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
2002121100032	20021211	00032	CE  	2002	12	11	001              	1	20021209	G	2520	SL0230028	LOCK            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										CABIN CHAIR	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	833QS	2182 	2182 			258433				CABIN CHAIR WILL FALL BACK WITHOUT USE OF RECLINE BUTTON ACTIVATION.  EXCESSIVE SLACK.						2	L	7	2 	4F			RT	A3EU    					 
2002031200157	20020312	00157	SO  	2002	3	12	0202             	1	20020211	G	5610		WINDSHIELD      			GULSTM	G1159 	GIV         	3980115	SO  										COCKPIT	CRACKED         	H				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			SW	99	VP-BH					1017				RIGHT FRONT WINDSHIELD OUTER HEATING/PROTECTIVE PLY CRACKED.						2	L	7	2 	4F			RT	A12EA   					 
2002020100007	20020201	00007	CE  	2002	2	1	020231           	1	20020130	G	3230	7089850810295	TORQUE LINK     			BEECH 	90    	65A901      	1152901	CE  										ZONE 700	MISMANUFACTURED 	B			EVGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	33	65JA					LM34				WE WERE REPLACING THE TORQUE LINKS ON OUR KING AIR 65A90 IN ORDER TO RELIEVE THE REPETITIVE INSPECTION REQUIREMENTS OF A	D 2001-01-10.  ONE OF THE TWO TORQUE LINKS SENT WAS FINE.  THE OTHER APPEARED AT FIRST GLIMPSE TO BE NORMAL.  AFTER INST	ALLATION, A RETRACTION TEST WAS PERFORMED AND THE FAULTY TORQUE LINK ALLOWED THE GEAR FORK TO OVEREXTEND AND CAUSED SUPE	RFICIAL DAMAGE TO THE WHEEL WELL.  UPON CLOSER EXAMINATION IT WAS DISCOVERED THAT THE ANGLE OF THE STOP BOSS WAS TOO SHA	LLOW, ALLOWING THE OVEREXTENSION OF THE FORK.		1	L	7	2 	3T			 	3A20    					 
2002050600055	20020506	00055	CE  	2002	5	6	020502           	1	20020502	G	1430		RIVET           			HELIO 	H295  	H295        	4300802	CE  										ZONE 100	WRONG PART      	B			EVGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	33						1257				DURING ANNUAL INSPECTION IT WAS DISCOVERED THAT A NUMBER OF INDUSTRIAL GRADE POP RIVETS WERE USED IN THE COURSE OF AIRFR	AME REPAIR INSTEAD OF AIRCRAFT GRADE RIVETS. INDUSTRIAL GRADE RIVETS WERE REMOVED AND REPLACED WITH PROPER AIRCRAFT QUAL	ITY RIVETS.				1	H	7	1 	3O			 	1A8     					 
2002073000007	20020730	00007	CE  	2002	7	30	0207008          	1	20020729	G	2800	051600918	RESERVOIR       			CESSNA	172   	172R        	2072401	CE  										FUEL SYSTEM	RUPTURED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	03	5172J	313  	313  			17281095				UPON ROUTINE INSPECTION, IT WAS NOTED THAT A FUEL STAIN WAS EVIDENT ON THE UNDERBELLY OF THE AIRCRAFT IN THE FACINITY OF	 THE FUEL SELEVTOR VALVE. CABIN FLOORING AND UPHOLSTERY WAS REMOVED AND THE FUEL SELECTOR AND FUEL RESEVOIR PN 0516009-1	8 WAS REMOVED & INSPECTED. THE RESEVOIR WAS PURGED AND PRESSURE TESTED. THE TANK WAS THEN COVERED IN A SOAPY WATER SOLUT	ION AND A LEAK WAS NOTED COMING FROM A WELDED SEAM. IT IS BELIEVED THAT A MINIMUM .75 INCH CRACK WAS EVIDENT IN A PART W	ITH ONLY 300 HOURS.		1	H	7	1 	3O			NT	3A12    					 
2002020500042	20020205	00042	SW  	2002	2	5	0216             	1	20020204	G	3230	940024005	PINION GEAR     			MOONEY	M20   	M20E        	5870212	SW  										MLG	FAILED          	B				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			WP	27	2103W	4917 	90   			952				DURING ANNUAL INSPECTION AND AD73-21-01 COMPLIANCE, FOUND END THREE THREADS BROKEN OFF, ACTUATOR BLOCK UNABLE TO RETRACK	 LANDING GEAR.  THREADS WHERE CORRORDED AND SEPERATED FROM GEAR.  TIME SINCE LAST ANNUAL INSPECTION - 90 HOURS. PART NOT	 REPAIRABLE.  REPLACED AND RETURNED TO SERVICE.  AGE 25 YRS.				1	L	7	1 	3O			 	2A3     					 
2002031200003	20020312	00003	GL  	2002	3	12	0242             	3	20020220	G	6114		WIRE            			MOONEY	M20   	M20E        	5870212	SW  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP HUB	WRONG PART      	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	27	5554Q	1450 	170  			630				DURING ANNUAL INSPECTION,  FOUND PROPELLER HUB SAFETY WIRE UNDER SIZE - .032. AIRCRAFT PARTS MANUAL CALLS FOR SIZE - .04	1 SAFETY.  INSTALLED PROPER WIRE AND RETURNED TO SERVICE.  SIX PRIOR INCIDENTS IN LAST THREE MONTHS.  AC 43.13-1B DOES N	OT SPECIFY ANYTHING.				1	L	7	1 	3O			 	2A3     		5	C	P920	 
2002091000112	20020910	00112	CE  	2002	9	10	025686FLTLOG     	1	20020716	G	2840		CONTROL PANEL   			BEECH 	90    	C90         	1152913	CE  										FUEL PANEL	DAMAGED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	15	21					LJ902				BATTERY CHARGE LIGHT CAME ON IN FLT, LT BOOST PUMP & LT TRANSFER PUMP CIRCUIT BREAKER POPPED : RESET CIRCUIT BREAKER & L	ANDED ASAP.  UPON INSPECTION FOUND FUEL PANEL DIODES AND WIRING CORRODED.  R&R DIODES, CIRCUIT BREAKER AND HARDWARE AND 	CLEANED CORROSION FROM WIRING AND PANEL AND REINSTALLED PANEL.				1	L	7	2 	3T			 	3A20    					 
2002041900003	20020419	00003	CE  	2002	4	19	029041702        	1	20020417	G	2910	306588002087	LINE            			RKWELL	NA265 	NA26565     	7630107	CE  	ALIDSG	TFE731	TFE7313AR   	 	WP  					HYD SYSTEM	CRACKED         	B				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CE	01	6NR	9564 				46529				PILOTS STARTED TAXI OUT TO TAKEOFF.  IN PROCESS CONDUCTED THE LANDING  SPOILER EXTENSION OPERATIONAL TEST WHICH SURGES A	ND SLAMS THE HYDRAULIC SYSTEM FAIRLY HARD.  WITHIN A FEW SECONDS RECEIVED MASTER WARNING CAUTION LIGHT AND NOTICED LOW H	YDRAULIC PRESSURE.  RETURNED TO HANGAR.  INSPECTION REVEALED .75 INCH LONG STRESS CRACK IN UPPER FORWARD RADIUS OF ALUMI	NUM HYDRAULIC LINE THAT WAS UNDETECTABLE TO THE EYE UNTIL UNLESS HYD PUMP WAS ON.  PROBABLE CAUSE IS MOST LIKELY WORK HA	RDENING AND STRESS DUE TO SURGES AND HYDRAULIC SYSTEM SLAM EXPERIENCED WITH SUDDEN SPOILER BOARD EXTENSION ON LANDINGS.		2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2002042300055	20020423	00055	EA  	2002	4	23	04230201         	2	20020423	G	8500	SL738190	BUSHING         								LYC   	O720  	IO720*      	41546	EA  					COUNTER WEIGHT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		250  	250  							COUNTER WEIGHT BUSHINGS P/N SL73810 HAVE FAILED AT 2 TO 250 HOURS. IT APPEARS THAT THE MATERIAL MAY BE TOO SOFT.  BUSHIN	GS WERE REMOVED BY OPERATOR AND SENT BACK FOR EVALUATION.										3	O			1E15				 
2002071900078	20020719	00078	CE  	2002	7	19	0605023221       	1	20020507	G	2450	S13605L	CIRCUIT BREAKER 			CESSNA	172   	172R        	2072401	CE  										ELECTRICAL	FAILED          	D			S1XB	A				UNSCHED LANDING         				A			FLAME/FIRE                			CL	CLIMB          	1			SO	17	972RA					17280412				THE OVERVOLTAGE SENSOR ACTIVATED, CLAMPING THE ACU POWER SUPPLY TO GROUND.  THE ALTERNATOR CIRCUIT BREAKER FAILED TO TRI	P.  THIS RESULTED IN AN INFLIGHT ELECTRICAL FIRE WITH THE HARNESS BETWEEN THE J-BOX AND CIRCUIT BREAKER PANEL DAMAGED AS	 MULTIPLE CIRCUITS WERE BURNED.  AT LEAST THREE OTHER BREAKERS TRIPPED BEFORE THE MAIN BUSS BREAKER LET GO.  THE FIRST W	IRE BURNING STARTED A CASCADE OF SHORT CIRCUITS.			1	H	7	1 	3O			NT	3A12    					 
2002071900080	20020719	00080	CE  	2002	7	19	0628022541       	1	20020628	G	3340	S13605L	CIRCUIT BREAKER 			CESSNA	172   	172S        	2072439	CE  										NAV LIGHTS	FAILED          	D			S1XB	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SO	17	484SP					172S8030				THE RIGHT WING NAV LIGHT POSITIVE AND NEGATIVE WIRES BURNED TOGETHER, SHORTING THE NAV CIRCUIT.  THE 5 AMP NAV LIGHT CIR	CUIT BREAKER NEVER TRIPPED.  AN INVESTIGATION WAS INITIATED WHEN A PILOT REPORTED THAT THE NAV LIGHT SWITCH WOULD NOT ST	AY IN THE "ON" POSITION.				1	H	7	1 	3O			NT	3A12    					 
