BE BEYOND LIMITS IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-01, FIGUR	E 1.  FLOORBEAM REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-04, FIGURE 1.  REFERENCE NO	N-ROUTINE CARD 19, DATED 03/04/08.			2	L	7	2 	4F			RT	A16WE   					 
2008042300133	20080423	00133	NM  	2008	4	23	SROM2008005      	1	20080406	G	5320		TORQUE BOX      			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CORROSION BETWEEN STA BS 1118 AND STA BS 1138 IN THE RIGHT HAND TORQUE BOX, BY THE APU INLET DUCT. CORROSION BETWEEN STA	 BS 1118 AND STA BS 1138 IN THE RIGHT HAND TORQUE BOX, BY THE APU INLET DUCT REMOVED IN ACCORDANCE WITH BOEING 737 STRUC	TURAL REPAIR MANUAL (SRM), 51-10-06.  ORIGINAL MATERIAL 0.063, AMOUNT OF REMOVED MATERIAL 0.025, OUT OF LIMITS IN ACCORD	ANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-01, PAGE 45, DETAIL V.  FORMED SECTION REPAIR CARRIED OUT IN 	ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-03.		2	L	7	2 	4F			RT	A16WE   					 
2008042300178	20080423	00178	NM  	2008	4	23	SROM2008006      	1	20080406	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CRACK IN FUSELAGE SKIN AT STA BS 760 STR 19L, (NDT CONFIRMED CRACK).  REPAIRED FUSELAGE SKIN AT STA BS 760 STR 19L IN AC	CORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-30-03, FIGURE 48, FASTENERS INSTALLED IN ACCORDANCE WITH SRM	 51-30-02.  REFERENCE NON-ROUTINE CARD 542, DATED 03/04/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300177	20080423	00177	NM  	2008	4	23	SROM2008007      	1	20080406	G	2520	43100001	BAR             		87513       	BOEING	737   	737205      	1384456	NM  										SEAT	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				REPAIR CRACKED SPREADER BARS ON PASSENGER SEATS.  REPAIRED CRACKED SPREADER BARS ON PASSENGER SEATS IN ACCORDANCE WITH C	PAI EO C007-2525-B737-01 AND FAA DER APPROVED 8110-3, 080-1226-08-471 AND ASI DRAWING 2520471-1, REV IR, DATED MARCH 19,	 2008.  REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 160, DATED 02/28/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300188	20080423	00188	NM  	2008	4	23	SROM2008008      	1	20080406	G	5314		KEELBEAM        			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				LOWER CHORDS OF KEEL BEAM IN MAIN LANDING GEAR HAS CORROSION AT LOWER FLANGE IN SEVERAL AREAS UPPER & LOWER SURFACES FRO	M STA BS 663-727 RBL 6.5 & LBL 6.5.  REPAIRED LOWER CHORD OF KEEL BEAM IN MLG WHEEL WELL AT LOWER FLANGE IN ACCORDANCE W	ITH BOEING MESSAGE 1-789220434-4, DATED MARCH 28, 2008.  FASTENERS INSTALLED IN ACCORDANCE WITH BOEING 737 STRUCTURAL RE	PAIR MANUAL (SRM), 51-30-2.  REFERENCE NON-ROUTINE CARD 570, DATED 03/04/08.			2	L	7	2 	4F			RT	A16WE   					 
2008042300172	20080423	00172	NM  	2008	4	23	SROM2008009      	1	20080406	G	5320		FITTING         			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CLIP CRACKED AT STA BS 1006 STR 21L.  REPLACED CLIP AT STA BS 1006 STR 21L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPA	IR MANUAL (SRM), 51-10-01 AND 51-30-02.  REFERENCE NON-ROUTINE CARD 578, DATED 03/04/08.					2	L	7	2 	4F			RT	A16WE   					 
2008042300173	20080423	00173	NM  	2008	4	23	SROM2008010      	1	20080406	G	5320		FITTING         			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				STRINGER TO FRAME CLIP REQUIRES BLENDING AT STA BS 907 STR 25L (REAR CARGO PIT).  INSTALLED NEW CLIP AT STA BS 907 STR 2	5L IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-03.  REFERENCE NON-ROUTINE CARD 586, DATED 03/04/	08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300169	20080423	00169	NM  	2008	4	23	SROM2008011      	1	20080406	G	5340		STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				STRINGER TIE CLIP DAMAGED AT STA BS 500A, STR 25R.  