2002102300061	20021023	00061	CE  	2002	10	23	081620027947Q    	1	20020816	G	5220	52111302	ESCAPE HATCH    			CESSNA	402   	402B        	207590P	CE  										FUSELAGE	SEPARATED       	E			QTVA	O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	11	7947Q	12782				402B0397				BETWEEN SLC & TWF PILOT REPORTED A LOUD BOOMING/STRIKING NOISE, AS IF HE HAD HIT A BIRD. UPON INVESTIGATION HE NOTICED T	HE ESCAPE HATCH WAS MISSING. HE NOTIFIED SALT LAKE CENTER OF THE SITUATION. NO OTHER DAMAGE WAS NOTICED. THE PILOT SLOWE	D THE AIRCRAFT AND CONTINUED SAFELY TO TWF.				1	L	7	2 	3O			 	A7CE    					 
2002082600006	20020826	00006	SO  	2002	8	26	1001             	1	20020627	G	5711		SPAR            			LKHEED	282   	C130A       	5262502	SO  										LT WING	CRACKED         	B			BZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	131HP	20230				56534				FORWARD WING SPAR WEB WAS CRACKED IN THE SAME LOCATION BOTH SIDES STA. 85 CENTER WING.  3 DIFFERENT LOWER WING STRINGER 	ATTACH ANGLES CRACKED IN THE SAME FASHION CWS 216 LT SIDE.  LOWER WING STRINGER CRACKED CWS 216 LEFT.  LEFT WING LOWER S	KIN CRACKED CWS 218.				2	H	7	4 	4T			 	A31NM   					 
2003010600007	20030106	00007	WP  	2003	1	6	10090226         	2	20021009	G	7320	8961151	GASKET          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	LEAKING         	E			HKGA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	17	323BA	24361	24361			TC280	P54282			P3 AIRLEAK AT PRIMARY BLEED PORT CAUSED ENGINE FIRE INDICATION. NO FIRE WAS DISCOVERED						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2002081200126	20020812	00126	SO  	2002	8	12	10991            	1	20020722	G	7100	554321	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					NACELLE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	4174D	303  				3449178				CABLE STIFF, THIS CABLE RUNS THROUGH THE FIRE WALL AND WITHIN THE TURBO REGION.  HEAT GENERATED FROM TURBO ASSEMBLY AFFE	CTS INSIDE LINNING.  RECOMMEND A FIRE JACKET OR ALTERNATE MEANS TO SHIELD CABLE ASSEMBLY FROM HEAT.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002081200127	20020812	00127	CE  	2002	8	12	11482            	1	20020731	G	3246	D30259	WHEEL           			CESSNA	210   	T210L       	2073449	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	94148	1899 	140  			21060519				ON PRECAUTIONARY INSPECTION FOUND CRACKS AT WHEEL/HUB FLANGE MOUNTING BOLT HOLES ON BOTH WHEELS. REPLACED BOTH WHEELS WI	TH CLEVELAND TWO PIECE WHEELS. WE HAVE FOUND 6 OF THE SAME WHEEL(HUBS)CRACKED ON 172/182/210 CESSNA AIRCRAFT IN THE LAST	 WEEK. RECOMMEND IMMEDIATE INSPECTION AND OR REMOVAL OF THESE WHEELS FROM SERVICE.				1	H	7	1 	3O			 	3A21    					 
2002081200128	20020812	00128	CE  	2002	8	12	11509            	1	20020731	G	3246	D30259	WHEEL           			CESSNA	182   	182P        	2075816	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	9448M	3198 	154  			18264764				ON REPLACING A WARN OUT TIRE WE FOUND THE CENTER HUB TO HAVE A CRACK AT 9 OF THE FLANGE MOUNTING BOLT HOLES, WE INSPECTE	D THE OTHER WHEEL/HUB FOUND IT TO HAVE 4 CRACKS. REPLACED BOTH WHEELS WITH CLEVELAND TWO PIECE WHEELS. WE HAVE FOUND 6 O	F THE SAME WHEELS (HUBS)CRACKED ON 172/182/210 CESSNA AIRCRAFT IN THE LAST WEEK.				1	H	7	1 	3O			NT	TA13    					 
2002081200129	20020812	00129	CE  	2002	8	12	11510            	1	20020731	G	3246	D30256	WHEEL           			CESSNA	172   	172M        	2072418	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	9682H	2725 	100  			17266311				ON INSPECTION OF CENTER HUBS OF THE TWO MAIN WHEELS FOUND ONE HUB TO HAVE 12 CRACKS ONE AT EA. BOLT HOLE. THE OTHER HUB 	HAD SIMILAR CRACKING. THESE WHEELS WERE INSPECTED 100 HRS PRIOR WHEN NEW TIRES WERE INSTALLED AND ON CRACKS WERE NOTED. 	THESE WHEELS/TIRES WERE REMOVED FOR INSPECTION DUE TO THE FACT WE HAVE FOUND 6 OF THE SAME WHEELS (HUBS)CRACKED ON 172/1	82/210 CESSNA AIRCRAFT IN THE LAST WEEK.			1	H	7	1 	3O			NT	3A12    					 
2002082600007	20020826	00007	CE  	2002	8	26	11518            	1	20020819	G	3246	D30321	HUB             			CESSNA	310   	T310R       	2074246	CE  										NGL WHEEL	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	500CH	4390 	350  			310R0734				WHEEL REPLACED DUE TO THE FACT WE HAVE FOUND MANY HUBS CRACKED ON THREE PIECE MCCAULEY WHEELS. WE FOUND THE CRACKS AFTER	 THE WHEEL WAS REMOVED AND COMPLETELY TAKEN APART. RECOMMEND ALL THREE PIECE MCCAULEY WHEELS BE COMPLETELY DISASSEMBLED 	FOR INSPECTION IMMEDIATELY, AND EACH ANNUAL THERE AFTER OR UNTIL THEY ARE REPLACED WITH A BETTER WHEEL. (IE: TIRE MUST B	E REMOVED FROM WHEEL.)WE RECOMMEND CLEVELAND WHEELS AS THEY ARE TWO PIECE WHEELS.			1	L	7	2 	3O			 	3A10    					 
2002121100033	20021211	00033	CE  	2002	12	11	11592            	1	20021202	G	3246	D30259	HUB             			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					MLG WHEEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	35182	1455 	77   			177RG1045				CENTER SECTION OF WHEEL FOUND CRACKED BOTH MAIN WHEELS. WHEELS REPLACE WITH NEW CLEVELAND TWO PIECE TYPE WHEELS.						1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2003010600010	20030106	00010	CE  	2003	1	6	123002           	1	20021230	G	5210	504300431329	CHANNEL         			BEECH 	200   	200BEECH    	1152920	CE  										CABIN DOOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	6509F	8276 				BB493				WHILE GROUND PRESSURIZING CABIN FOR LEAK CHECK, THE CABIN DOOR WOULD LEAK AT 3 PSI AND APPEARED TO SHIFT WITHIN THE FRAM	E AS PRESSURE WAS APPLIED.ADJUSTMENTS TO THE LATCHING MECHANISM ALLOWED THE DOOR TO HOLD TILL 5.2 PSI (6 PSI WAS THE TES	T TARGET) BUT IT WAS NOTED THAT THE DOOR WAS STILL SHIFTING AFT AT THE UPPER PORTION UNDER PRESSURE.THE DOOR HINGE AFT S	ECTION HAD EXCESSIVE PLAY. THE DOOR WAS REMOVED AND A CLOSER INSPECTION REVEALED THAT THE DOOR END CHANNEL WAS CRACKED F	OR 6 INCHES SPANNING THE AFT 6 RIVETS WHICH ATTACH THE DOOR HINGE TO THE DOOR. REPLACED THE CHANNEL AND HINGE HALF PIECE	S AND ADJUSTED DOOR LATCHING MECHANISM AS REQUIRED.	1	L	7	2 	4T			 	A24CE   					 
2002092700018	20020927	00018	SO  	2002	9	27	16138C           	1	20020918	G	5730		SKIN            			LKHEED	282   	C130A       	5262502	SO  										CENTER WING	CRACKED         	B			BZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	133HP					570482				LOWER CENTER WING SKIN CRACKED AT FASTINER HOLES.						2	H	7	4 	4T			 	A31NM   					 
2002102300062	20021023	00062	NM  	2002	10	23	16214            	1	20021016	G	5710		STRUCTURE       			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R335042     	 	EA  					LT & RT WING	CRACKED         	B			BZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	139HP					145906				IN THE WHEEL WELL AREA OF THE P2V-7 THERE ARE 2 FUEL CELL INTERCONNECT ACCESS PANELS.  THE FURTHEST INBOARD PANELS ON EA	CH SIDE ARE PANEL 53L AND 53R.  PANEL 53L, THERE IS A CRACK LOCATED AT THE INBOARD FORWARD CORNER, RUNNING FROM THE RADI	US OF THE DOUBLER CUTOUT FORWARD .3125 INCH TO ONE OF THE DOUBLER ATTACH FASTENERS.  IN PANEL 53R, THERE IS A CRACK LOCA	TED AT THE INBOARD FORWARD CORNER, RUNNING FROM THE RADIUS OF THE DOUBLER CUTOUT FORWARD COMPLETELY THROUGH THE DOUBLER.	  THERE IS NO DAMAGE FOUND IN THE WING SKIN OR THE HAT SECTION FLANGES.  (SW)		2	M	7	2 	2R	4	R	RT	A1RM    	 				 
2003010600006	20030106	00006	CE  	2003	1	6	1B               	1	20021220	G	3252	07436242	SHIMMY DAMPENER 			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	NLG	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	6506R					U2060969	818948R	731126		SHIMMY DAMPENER SLIDING SHAFT INSTALLED 180 DEGREES OUT.  UNIT WAS OVERHAULED.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002062500118	20020625	00118	SO  	2002	6	25	200202           	1	20020606	G	2400	RSU21	RELAY           			PIPER 	PA46  	PA46310P    	7104605	SO  										ELECTRICAL	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	221TB					468508061				DURING AVIONICS TROUBLE SHOOTING, AN INSPECTION PANEL WAS REMOVED FROM THE COCKPIT FLOOR IN THE AREA JUST FORWARD OF THE	 CO PILOT'S SEAT TO GAIN ACCESS TO A SWITCHING RELAY MOUNTED ON THE UNDERSIDE OF THAT SAME PANEL. ONCE REMOVED, IT WAS N	OTED THAT THE "SWITCHING RELAY" BOX WAS DISPLACING THE OUTER SHEATHING OF THE ENGINE FUEL MIXTURE CABLE UP AGAINST A HYD	RAULIC "B" NUT AND WAS IN THE INTIAL STAGES OF CHAFFING ACTIVITY. SPACE IN THIS AREA IS LIMITED AND THE SWITCHING RELAY 	WAS MOUNTED TO STAND OFF ANGLES ATTACHED TO A LIGHT GAUGE ACCESS PANEL.   REPLACEMENT OF THE SWITCHING RELAY INCLUDED TH	E MANUFACTURE OF A NEW PANEL OF HEAVIER GAUGE THAT NO LONGER REQUIRED "STIFFNERS" AND RESULTED IN ADEQUATE CLEARANCE IN 	1	L	7	1 	3O			RT	A25SO   					 
2002062500119	20020625	00119	CE  	2002	6	25	2002F00637       	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195         	2073102	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	3040B					7923				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND 	CRACKS THE BOSS.  REMOVE BRACKETS FROM AIRCRAFT AND BEAD BLAST BODY WHILE PROTECTING BEARING.					1	H	7	1 	3R			NC	A790    					 
2002082700002	20020827	00002	SO  	2002	8	27	2002F00780       	1	20020628	G	5620	4AS3134031004	PANEL           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	PWA   	306   	PW306B      	 	NE  					FUSELAGE	INCORRECT       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	362GA	24   				062				WHILE ROUGH FITTING THE RIGHT WINDOW PANEL,  IT WAS NOTED THE THE NR 4 WINDOW  (FS 7558) WAS 0.75 INCH TOO FAR FORWARD. 	 A CHECK OF AIRCRAFT REVEALED THE SAME CONDITION ON THE LT SIDE OF AIRCRAFT S/N 63 AND 67. (F.S. 7558) PART NUMBER: 4AS3	134031-003.  SUBSEQUENT TO OUR INVESTIGATION AND ASSEMBLY LINE CHECK (S/N 68 - 80) REVEALED THE SAME CONDITION ON RT SID	E OF SN 68.			2	L	7	2 	4F	4	F	RT	A12EA   	E35NE				 
2002112700033	20021127	00033	SO  	2002	11	27	2002F01028       	1	20021101	G	2823		SHUTOFF VALVE   			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL SYSTEM	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	56418					28R7335434				FUEL SHUTOFF VALVE UNIVERSAL FAILED WHILE TURNING OFF FUEL.  THIS PART IS NO LONGER USED ON NEWER AC AND PART NUMBER NOT	 LISTED IN THE PARTS BOOK.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002012800002	20020128	00002	CE  	2002	1	28	2002FA0000039    	1	20020102	G	3230	22411027	PIVOT ASSY      			CESSNA	182   	R182        	2072734	CE  										LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	757KP					R18201242				FORWARD BEARING AREA OF RIGHT MAIN GEAR PIVOT WAS DETERMINED TO BE CRACKED AND LEAKING BRAKE FLUID.  THE PIVOT ASSY WILL	 BE REPLACED WITH A NEW PIVOT ASSY PART NUMBER 2241102-13 AS OUTLINED IN MFG SB.					1	H	7	1 	3O			RT	3A13    					 
2002012800008	20020128	00008	CE  	2002	1	28	2002FA0000047    	1	20020104	G	3233	S1997C78	BEARING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					ACTUATOR	DAMAGED         	B			X0FR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6091V	3067 				172RG0574				FOUND ACTUATOR PISTON 1 RACK SUPPORT BEARING MIGRATED APPROX.  .2500 INCH FROM HOUSING.  BEARING WAS FOUND UNSERVICEABLE	.  CAUSE UNKNOWN.					1	H	7	1 	3O	3	O	 	3A17    	E286				 
2002012800013	20020128	00013	EA  	2002	1	28	2002FA0000054    	2	20020114	G	8530	32000WLA1	CYLINDER        			BBAVIA	7     	7AC         	2110102	SW  	LYC   	O320  	IO320C1A    	41508	EA  					ENGINE	CUT             	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	85664					7AC4409	371355A			ENGINE WAS INSTALLED ON THE AIRCRAFT AND RUN UP.   AN OIL LEAK WAS NOTICED IN THE LOWER SPARK PLUG BOSS AREA OF NR 1 CYL	INDER.  FURTHER EXAMINATION REVEALED THAT SOME CUTS BETWEEN FINS ADJACENT TO THE SPARK PLUG HOLE NEARLY PENETRATED THE T	HREAD AREA OF THE SPARK PLUG HOLE.  CYLINDER NR 2 HAD A SIMILAR PROBLEM BUT THE CUTS ONLY PENETRATED HALFWAY THROUGH THE	 BOSS SURFACE.			1	H	7	1 	3O	3	O	 	A759    	1E12				 
2002012800014	20020128	00014	EA  	2002	1	28	2002FA0000055    	2	20020114	G	8530	32000WLA1	CYLINDER        			BBAVIA	7     	7AC         	2110102	SW  	LYC   	O320  	IO320C1A    	41508	EA  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	85664					7AC4409	371355A			ENGINE WAS INSTALLED ON THE AIRCRAFT AND RUN UP.  AN OIL LEAK WAS NOTICED IN THE LOWER SPARK PLUG BOSS AREA OF NR 1 CYLI	NDER.  FURTHER EXAMINATION REVEALED THAT SOME CUTS BETWEEN FINS ADJACENT TO THE SPARK PLUG HOLE NEARLY PENETRATED THE TH	READ AREA OF THE SPARK PLUG HOLE.  CYLINDER NR 2 HAD A SIMILAR PROBLEM BUT THE CUTS ONLY PENETRATED HALFWAY THROUGH THE 	BOSS SURFACE.			1	H	7	1 	3O	3	O	 	A759    	1E12				 
2002011800029	20020118	00029	WP  	2002	1	18	2002FA0000077    	1	20020114	G	2913	D5001	PUMP            			ROBSIN	R44   	R44         	7640120	WP  										HYD SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	144JD	261  	261  			0938				HYDRAULIC PUMP LEAKING BETWEEN THE MATING SURFACES OF THE PUMP.  						1	G	7	1 	3O			 	H11NM   					 
2002012800020	20020128	00020	WP  	2002	1	28	2002FA0000084    	1	20020108	G	7922	53E22144	VERNATHERM      			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					OIL COOLER	STUCK           	D				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			NE	05	49CN	338  				0554	L2533240A			OPERATOR COMPLAINT, HIGH OIL TEMPERATURES, 245 DEGREES F.   VERIFIED BY A DECREASE IN OIL PRESSURE.  FOUND VALVE DEFECTI	VE.  REMOVED AND REPLACED VALVE WITH NEW PART.  OPS CHECKED GOOD.					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002012800021	20020128	00021	EA  	2002	1	28	2002FA0000086    	2	20020114	G	8530	72877	LIFTER          			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					ENGINE	BROKEN          	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	4351D	1254 				288411016	L2373740A			DURING OIL CHANGE FOUND METAL IN OIL FILTER.  REMOVED SUCTION SCREEN FOUND .5000 INCH DIAMETER PIECES OF METAL.  DISASSE	MBLED ENGINE AND FOUND LIFTER FACES BROKEN OFF 3 LIFTERS.					1	L	7	1 	3O	3	O	 	2A13    	E295				 
2002012800026	20020128	00026	CE  	2002	1	28	2002FA0000090    	1	20020102	G	3222		STRUT           			CESSNA	310   	310F        	2074216	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG	STUCK           	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03	6721X	3167 				3100021				THE NOSE STRUT APPEARS TO HAVE GONE FLAT DURING TAXI FOR TAKE OFF.  DURING THE GEAR RETRACTION CYCLE THE NOSE STRUT, NOT	 FULLY EXTENDED, HUNG UP ON THE CENTER ATTACH ARMS OF THE NOSE GEAR DOORS PULLING THE IDLER BELLCRANK (PN 0842102-2) APA	RT.				1	L	7	2 	3O	3	O	 	3A10    	E1CE				 
2002012800035	20020128	00035		2002	1	28	2002FA0000093    	4	20020110	G	2561	KD9P0101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED.																			 