REPLACED STRINGER TIE CLIP AT STA BS 500A STR 25R IN ACCORDANCE WITH	 BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-1, PAGE 9, SECTION 7 AND 51-30-03.  REFERENCE NON-ROUTINE CARD 590, DA	TED 03/04/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300181	20080423	00181	NM  	2008	4	23	SROM2008012      	1	20080406	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				LIGHTNING STRIKE AT STA BS 933 STR 25.5R.  REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-30-	03, FIGURE 23 (PERMANENT REPAIR), SECTION 1, PARAGRAPH 3., (NDT08-0509).  REFERENCE NON-ROUTINE CARD 602, DATED 03/04/08	.				2	L	7	2 	4F			RT	A16WE   					 
2008042300134	20080423	00134	NM  	2008	4	23	SROM2008013      	1	20080406	G	5320		ATTACH FITTING  			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CRACK IN INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L.  REPLACED INTERCOSTAL ATTACH CLIP AT STA BS 360 STR 11L IN ACCOR	DANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-2, FIGURE 1, 51-20-1, FIGURE 7, 51-30-2, 7.D.(6), AND 51-30-	2, FIGURE 7,3,11 AND 12.  REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CARD 647, DATED 03/05/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300170	20080423	00170	NM  	2008	4	23	SROM2008014      	1	20080406	G	5320		ATTACH FITTING  			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CRACK IN INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L.  REPLACED INTERCOSTAL ATTACH CLIP STA BS 294.5 STR 11L IN ACCORDA	NCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-2, FIGURE 1, 51-20-1, FIGURE 7, 51-30-2, 7.D.(6), AND 51-30-2,	 FIGURE 7, 3, 11 AND 12.  REFERENCE NON-ROUTINE CARD 648, DATED 03/05/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300135	20080423	00135	NM  	2008	4	23	SROM2008015      	1	20080406	G	5311		FRAME           			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CRACK ON BODY FRAME INNER CHORD STA BS 616 LEFT HAND AT STUB BEAM LOWER CHORD.  REPAIRED BODY FRAME INNER CHORD STA BS 6	16 LT AT STUB BEAM LOWER CHORD IN ACCORDANCE WITH BOEING SB 737-53A-1254.  REFERENCE KELOWNA FLIGHTCRAFT NON-ROUTINE CAR	D 672, DATED 03/05/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300167	20080423	00167	NM  	2008	4	23	SROM2008016      	1	20080406	G	5514		BUSHING         			BOEING	737   	737205      	1384456	NM  										HORIZ STAB	LOOSE           	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				LOOSE BUSHING ON STABILIZER SCREW JACK LOWER RIGHT HAND MOUNTING STRUCTURE (P/N 6-37464-1).  REPLACED BUSHING ON STABILI	ZER SCREW JACK LOWER RT MOUNTING STRUCTURE IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 078-1236-08-473 AND ASI SOLU	TIONS DRAWING 5340473-1, REV IR, DATED MARCH 14, 2008.  REFERENCE NON-ROUTINE CARD 740, DATED 03/06/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300174	20080423	00174	NM  	2008	4	23	SROM2008017      	1	20080406	G	7830	65MK781031	BRACKET         			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					NR 1 ENGINE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	39277				23466	709507			LEFT HAND ENGINE TAILPIPE CRACKED AT BRACKET MOUNT (3 O'CLOCK POSITION).  REPAIRED LEFT HAND ENGINE TAILPIPE BRACKET MOU	NT (3 O'CLOCK POSITION) IN ACCORDANCE WITH FAA DER APPROVED FORM 8110-3, 073-1236-08-477 AND ASI SOLUTIONS DRAWING 78304	77-1, REV IR, DATED MARCH 18, 2008.  REFERENCE NON-ROUTINE CARD 826, DATED 03/11/08.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2008042300175	20080423	00175	NM  	2008	4	23	SROM2008018      	1	20080406	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT LBL 24.5 STA BS 663.  REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT LBL 2	4.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410.  