2002012400031	20020124	00031	CE  	2002	1	24	2002FA0000094    	1	20020123	G	7500	85300	CHECK VALVE     			CESSNA	501   	501         	2076603	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RT ENGINE	FAILED          	B				O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			SW	43	501GS	5690 				5010012	6009			CHECK VALVE FAILED AND ALLOWED THE RT ENGINE BLEED AIR TO FLOW UNABATED FROM RT ENGINE ACROSS AND INTO THE LT ENGINE VIA	 THE AIRCRAFT BLEED AIR LINES DURING IN FLIGHT RESTARTS OF THE LT ENGINE. HOT BLEED AIR GASES DISTURBED THE NORMAL AIRFL	OW INTO THE LT ENGINE COMBUSTION CHAMBER AND CAUSED THE LH ENGINE TO HAVE A RAPID ITT RISE RESULTING IN AN ENGINE HOT ST	ART AND RESULTANT TEARDOWN/OVERHAUL OF THE ENGINE.			1	L	7	2 	4F	4	F	 	A27CE   	E3GL				 
2002012800039	20020128	00039	CE  	2002	1	28	2002FA0000097    	1	20020114	G	3230	24411001	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					RT MAIN GEAR	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	9602B					172RG0912				FOUND PIVOT ASSEMBLY SPINE AREA FAILED, NO WARNING, NO INDICATION OF SPONGY BREAKS, NO SQUAWKS OF HUG GEAR, OR ANY OTHER	 GEAR PROBLEMS.  PERFORMED 3 GEAR SWINGS, AND ONE EMERGENCY GEAR SWING PRIOR TO INCIDENT.  GEAR HAD FUNCTION 100 PERCENT	, AND WITH IN SERVICE MANUAL RECOMMENDED TIME FRAMES.  PERFORMED GEAR SWING AFTER INCIDENT, FOUND PIVOT ASSEMBLY SHEARED	.  REMAINING LEFT, AND NOSE GEAR FUNCTIONING NORMAL.  AD WAS PERFOREMD 103.4 HOURS PRIOR, NO GEAR PROBLEMS NOTED.			1	H	7	1 	3O	3	O	 	3A17    	E286				 
2002012800040	20020128	00040	CE  	2002	1	28	2002FA0000098    	1	20020114	G	3230	35815129	LEG ASSY        			BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520*      	17032	SO  					RT MAIN GEAR	FROZEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	17814	5942 				D10144				FOUND LEG ASSEMBLY FAULITY.  A FALSE INDICATION OF A LOCK OUT MAY BE INDICATED DUE TO A PARTALY FROZEN/BUSHING AND BOLT.	  EVEN THOUGH THE SERK FITTING RECIEVED GREASE, AND EXPELLED IT FROM THE SIDES OF THE BUSHING.  THE FULL EXTENTION OF TH	E DOWN LOCK WAS COMPROMISED, CORRECT SPRING PRESSURES WERE INDICATED DURING RIGGING, AND 3 GREEN LIGHT INDICATED, BUT TH	E LEG ASSEMBLY WOULD BIND, CAUSING THE UP LOCK TO DISENGAGE AT THE FIRST INDICATION OF SIDE LOAD (CROSS WIND LANDING).			1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002012800042	20020128	00042	CE  	2002	1	28	2002FA0000099    	1	20020102	G	2720		BELLCRANK       			CESSNA	150   	A150K       	2071824	CE  	CONT  	O200  	O200*       	17020	SO  					RUDDER	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	8458M	3500 				A15000158				RIGHT RUDDER NOISE, INSPECTED AND FUND RUDDER BELLCRANK LOOSE.  RIGHT SIDE, THE RIVETS ON THE RIGHT SIDE WORKING, ALLOWI	NG THE BELLCRNK TO MOVE UP AND DOWN, THAT COULD CATCH BELLCRANK STOP AND RUDDER STOP AND JAM.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002012400064	20020124	00064	WP  	2002	1	24	2002FA0000114    	2	20020107	G	7250	31033021	DEFLECTOR       	ALIDSG      							GARRTT	TPE331	TPE33112UA  	01514	WP  					TURBINE NOZZLE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03					980134516516					P/N 3103302-1 DEFLECTOR COMPONENT OF P/N 3103783-9 SECOND STAGE TURBINE NOZZLE ASSEMBLY EXHIBITS WEAR AND MISSING MATERI	AL.  DAMAGE APPEARS THE RESULT OF INADEQUATE RETENTION AND SPINNING OF THE DEFLECTOR IN SERVICE. DAMAGE NOTED AT RECEIVI	NG INSPECTION BY REPAIR STATION PRIOR TO REPAIR. REPAIR DEVELOPED AND DER-APPROVED TO CORRECT CONDITION IN REPAIRED ASSE	MBLIES, HOWEVER DESIGN SHOULD BE REVIEWED AS DISLODGED MATERIAL HAS POTENTIAL TO CONTACT TURBINE ROTOR.								4	T			E4WE				 
2002012400065	20020124	00065	WP  	2002	1	24	2002FA0000115    	2	20020107	G	7250	31033021	DEFLECTOR       	ALIDSG      							ALIDSG	TPE331	TPE331201A  	0517	WP  					TURBINE NOZZLE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03					980134516516					P/N 3103302-1 DEFLECTOR COMPONENT OF P/N 3103783-9 SECOND STAGE TURBINE NOZZLE ASSEMBLY EXHIBITS WEAR AND MISSING MATERI	AL.  DAMAGE APPEARS THE RESULT OF INADEQUATE RETENTION AND SPINNING OF THE DEFLECTOR IN SERVICE. DAMAGE NOTED AT RECEIVI	NG INSPECTION BY REPAIR STATION PRIOR TO REPAIR. REPAIR DEVELOPED AND DER-APPROVED TO CORRECT CONDITION IN REPAIRED ASSE	MBLIES, HOWEVER DESIGN SHOULD BE REVIEWED AS DISLODGED MATERIAL HAS POTENTIAL TO CONTACT TURBINE ROTOR.								3	T			AEXJ STC				 
2002012400066	20020124	00066	WP  	2002	1	24	2002FA0000116    	2	20020107	G	7250	31033021	DEFLECTOR       	ALIDSG      							ALIDSG	TPE331	TPE331201A  	0517	WP  					TURBINE NOZZLE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03					4013451412					P/N 310330201 DEFLECTOR COMPONENT OF P/N 3103783-9 SECOND STAGE TURBINE NOZZLE ASSEMBLY EXHIBITS WEAR AND MISSING MATERI	AL. DAMAGE APPEARS THE RESULT OF INADEQUATE RETENTION AND SPINNING OF THE DEFLECTOR IN SERVICE. DAMAGE NOTED AT RECEIVIN	G INSPECTION BY REPAIR STATION PRIOR TO REPAIR. REPAIR DEVELOPED AND DER-APPROVED TO CORRECT CONDITION IN REPAIRED ASSEM	BLIES, HOWEVER DESIGN SHOULD BE REVIEWED AS DISLODGED MATERIAL HAS POTENTIAL TO CONTACT TURBINE ROTOR.								3	T			AEXJ STC				 
2002012400068	20020124	00068	CE  	2002	1	24	2002FA0000118    	1	20020110	G	3213		AXLE            			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										DURING FLOURESCENT PENETRANT INSPECTION, FOUND CRACK IN AREA 1A (AXLE SHAFT RADIUS)						1	H	7	1 	3O			 	3A17    					 
2002012400069	20020124	00069	CE  	2002	1	24	2002FA0000119    	1	20020110	G	3213		AXLE            			CESSNA	177   	177RG       	2073709	CE  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										DURING FLOURESCENT PENETRANT INSPECTION, FOUND CRACK IN RADIUS OF AXLE SHAFT (AREA 1A )						1	H	7	1 	3O			 	A20CE   					 
2002012400071	20020124	00071	CE  	2002	1	24	2002FA0000120    	1	20020110	G	3213		AXLE            			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										DURING FLOURESCENT PENETRANT INSPECTION, FOUND CRACK IN AXLE SHAFT RADIUS.						1	H	7	1 	3O			 	3A17    					 
2002012400077	20020124	00077	CE  	2002	1	24	2002FA0000122    	1	20020114	G	2750	151228024	BUSHING         			CESSNA	172   	172S        	2072439	CE  										TE FLAPS	MISSING         	B				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		DE	DESCENT        	1			WP	07	521ER	342  				172S8924				FLAPS FAILED TO RETRACT DURING TOUCH AND GO TRAINING.   INSPECTION BY MAINTENANCE FOUND BUSHING (P/N 1512280-24) HAD NOT	 BEEN INSTALLED AT THE FACTORY.  THIS ALLOWED THE FLAP ARM ASSEMBLY (P/N 0560022-8) TO MOVE AWAY FROM FLAP LEVER ASSEMBL	Y (P/N 0560021-1) PREVENTING PROPER OPERATION OF THE FLAP SWITCHES (P/N S1906-1).				1	H	7	1 	3O			NT	3A12    					 
2002012400078	20020124	00078	CE  	2002	1	24	2002FA0000123    	1	20020108	G	5610		WINDOW          			CESSNA	150   	150M        	2071830	CE  										COCKPIT	SEPARATED       	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			EA	23	63206					15077174				PILOT SIDE WINDOW (LOCATED ON PILOT'S DOOR) DEPARTED AIRCRAFT DURING FLIGHT WHEN WINDOW WAS OPENED. FOLLOWING AN EXAMINA	TION OF THE DOOR ON THE AIRCRAFT, IT APPEARED THAT BOTH THE FORWARD AND REAR HINGE PINS SHEARED ALLOWING THE WINDOW AND 	WINDOW FRAME TO SEPARATE FROM THE AIRCRAFT. THERE WAS NO DAMAGE TO THE HINGE HALVES SECURED TO THE DOOR FRAME.				1	H	7	1 	3O			 	3A19    					 
2002012400083	20020124	00083	SO  	2002	1	24	2002FA0000125    	2	20020117	G	7414	10391586	DISTRIBUTOR BLK 	CONT        	S6RN1225    	CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					MAGNETO	BROKEN          	D				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			WP	23	PKMCA	452  			E259925FR	U20601269				THE CENTER BUSHING IN THE DISTRIBUTOR BLOCK IS LOOSE AND SHOWS SIGNS OF OVERHEATING.  AS A RESULT THE DISTRIBUTOR GEAR W	OBBLED AND THE FINGER CONTACTED ALL THE HIGH TENSION CONTACT TOWERS AND GROUND THEM OFF.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2002012400086	20020124	00086	CE  	2002	1	24	2002FA0000126    	1	20020109	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										LT CENTER WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	332DM	7401 				4410167				DURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85 	INCHES) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45 ) AND EXTENDING APPROXIMATELY 1 IN	CH AFT OF THE SPAR. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED W	ITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK.			1	L	7	2 	3T			RT	A28CE   					 
2002012400087	20020124	00087	CE  	2002	1	24	2002FA0000127    	1	20020109	G	5712	57222062	RIB             			CESSNA	441   	441         	2076020	CE  										RT CENTER WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	332DM	7401 				4410167				DURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCWS 26.85	) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1 INCH AFT 	OF THE SPAR. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE	 BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK. CESSNA CURRENTLY DOES NOT HA	VE ANY SPECIFIC INSPECTIONS RELATING TO THIS MATTER, THEREFORE, THIS AREA SHOULD BE CLOSELY INSPECTED DURING ROUTINE INS	PECTIONS.	1	L	7	2 	3T			RT	A28CE   					 
2002012400089	20020124	00089	CE  	2002	1	24	2002FA0000128    	1	20020118	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										LT CENTER WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	621SC	7401 				4410070				DURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85)	 HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1.5 INCH AFT	 OF THE SPAR. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH TH	E BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK.			1	L	7	2 	3T			RT	A28CE   					 
2002012400090	20020124	00090	CE  	2002	1	24	2002FA0000129    	1	20020118	G	5712	57222062	RIB             			CESSNA	441   	441         	2076020	CE  										RT CENTER WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	621SC	10559				4410070				DURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCWS 26.85	) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1.5 INCH AF	T OF THE SPAR. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH T	HE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK.			1	L	7	2 	3T			RT	A28CE   					 
2002012400091	20020124	00091	CE  	2002	1	24	2002FA0000130    	1	20020123	G	3010	2H4814	VALVE           			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					DEICE SYSTEM	FAULTY          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	340SV					340A1003				REPLACED DEFECTIVE SURFACE DEICE CONTROL VALVE WITH NEW 2H48-14 S/N 2AU 29.  ON RUN CHECK FOUND SYSTEM TO HAVE UNCOMMAND	ED SURFACE DEICE ACTIVATION.  CHECKED SYSTEM AND FOUND NEW VALVE LEAKING FROM FAULTY ASSEMBLY AT RIVETED TOP CAP WHERE S	OLENOID IS ATTACHED. THIS ALLOWS FAULTY SEAL AND AIR BYPASS TO ACTIVATE VALVE.				1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2002012400094	20020124	00094	CE  	2002	1	24	2002FA0000132    	1	20020123	G	3340	TTGCTA201TWB	SWITCH          			CESSNA	172   	172N        	2072434	CE  										TAXI LIGHT	FAILED          	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			WP	07	5124E					17271723				SWITCH ARCED INTERNALLY AND QUIT WORKING.  SWITCH TERMINALS WERE CLEAN AND THE WIRE SLIP-ON CONNECTORS WERE CLEAN AND TI	GHT.  WHEN SWITCH FAILS IT EMITS A BIT OF SMOKE.  THESE SWITCHES FAIL ON A REGULAR BASIS.					1	H	7	1 	3O			NT	3A12    					 
2002012500001	20020125	00001	CE  	2002	1	25	2002FA0000134    	1	20020116	G	7120	J96135	SHOCK MOUNT     			BEECH 	55    	95A55       	1152704	CE  	CONT  	O470  	IO470L      	17026	SO  					RT ENGINE	MISSING         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	9624Y					TC377	1920027LR			FOUND RIGHT FORWARD ENGINE VIBRATION ISOLATOR MOUNT AND ATTACH HARDWARE MISSING FROM RIGHT ENGINE.						1	L	7	2 	3O	3	O	 	3A16    	3E1				 
2002012800044	20020128	00044	EU  	2002	1	28	2002FA0000135    	1	20020116	G	2913	GHE1004	PUMP            			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					HYDRAULIC SYS	SLUGGISH        	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	266SD	346  				1133				FLIGHT CONTROLS HAD A SLIGHT RATCHET FEELING AND SLUGGISH.  HYDRAULIC OFF CHECKS RESPONDED SLOWLY (10 SECONDS).  PROBABL	E CAUSE: LOWER THAN NORMAL PRESSURE AND/OR LOWER THAN NORMAL FLOW.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2002012800049	20020128	00049		2002	1	28	2002FA0000137    	4	20020110	G	2561	SMV2102	LIFE VEST       																	CABIN	FAILED          	C			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25										LIFE VEST FAILED,																			 
2002012900001	20020129	00001	CE  	2002	1	29	2002FA0000138    	1	20020128	G	5412		FIREWALL        			CESSNA	172   	172R        	2072401	CE  										NACELLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	9577F	1075 				17280526				IT WAS DISCOVERED DURING ROUTINE MAINTENANCE THAT THE LT LOWER FIREWALL HAD A NEARLY 3 INCH CRACK BENEATH THE CENTER, LO	WER COWL MOUNT DOUBLER. THIS CONDITION WAS ALSO DISCOVERED ON THE NEXT FOUR LIKE AIRCRAFT AND THEY WERE ALL CORRECTED IN	 ACCORDANCE WITH SERVICE BULLETIN 98-53-02, REVISION 2, DATED 12/26/00				1	H	7	1 	3O			NT	3A12    					 