REFE	RENCE NON-ROUTINE CARD 843, DATED 03/18/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300183	20080423	00183	NM  	2008	4	23	SROM2008019      	1	20080406	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				LOWER LONGITUDINAL FLOORBEAM CHORD CRACKED AT RBL 24.5 STA BS 663.  REPLACED LOWER LONGITUDINAL FLOORBEAM CHORD AT RBL 2	4.5 STA BS 663 IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-01 AND BOEING DRAWING 65-45410.  REFE	RENCE NON-ROUTINE CARD 844, DATED 03/18/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300189	20080423	00189	NM  	2008	4	23	SROM2008020      	1	20080406	G	5315		FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CORROSION ON FLOOR I-BEAM AT STA BS 344 LBL 18 THRU RBL 39.  REPAIRED FLOOR I-BEAM AT STA BS 344 LBL 18 THRU RBL 39 IN A	CCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 53-10-9, FIGURE 5.  REFERENCE NON-ROUTINE CARD 858, DATED 03/2	5/08.				2	L	7	2 	4F			RT	A16WE   					 
2008042300195	20080423	00195	NM  	2008	4	23	SROM2008021      	1	20080406	G	5320		TORQUE BOX      			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				CRACKED APU TORQUE BOX WEB AT STA BS 1115 RBL 2.  HFEC CARRIED OUT IN ACCORDANCE WITH BOEING 737 NDT MANUAL 51-00-00, FI	GURE 23, PART 6 ON A CUT-OUT ON THE APU TORQUE BOX, STA BS 1115.  NO DEFECTS EVIDENT (NDT08-0461).  APU TORQUE BOX WEB A	T STA BS 1115 RBL 2 REPAIRED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-40-01, FIGURE 1 AND INSTAL	LED IN ACCORDANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-30-02, FIGURE 3 AND 11.  REFERENCE NON-ROUTINE CARD	 859, DATED 03/25/08.		2	L	7	2 	4F			RT	A16WE   					 
2008042300184	20080423	00184	NM  	2008	4	23	SROM2008022      	1	20080405	G	5314		KEELBEAM        			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA					23466				LOWER CHORD OF KEEL BEAM IN MLG HAS CORROSION ON VERTICAL AND HORIZONTAL FLANGES IN SEVERAL AREAS FROM STA BS 663-727 LB	L 615.  REPAIRED LOWER CHORD OF KEEL BEAM ON LT SIDE BETWEEN STA BS 663 THRU 727 IN ACCORDANCE WITH FAA DER APPROVED FOR	M 8110-3,  095-1236-08-483 AND ASI SOLUTIONS DRAWING 5310483-1, REV IR, DATED APRIL 4, 2008.  CORROSION BLENDED IN ACCOR	DANCE WITH BOEING 737 STRUCTURAL REPAIR MANUAL (SRM), 51-10-06 AND FAIRED AT A 10:1 RATIO IN ACCORDANCE WITH SRM 51-10-0	6.  ALL PARTS TREATED AND PROTECTED IN ACCORDANCE WITH SRM 51-10-2.  ALL FASTENERS INSTALLED IN ACCORDANCE WITH SRM 51-3	0-2.  REFERENCE NON-ROUTINE CARD 876, DATED 03/31/08.	2	L	7	2 	4F			RT	A16WE   					 
2008041000163	20080410	00163		2008	4	10	STS004           	4	20080402	G	2564	1218FASA6311701	LIFE RAFT       			EMB   	135   	EMB135KL    	3260302	SO  											MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	WL7R		2    							THE CONFIGURATION BETWEEN THE FIRING HEAD BELL HOUSING AND THE LINK VALVE ARE NOT LOCATED PROPERLY.  THE CAUSES THE LENG	TH OF THE FREE LANYARD TO THE LINK VALVE TO BE REDUCED.  THIS MAY CAUSE THE LIFE RAFT TO NOT DEPLOY IN THE SECONDARY MET	HOD FOR INFLATION VERSUS ACTIVATING THE PRIMARY INFLATION METHOD, THE RIPCORD HANDLE.				2	L	7	2 	4F			RT	T00011AT					 
200805141    	20080514	1    	NE  	2008	5	14	SWDG08RD0113     	2	20080508	G	7210	3030988	SEAL            	PWC         		AIRTRC	AT802 	AT802A      	0390308	SW  	PWC   	PT6   	PT6A67AG    	52211	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	RGB	DEFORMED        	D			SWDG	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	11	804DG	738  			PCERD0113	802A0089	PCERD0113			EXCESSIVE OIL LEAKAGE AROUND PROP SHAFT.  FOUND FELT SEAL MISALIGNED AND INTERFERING WITH THE SHAFT SEAL.						1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