2002013000004	20020130	00004	EU  	2002	1	30	2002FA0000139    	1	20020117	G	3340	350A73029001	CONTROL PANEL   			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					SEARCH LIGHT	FAILED          	C				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	25	277SD	58   				1134				SX 16 NIGHTSUN QUIT OPERATING.  FOUND RELAY PANEL INOPERATIVE.  REPLACE RELAY ASSEMBLY.  PROBABLE CAUSE:  RELAY INTERNAL	 FAILURE.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2002013000005	20020130	00005	EU  	2002	1	30	2002FA0000140    	1	20020117	G	3340	350A73029001	CONTROL PANEL   			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					SEARCH LIGHT	INOPERATIVE     	C				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			WP	25	277SD	58   				1134				SX16 NIGHTSUN QUIT OPERATING.  FOUND RELAY PANEL INOPERATIVE, REPLACE RELAY ASSEMBLY.  PROBABLE CAUSE:  RELAY INTERNAL F	AILURE.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2002013000006	20020130	00006	EU  	2002	1	30	2002FA0000141    	1	20020117	G	3340	6485000	LIGHT           			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ANTICOLLISION	SHORTED         	C				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			WP	25	266SD	9    				1133				ANTI COLLISION LIGHT POPPED CIRCUIT BREAKER.  REPLACED WITH NEW ASSEMBLY.  PROBABLY CAUSE:  INTERNAL SHORT CIRCUIT.						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2002013000007	20020130	00007	NE  	2002	1	30	2002FA0000142    	2	20020117	G	7313	319307840	NOZZLE          			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					TURBINE SECTION	BURNED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	266SD	200  				1133	34144			ENGINE WOULD NOT START.  REPLACED START NOZZLES (START-INJECTORS).  POSSIBLE CAUSE: FUEL BURNED IN NOZZLE AT END OF STAR	T CYCLE.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2002013000015	20020130	00015	SO  	2002	1	30	2002FA0000146    	1	20020116	G	2720	317729	CONTROL CABLE   			MAULE 	M5    	M5235C      	5460135	SO  	LYC   	O540  	O540*       	41532	EA  					RUDDER	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	382X	1660 				7021C				UPON LANDING, WINDS WERE DOWN RUNWAY AT 15 MPH, THE LEFT RUDDER CABLE CAME LOOSE AT AIRCRAFT NICOPRESS SLEEVE CAUSING AI	RCRAFT TO GROUND LOOP.  THERE WAS NO EVIDENCE OF CORROSION ON CABLE OR SLEEVE AND SLEEVE WAS PREVIOUSLY INSPECTED FOR CO	RRECT SWEDGE PER AD.  THE AIRCRAFT IS REPAIRABLE AND WILL BE REPLACING ALL CABLES AND DOUBLING THE NUMBER OF NICOPRESS S	LEEVES TO ENSURE SECURITY.			1	H	7	1 	3O	3	O	 	3A23    	E295				 
2002013000002	20020130	00002	SO  	2002	1	30	2002FA0000147    	1	20020130	G	2822	481780	PUMP            			PIPER 	PA28  	PA28R201    	7102816	SO  										FUEL SYS	SHORTED         	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	11	448PA	154  				2844063				FUEL PUMP CIRCUIT BREAKER POPS. RESET BREAKER POPS AGAIN WHEN PUMP SWITCH IS TURNED ON.						1	L	7	1 	3O			 	2A13    					 
2002013000003	20020130	00003	SO  	2002	1	30	2002FA0000148    	1	20020130	G	2140	484180	SHUTOFF VALVE   			PIPER 	PA44  	PA44180     	7104402	SO  										HEATER	LEAKING         	C				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			SO	15	432PA	474  				4496058				CREW REPORTED FUEL FUMES IN COCKPIT WHEN HEATER SELECTED ON. SUBSEQUENT INSPECTION REVEALED THAT FUEL REGULATOR AND SHUT	OFF VALVE WAS LEAKING.					1	L	7	2 	3O			 	A19S0   					 
2002013000092	20020130	00092	EU  	2002	1	30	2002FA0000151    	1	20020127	G	2913	42046	PUMP            			FOKKER	F28   	F28MK0070   	4990811	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					HYD SYS	LEAKING         	C				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			GL	23	324K	1490 				11545	17107			APPROX. 2 HOURS INTO FLIGHT FROM DTW TO SNA SYSTEM 1 PUMP 1 FAULT LIGHT ILLUMINATED. CREW FOLLOWED THE ABNORMAL PROCEDUR	ES FOR HYDRAULIC SYSTEM 1 LOW PRESSURE. CREW NOTICE SYSTEM NR 1 QUANTITY BEGINING TO DROP. CREW DIVERTED HOPING TO GET O	N THE GROUND BEFORE LOSS OF TOTAL SYSTEM 1 QUANTITY AND PRESSURE. 15 - 20 MINUTES LATER SYSTEM 1 LO QUANTITY ALERT ILLIM	INATED. GEAR AND FLAPS WERE LOWERED USING THE ALTERNATE PROCEDURES. AIRCRAFT LANDED AT THE SLN AIRPORT. A MAINTENANCE CR	EW WAS DISPATCED FROM DTW TO REPAIR THE PROBLEM. THE MAINTENANCE CREW INSPECTED THE LEFT ENGINE FOUND THE NR 1  HYD. PUM	P LEAKING AT THE PUMP SPLIT LINE. THE  PRESSURE FILTER WAS INSPECTED FOR CONTAIMINATION, NONE WAS FOUND. THE PUMP WAS RE	2	L	7	2 	4F	4	F	RT	A20EU   	E25NE				 
2002020100001	20020201	00001	CE  	2002	2	1	2002FA0000152    	1	20020131	G	2731		PIN             			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ELEVTOR TRIM	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	24442	474  				17280862	L2869351A			WHILE REMOVING THE TRIM TAB ACTUATOR FOR SERVICE, BOTH GROOVE-PINS  (P/N 3/32X.38TYPE3)  WHICH ATTACH THE ROLL CHAIN SPR	OCKET, (P/N 0310332-0)  TO THE SCREW-INTERNAL THREADS (P/N 1260049-1) OF THE TRIM TAB ACTUATOR WERE FOUND TO HAVE SHEARE	D. THIS ALLOWED THE SPROCKET TO BE SLIPPED OFF BY HAND. ONLY FRICTION BETWEEN THE SPROCKET AND THE SCREW-INTERNAL THREAD	S WAS ENABLING THE TRIM TAB TO BE MOVED.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002020100002	20020201	00002	SO  	2002	2	1	2002FA0000153    	1	20020131	G	5600	494739	WINDOW          			PIPER 	PA46  	PA46350P    	7104602	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCE4N	HCE4N3      	NE  	FUSELAGE	CRACKED         	B				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	09	9167Q	760  	15   			4622031	PCKRB008	HH1000		WINDOW CRACKED LOWER FORWARD CORNER FROM STORM WINDOW OPENING TO MOUNTING BOLTS. AIRCRAFT WAS AT CRUISE AND 5PSI WHEN IN	CIDENT OCCURED.					1	L	7	1 	3O	4	T	RT	A25SO   	E4EA	5	C	P10NE	 
2002020500044	20020205	00044	SO  	2002	2	5	2002FA0000156    	2	20020105	G	8530		CONNECTING ROD  			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300*       	17022	SO  					NR 3 CYLINDER	FAILED          	D				O				OTHER                   				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			EA	23	3910R					17255410				NR 3 CYLINDER CONNECTING ROD AND CAP FAILED AT THE CRANKSHAFT. CONNECTING ROD FELL TO BOTTOM OF CYLINDER BORE AND WAS RE	PEATEDLY STRUCK BY THE CRANKSHAFT UNTIL ENGINE WAS SHUT DOWN.  THE FAILURE OCCURRED AFTER FINAL POWER REDUCTION DURING A	 ROUTINE LANDING.  PILOT REPORTED HEARING A LOUD BANG FOLLOWED BY POWER LOSS.  CAUSE OF FAILURE INDETERMINABLE.  PROBABL	E CAUSE OF FAILURE DEFECT IN ROD CASTING.  NOTED THAT THIS ENGINE HAS A MANUFACTURER RECOMMENDED TBO TIME OF 1800 HOURS.	  ENGINE HAD 2115 HOURS ON IT SINCE MAJOR OVERHAUL.  ENGINE DISASSEMBLY  WAS FOUND THAT ONE OF THE TWO ROD CAP BOLTS HAD	 BACKED OFF, AND THE NUT WAS FOUND IN THE BOTTOM OF THE CASE.	1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002020500045	20020205	00045		2002	2	5	2002FA0000157    	4	20020121	G	3452	118280001	TRANSFORMER     			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235*       	41505	EA  					TRANSPONDER	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	2509A					3878A0724				TRANSFORMER SHORTED.						1	L	7	1 	3O	3	O	 	A18SO   	E223				 
2002031200005	20020312	00005	WP  	2002	3	12	2002FA0000162    	1	20020114	G	3246	1542511	WHEEL           			DOUG  	DC8   	DC8*        	       	WP  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										DC8,  MAIN WHEEL ASSEMBLY, NON DESTRUCTIVE TESTING INSPECTION SHOWED HI-CONDUCTIVITY.						2	L	7	4 	4J			F	4A25    					 
2002031200006	20020312	00006	WP  	2002	3	12	2002FA0000163    	1	20020114	G	3246	2601475	WHEEL           			DOUG  	DC8   	DC8*        	       	WP  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										DC8, MAIN WHEEL ASSEMBLY, NON DESTRUCTIVE TESTING INSPECTION SHOWED CRACK INDICATION AT TUBE WELL AREA.						2	L	7	4 	4J			F	4A25    					 
2002031200007	20020312	00007		2002	3	12	2002FA0000164    	4	20020119	G	2561	P0201105	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOTATION DEVICE FAILED MFG RECOMMENDED 2 PSI CELL TEST IAW SB.																			 
2002031100105	20020311	00105	EU  	2002	3	11	2002FA0000165    	1	20020118	G	2910	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYDRAULIC SYS	DEBONDED        	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	19	352NT	395  				2553	886			WHILE RETURNING FROM STRIP TOURS, THE AIRCRAFT EXPERIENCED A LOSS OF HYDRAULIC POWER.  UPON SAFE LANDING ON THE TAXI WAY	, THE AIRCRAFT WAS IMMEDIATELY TOWED TO THE MAINTENANCE HANGER AND INSPECTED FOR PROBABLE CAUSES OF THE HYDRAULIC FAILUR	E.  IT WAS FOUND THAT THE BONDED SEAM OF THE HYDRAULIC DRIVE BELT HAD SEPARATED AT THE BOND.  POSSIBLE RECOMMENDATIONS T	O PREVENT REOCCURRANCE WOULD BE HIGHER QUALITY CONTROL AT THE MANUFACTURER OR A HIGHER QUALITY HYDRAULIC DRIVE BELT.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002031200008	20020312	00008	CE  	2002	3	12	2002FA0000166    	1	20020109	G	3230	501202015	DRAG BRACE      			BEECH 	200   	A200        	1152921	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	783MC	12588				BC02				DURING SCHEDULED LANDING GEAR TIME CHANGE, THE DRAG BRACE SUPPORTS WERE CLEANED AND INSPECTED.  THE RIGHT DRAG BRACE SUP	PORT APPEARED TO BE CRACKED.  A DYE-PENETRANT INSPECTION WAS CONDUCTED AND THE CRACKED CONFIRMED.  AT THAT TIME AN ALERT	 WAS ISSUED TO TEST THE  FLEET AND ANOTHER 4 SUPPORTS WERE FOUND CRACKED.  THE AREA TO PAY CLOSE ATTENTION TO IS THE RAD	IUS BETWEEN THE TWO LUGS.  THE C12 FLEET BEING USED ARE HIGH TIME AIRCRAFT WITH HIGH LANDING CYCLES.  DURING MAINTENANCE	 INSPECTIONS, CLOSE ATTENTION SHOULD BE PAID TO THE DRAG BRACE SUPPORTS.		1	L	7	2 	4T			 	A24CE   					 
2002031200009	20020312	00009	CE  	2002	3	12	2002FA0000167    	1	20020116	G	2421	648843	ALTERNATOR      			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	FAILED          	B			VJ3R	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			WP	03	5544A	72   				CE1343	825767R			ALTERNATOR FAILED IN FLIGHT,  WILL NOT CARRY THE LOAD.  REPLACED ALTERNATOR,  GROUND CHECKED OK.  RETURNED TO SERVICE.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002031200010	20020312	00010		2002	3	12	2002FA0000168    	4	20020120	G	2561	P02301105	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOTATION DEVICE FAILED MFG RECOMMENDED 2 PSI CELL TEST.																			 
2002031200011	20020312	00011	CE  	2002	3	12	2002FA0000169    	1	20020117	G	2460	7014300901	CIRCUIT BREAKER 			CESSNA	500   	560CESSNA   	2076750	CE  										ELECTRICAL	ARCED           	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	25	CGJEI					5600588				COCKPIT FILLED WITH SMOKE AND ODOR OF BURNING MATERIAL.  INSPECTION OF WIRING AND SYSTEM INSTALLATION, FOUND ONE TERMINA	L ON POWER CIRCUIT BREAKER PANEL WITH EVIDENCE OF  ARCING,  BUT NOT RELATED TO THIS UNITS OPERATION SOME INTERNAL FAILUR	E HAS OCCURRED, W HEN POWERED UP IT STARTS TO SMOKE.				2	L	7	2 	4F			RT	A22CE   					 
2002031200012	20020312	00012	GL  	2002	3	12	2002FA0000170    	1	20020128	G	2822		PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					FUEL BOOST	INOPERATIVE     	G				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	07	645DC					C0145	806272			ENGINE QUIT DURING STALL PRACTICE.  ENGINE WOULD START BUT NOT RUN.  LANDED IN FIELD.  FUEL PRESSURE TOO LOW.  FACTORY R	EP INSTALLED SETUP GAGES AND ADJUSTED TO PROPER SPECS.  ENGINE RAN GOOD AFTER PROPER ADJUSTMENT.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2002031200013	20020312	00013	CE  	2002	3	12	2002FA0000171    	1	20020109	G	2760	55170115	LINE            			CESSNA	500   	550         	2076604	CE  										SPEED BRAKES	CHAFED          	B			CNQ6	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	133AV	1369 				5500847				REPORTED HYDRAULIC LEAK INSPECTED AND FOUND TO BE SPEED BRAKE RETRACT LINE.  LINE HAS BEEN CHAFFED THROUGH BY CENTER FLA	P BELLCRANK PUSH ROD ATTACH HARDWARE.  FABRICATED REPLACEMENT LINE AND MADE APPROPRIATED BENDS TO CLEAR OFFENDING AREA O	F FLAP BELLCRANK.				1	L	7	2 	4F			 	A22CE   					 
2002031100106	20020311	00106		2002	3	11	2002FA0000172    	4	20020201	G	3422	5050010902	GYRO            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COCKPIT	PRECESSES       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	891SA		429  			2201	4193			GYRO REMOVED DUE TO EXCESS PRECESSION.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002031200014	20020312	00014	CE  	2002	3	12	2002FA0000173    	1	20020131	G	5210	504300431291	INTERCOSTAL     			BEECH 	200   	B200        	1152922	CE  										PAX DOOR	CRACKED         	B			KX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	417MC	4738 				BB1526				UPON PHASE INSPECTION OF CABIN DOOR, FOUND EXCESSIVE MOVEMENT FROM HAND RAIL ASSEMBLIES AT HINGE AREAS ON BOTH FORWARD A	ND AFT HANDRAILS.  UPON FURTHER INSPECTION, FOUND BOTH INTERCOSTAL STRUCTURES CRACKED AROUND RIVETS.					1	L	7	2 	4T			 	A24CE   					 
2002031200015	20020312	00015	CE  	2002	3	12	2002FA0000174    	1	20020123	G	7810	99102992	EXHAUST PIPE    			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT ENGINE	CRACKED         	B			EWGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	340WT					340A0332				PILOT OBSERVED RT FUEL QUANTITY INDICATOR FAILED, THEN RT FUEL TRANSFER LIGHT ON AND RT LANDING LIGHT CIRCUIT BREAKER PO	PPED.  AFTER FLIGHT, VISUAL INSPECTION OF THE RT ENGINE NACELLE IDENTIFIED A BURN THROUGH NACELLE SKIN ADJACENT TO THE R	T ENGINE OVERBOARD TAILPIPE.  INVESTIGATION REVEALED THE TAILPIPE HAD FAILED AT THE  OUTBOARD BEND, IN THE ENGINE COMPAR	TMENT, DAMAGING THE EXTERNAL NACELLE SKIN, FIREWALL, CANTED BULKHEAD, ENGINE BEAM, AND WIRING BEHIND THE FIREWALL.			1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2002031200016	20020312	00016	SO  	2002	3	12	2002FA0000175    	2	20020130	G	8500	IO470D	ENGINE          			CESSNA	310   	310G        	2074218	CE  	CONT  	O470  	IO470D      	17026	SO  					5&6 CYLINDERS	FAILED          	D				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SO	19	8939Z	2642 	1170 			310G0039				WHILE PERFORMING A STATIC GROUND RUN, AT APPROX. 2200 RPMS THE ENGINE SHOOK VIOLENTLY.  THE ENGINE WAS QUICKLY SHUT DOWN	 AND FUEL SHUT-OFF VALVE SELECTED TO THE OFF POSITION.  CLOSE INSPECTION OF THE ENGINE REVEALED THAT THE NR 6 CYLINDER H	AD SEPARATED FROM THE ENGINE.  THE NR 5 CYLINDER WAS JAMMED WITH THE PISTON CONNECTING ROD SEVERED IN HALF.  THE FORWARD	 ENGINE CASE WAS CRACKED IN SEVERAL PLACES EXPOSING BOTH NR 5 AND NR 6 CYLINDER ASSEMBLIES INNER MECHANISM AND CRANKSHAF	T.  RECOMMENDATIONS ARE TO REMOVE ENGINE AND SUBMIT IT TO A TEARDOWN INSPECTION ALONG WITH A METALLURGIC EVALUATION ON T	HE INTERNAL PARTS FOR FAILURE.  IN PARTICULAR, THE NR 5 CYLINDER CONNECTING ROD AND FORWARD ENGINE CASE.	1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2002031200017	20020312	00017	NE  	2002	3	12	2002FA0000176    	2	20020125	G	7314	025323150	PUMP            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					FUEL SYSTEM	FAILED          	C			NSPA	A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	05	9454B	845  				208B0072				HAD AN ENGINE FAILURE WHICH RESULTED IN THE AIRCRAFT LANDING SHORT OF THE AIRPORT.  NO ONE WAS INJURED AND THE AIRCRAFT 	WAS NOT DAMAGED.  ENGINE QUIT DUE TO ENGINE DRIVEN FUEL PUMP FAILURE.  FUEL PUMP WAS REMOVED, A NEW PUMP INSTALLED, AND 	THE AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2002020800021	20020208	00021	CE  	2002	2	8	2002FA0000177    	1	20020205	G	3240	S14953	HOSE            			CESSNA	182   	182Q        	2072732	CE  										RT MLG	OUT OF POSITION 	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23	4603N	2976 				18267280				WHILE BOTH MLG TRUNNION FAIRINGS WERE REMOVED FOR OTHER MAINTENANCE, TRUNNIONS AND BRAKE LINES WERE CLEANED AND INSPECTE	D.  OPERATOR DISCOVERED RT BRAKE LINE CHAFED THROUGH AND WEEPING HYDRAULIC FLUID.  CHAFED POINT IN LINE WAS A BEAM FLANG	E ON TRUNNION WHICH SUPPORTS COPILOT'S STEP.  A HOSE (WHICH SHOULD BE POSITIONED MIDWAY ALONG BRAKE LINE TO PREVENT CONT	ACT WITH THE STEP STRUCTURE) WAS FOUND AT LOWER END OF BRAKE LINE.  HOSE SEGMENT HAD EVIDENTLY MIGRATED DOWN THE LINE AS	 RESULT OF VIBRATION OR ACCUMULATED LANDINGS.  LOGBOOK ENTRIES SUGGEST THIS HOSE COMPONENT WAS PART OF ORIGINAL INSTALLA	TION.	1	H	7	1 	3O			NT	3A13    					 