200805141    	20080514	1    		2008	5	14	SWDG20085569     	4	20080414	G	6122	311849703	GOVERNOR        			AIRTRC	AT802 	AT802A      	0390308	SW  	PWC   	PT6   	PT6A67AG    	52211	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	PROPELLER	LEAKING         	D			SWDG	A				UNSCHED LANDING         				K	R		FLUID LOSS                	PARTIAL RPM/PWR LOSS      		AG	AGRICULTURE    	1			SW	11	804DG	721  	721  			802A0089	PCERD0113	HBA1298		GOVERNOR HAS EXCESSIVE BETA VALVE OIL LEAKAGE AND ERRATIC TORQUE FLUCTUATION.  PART REMOVED AND SENT TO REPAIR STATION F	OR EVALVUATION.					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2008022500007	20080225	00007	CE  	2008	2	25	TIMR20080001     	1	20080213	G	3233	993880081	ACTUATOR        			BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  					MLG	LEAKING         	B			TIMA	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			NM	07	239AL		4731 			U239				LT MLG DID NOT RETRACT AFTER TAKEOFF.  PILOT FLEW AC TO HOME BASE WITH GEAR DOWN.  INVESTIGATION REVEALED THAT FLUID WAS	 PASSING THE PISTON INTERNALLY.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2008011100307	20080111	00307	EA  	2008	1	11	UE5R010208001    	2	20080102	G	7313	3013635	NOZZLE          			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A28      	 	EA  					ENGINE	SHEARED         	B			UE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	61										WHEN INSTALLING NOZZLE PN 3013635 ONTO NOZZLE ADAPTER ASSEMBLY USING SPECIFIED OHM TORQUE, NOZZLE SHEARED OFF COMPLETELY	 AT BASE OF THREADS.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2008041000258	20080410	00258	CE  	2008	4	10	VIB8368K         	1	20080320	G	3220		BRACE           			BEECH 	100   	B100        	1152919	CE  										NLG	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	97WD	7178 				BE97				DISASSEMBLED NLG DURING SCHEDULED MAINT AND FOUND SIGNIFICANT CORROSION OVER MOST OF THE NOSE LANDING GEAR V BRACE, PN 5	0-820204. WE ALSO FOUND A CRACK OF 0.008 INCH IN THE NOSE BARREL, PN 99-820100-5, WHERE IT LOOKED LIKE IT HAD BEEN REPAI	RED IN THE PAST. WE ALSO FOUND A CRACK OF 0.020 INCH IN THE V BRACE, PN 99-810028-989, OF THE LT LANDING GEAR.				1	L	7	2 	4T				A14CE   					 
	20081126		EA  	2008	11	26	VJ1R20081118001  	1	20081107	G	3810	500120701	WATER HEATER    			CNDAIR	CL600 	CL6002B16   	1900305	EA  										ZONE 900	OVERTEMP        	B			VJ1R	B	A	H		EMER. DESCENT           	UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS		M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			SW	05	CGQWI					5016				ACFT AT CRUISING ALTITUDE WHEN A PASSENGER ADVISED THE CREW THAT THEY COULD ODOR SOMETHING BURNING IN THE CABIN AREA. TH	E CREW DECLARED AN EMERGENCY AND DIVERTED. AFTER LANDING, THE PROBLEM WAS DETERMINED TO BE THE LAVATORY WATER HEATER HAD	 OVER HEATED CAUSING THE HEATER BLANKET TO EMIT SMOKE AND FUMES. THE WATER HEATER SYS WAS DISABLED BY PULLING THE SYS CI	RCUIT BREAKER AND THE ACFT RETURNED TO DEPARTURE. THIS IS THE THIRD SUCH INCIDENT INVOLVING CANADIAN REGISTERED AIRCRAFT	.  THE WATER HEATERS WERE UTILIZED FROM 1981 TO 1997 IAW STC SA4370SW IN APPROX 200 NEW ACFT EXECUTIVE INTERIOR INSTALLA	TIONS. THERE ARE POSSIBLY (2) PER INTERIOR ONE LOCATED BEHIND THE GALLEY AND ONE LOCATED BEHIND THE LAVATORY VANITY. A C	2	L	7	2 	4F			RT	A21EA   					 
2008041400041	20080414	00041		2008	4	14	WL7R040208001    	4	20080402	G	2564		HOUSING         			EMB   	135   	EMB135KL    	3260302	SO  										LIFE RAFT	MISINSTALLED    	B			WL7R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15			2    							THE CONFIGURATION BETWEEN THE FIRING HEAD BELL HSG AND THE LINK VALVE ARE NOT LOCATED PROPERLY.  THIS CAUSES THE LENGTH 	OF THE FREE LANYARD TO THE LINK VALVE TO BE REDUCED.  THIS MAY CAUSE THE LIFE RAFT TO NOT DEPLOY IN THE SECONDARY METHOD	 FOR INFLATION VERSUS ACTIVATING THE PRIMARY INFLATION METHOD, THE RIPCORD HANDLE.				2	L	7	2 	4F			RT	T00011AT					 
2008040400007	20080404	00007	SO  	2008	4	4	WS9R030608001    	2	20080306	G	8530	AEC631397	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	CRACKED         	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07		205  					814500			CRACK BETWEEN 3RD AND 4TH CYLINDER HEAD, COOLING FIN.						1	L	7	1 	3O	3	O		3A15    	E3SO				 
2008040400011	20080404	00011	SO  	2008	4	4	WS9R031108001    	2	20080311	G	8530		CYLINDER HEAD   			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470L       	17026	SO  					ENGINE	CRACKED         	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	001						069693R			VISUAL INSPECTION OF THE CYLINDER AS IT WAS RECEIVED FROM THE MFG, REVEALED CRACKED FINS NEAR THE FUEL INJECTOR NOZZLE.						1	H	7	1 	3O	3	O		5A6     	E273				 
2008040400012	20080404	00012	EA  	2008	4	4	WS9R031908001    	2	20080319	G	8530	AEL14995	RETAINER        			PIPER 	PA28  	PA28*       	       	SO  	LYC   	O360  	O360A4M     	41514	EA  					CYLINDER	BROKEN          	B			WS9R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07							L2841136A			DISCOVERED THAT ALL (4) OF THE PUSH ROD TUBE RETAINERS WERE BROKE UPON REMOVING THE ROCKER BOX COVERS.  THIS ENGINE HAD 	JUST BEEN OVERHAULED AND HAS TEST CELL TIME ONLY.					1	L	7	1 	3O	3	O		2A13    	E286				 
2008040100120	20080401	00120	NM  	2008	4	1	Y5CR200700003    	1	20080122	G	6200	369D25351	SPRAG CLUTCH    			DOUG  	MD500 	MD500E      	3027372	NM  										MAIN ROTOR	BROKEN          	B			Y5CR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05		760  								DURING  A 300HR. INSPECTION ON THE O/R CLUTH THE CUSTOMER FOUND A BROKEN SPRAG CLIP ON THE SPRAG ASSY.						1	G	7	2 	3U			NC	        					 
	20080520		NM  	2008	5	20	Y5CR200700004    	1	20080501	G	6320	369D2512311	BEVEL GEAR      	DOUG        		DOUG  	MD500 	MD500E      	3027372	NM  										M/R TRANSMISSION	BROKEN          	B			Y5CR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05		616  			3668					M/R TRANSMISSION GEAR HAS BROKEN TOOTH.						1	G	7	2 	3U			NC	        					 
2008040300044	20080403	00044	WP  	2008	4	3	YZ4R200800001    	1	20080222	G	2620	3260007	EXTINGUISHER    			DOUG  	DC3   	DC3CR183090C	3021466	WP  	PWA   	PT6   	PT6*        	52043	EA  						INOPERATIVE     	B			YZ4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	39	300BF					26744				FIRE EXTINGUISHER DID NOT ACTIVATE. THE FIRE EXTINGUISHER IS FILLED WITH 4.5 POUNDS OF HALON 1301 AND PRESSURIZED TO 600	 PSIG WITH DRY NITROGEN. THE CONTENTS ARE HELD IN THE CYLINDER BY A PLUG VALVE, PN 13038 WITH AN O-RING SEAL. THIS PLUG 	VALVE IS COMPRESSED BY THE HOUSING ASSY, PN 33370004. THE HOUSING ASSY IS THREADED INTO THE STEM, PN 31840000. THE DISCH	ARGE OUTLET IS BETWEEN THE HOUSING ASSY AND STEM. THE OUTLET ASSY SWIVELS ABOUT THE STEM AND HOUSING ASSY FOR ALIGNMENT 	AT TIME OF INSTALLATION IN AN AIRCRAFT.  WHEN THE FIRE EXTINGUISHER IS FILLED, THE PLUG VALVE AND HOUSING ASSY ARE IN CO	MPRESSION. THE HOUSING ASSY IS MFG WITH VARIOUS MACHINED GROOVES AND IS DESIGNED FOR THE COMPRESSIVE FORCES. WHEN THE CA	2	L	7	2 	4R	3	T		A669    	E2NE				 
2008012200061	20080122	00061	CE  	2008	1	22	ZB0R20080001     	1	20080111	G	2842	S35942	SENSOR          			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL QTY	INTERMITTENT    	B			ZB0R	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			EA	39	272RP	420  	40   			172S8405				RT FUEL QUANTITY INTERMITTENT AT HIGH FUEL LEVELS.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2008012200056	20080122	00056	CE  	2008	1	22	ZB0R20080002     	1	20080111	G	2842	S35942	SENSOR          			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL QTY	INTERMITTENT    	B			ZB0R	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			EA	39	963AC	226  	45   			172S8259				RT FUEL QUANTITY INTERMITTENT AT HIGH FUEL LEVELS.						1	H	7	1 	3O	3	O	NT	3A12    	1E10