2002031200018	20020312	00018	SO  	2002	3	12	2002FA0000180    	2	20020124	G	7414	6320	MAGNETO         			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520*    	17040	SO  					RIGHT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	47BC					4608129				PILOT REPORTED FAILED RT MAGNETO.  REMOVED MAGNETO FROM ENGINE AND DISASSEMBLED.  FOUND ONE OF THE COIL ANCHOR WEDGES WA	S DISPLACED AND HAD MIGRATED ONTO THE SECONDARY TOWER.  THE TOWER WAS BURNED AND MELTED AND THERE WAS OBVIOUS SIGNS OF A	 DIRECT SHORT AT THE SECONDARY TERMINAL CONTACT TAB.				1	L	7	1 	3O	3	O	RT	A25SO   	E8CE				 
2002021100018	20020211	00018	CE  	2002	2	11	2002FA0000181    	1	20020208	G	5720		BRACKET         			CESSNA	500   	560CESSNA   	2076750	CE  										RT WING	FAILED          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	09	300QS	2553 				0322				IN-TRANSIT LIGHT STAYED ON AFTER GEAR WAS RETRACTED.  GEAR WAS EXTENDED AND A/C LANDED WITHOUT INCIDENT.  UPON INSPECTIO	N, THE RT GEAR WELL PLACARD CLOSEOUT PANEL WAS FOUND TORN AND BENT UP.  THE INBOARD Z-BRACKET HAD FAILED, AS WELL AS THE	 LOWER ANGLE, THAT THE PANEL IS RIVETED TO.  AFTER FAILURE OF BOTH PANEL MOUNT BRACKETS, AIRLOADS MAY HAVE STARTED TO PU	LL THE PANEL OUT UNTIL THE LANDING GEAR FINALLY CAUGHT IT AND TORE IT UPWARD WHEN GEAR WAS RETRACTED.  REPLACED THE PANE	L AND BOTH MOUNT BRACKETS.  THE Z-BRACKET IN THIS AREA HAS A HISTORY OF FAILING AND IS REPLACED AT FAIRLY FREQUENT INTER	VALS.	2	L	7	2 	4F			RT	A22CE   					 
2002021100019	20020211	00019	CE  	2002	2	11	2002FA0000182    	1	20020208	G	2720	1285200041	PUSHROD         			MTSBSI	MU300 	MU300       	5780602	CE  										RUDDER PEDAL	CHAFED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	399MM	6539 				A017				UPON INSPECTION, PILOT AND COPILOT RUDDER PEDAL PUSH RODS WERE FOUND SEVERELY CHAFED ON THE TOP SIDE, EVIDENTLY BY MAKIN	G CONTACT WITH THE FLOOR SKIN.  THIS CONDITION HAD BEEN OCCURRING FOR QUITE SOME TIME FOR THE PUSH RODS TO HAVE BEEN CHA	FED THIS SEVERELY.  REPLACED BOTH PUSH RODS WITH NEW.  CORRECTED CHAFE CONDITION WITH FLOOR SKIN.  RECOMMEND THIS AREA G	ET PARTICULAR ATTENTION DURING INSPECTIONS TO LOOK FOR CHAFE CONDITION OF THESE PUSH RODS.			2	H	7	2 	4F			RT	A14SW   					 
2002031200019	20020312	00019	CE  	2002	3	12	2002FA0000186    	1	20020129	G	5412		FIREWALL        			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE BAY	CRACKED         	D			MNZS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	361SA					17280755				DISCOVERED DURING ROUTINE MAINTENANCE THAT THE LEFT LOWER FIREWALL HAD  CRACK LOCATED BENEATH THE DOUBLER FOR THE LEFT L	OWER COWL MOUNT.  IN ONE INSTANCE, CRACK WAS ACTUALLY LOCATED BENEATH THE LEFT FLANGE OF THE BATTERY MOUNT.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002031200020	20020312	00020	CE  	2002	3	12	2002FA0000187    	1	20020210	G	5412		FIREWALL        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE BAY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	364MA					172S8007				IT WAS DISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DO	UBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER W/O KNOWLEDGE OF THE PROBLEM.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002031200021	20020312	00021	CE  	2002	3	12	2002FA0000191    	1	20020210	G	5412		FIREWALL        			CESSNA	172   	172R        	2072401	CE  										ENGINE BAY	CRACKED         	D			MNZS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9577F					17280526				IT WAS DISCOVERED DURING AN ANNUAL INSPECTION THAT FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLE	R.  ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF PROBLEM.					1	H	7	1 	3O			NT	3A12    					 
2002031200022	20020312	00022	CE  	2002	3	12	2002FA0000193    	1	20020210	G	5412		FIREWALL        			CESSNA	172   	172R        	2072401	CE  										ENGINE BAY	CRACKED         	D			MNZS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9532K					17280475				DISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. 	 ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM.					1	H	7	1 	3O			NT	3A12    					 
2002031200023	20020312	00023	CE  	2002	3	12	2002FA0000194    	1	20020210	G	5412		FIREWALL        			CESSNA	172   	172R        	2072401	CE  										ENGINE BAY	CRACKED         	D			MNZS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	361SA					17280755				DISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. 	 ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM.					1	H	7	1 	3O			NT	3A12    					 
2002031200024	20020312	00024	CE  	2002	3	12	2002FA0000195    	1	20020210	G	5412		FIREWALL        			CESSNA	172   	172R        	2072401	CE  										ENGINE BAY	CRACKED         	D			MNZS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	24338					17280810				DISCOVERED DURING AN ANNUAL INSPECTION THAT FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER.  ALM	OST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM.					1	H	7	1 	3O			NT	3A12    					 
2002031200025	20020312	00025	CE  	2002	3	12	2002FA0000196    	1	20020201	G	3230	08421022	BELLCRANK       			CESSNA	310   	310L        	2074230	CE  										MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	510V					310L0113				AFTER REPLACING BROKEN SQUAT SWITCH, CONDUCTED ROUTINE RETRACTION TEST TO CHECK FUNCTION OF GEAR.  MAINS RETRACTED NORMA	LLY, NOSE GEAR STARTED TO RETRACT AND THEN BOUND UP. BEFORE LANDING GEAR LEVER COULD BE MOVED TO NEUTRAL POSITION, LOUD 	BANG AND MOVEMENT OF FLOOR UNDER LEFT SIDE OF CONSOLE NOTED.  NOSE GEAR SWUNG FREE, INSPECTION FOUND THAT THE IDLER BELL	CRANK HAD A UNSEEN BREAK IN THE METAL AROUND THE REAR BOLT HOLE. THIS ALLOWED THE METAL TO TIP UP AND CONTACT THE BULKHE	AD, THE RESULTING BINDING CAUSED THE BOLT AND BEARING IN THE REAR DRIVE TUBE TO BE PULLED OUT OF THE ROD END.  FORTUNATE	LY THIS OCCURRED WHEN AIRCRAFT WAS ON JACKS.	1	L	7	2 	3O			 	3A10    					 
2002031200026	20020312	00026	CE  	2002	3	12	2002FA0000197    	1	20020130	G	2421		BEARING         			BEECH 	35    	S35         	1151532	CE  	CONT  	O520  	IO520*      	17032	SO  					ALTERNATOR	INOPERATIVE     	B			X0FR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	07	10WR	340  			A86333	D7689	1203824B			AIRCRAFT CAME IN FOR ALTERNATOR FAILURE.  TESTED ALTERNERATOR SYSTEM AND DETERMINED ALTERNATOR, FAILED.  REMOVED ALTERNA	TOR, NOTICED THAT THE COTTER KEY, NUT AND WASHER THAT HOLDS THE CLUTCH ON, WAS MISSING.  FOUND CLUTCH ASSEMBLY BROKEN AN	D SHAFT OF ALTERNATOR VERY WORN OUT.  REMOVED ENGINE AND OIL PAN.  FOUND MISSING HARDWARE IN OIL PAN.  APPEARS SHAFT BEA	RINGS WORN OUT AND SHAFT WAS LOOSE ENOUGH TO BAKE COTTER KEY AND TO DISLODGE NUT AND WASHER.  ALTERNATOR INTERIOR OIL SO	AKED.  FRONT BEARING/SEAL WORN OUT.		1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002031200027	20020312	00027	CE  	2002	3	12	2002FA0000198    	1	20020115	G	7120		WASHER          			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A11      	52043	NE  					ENGINE BOLTS	WRONG PART      	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05	208LB	801  				20800283				DURING A ROUTINE INSPECTION,  FOUND THE ENGINE MOUNT BOLTS HAD AN960616L WASHERS INSTALLED UNDER BOLT HEADS (12 BOLTS ) 	TOTAL.  THIS TYPE BOLT MUST HAVE MS20002C6 WASHERS.					1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
2002031200028	20020312	00028		2002	3	12	2002FA0000199    	4	20020109	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					PROPELLER	CRACKED         	B			FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	792SP	156  				172S8717				FOUND CRACKED PROP SPINNER.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002031200029	20020312	00029	WP  	2002	3	12	2002FA0000201    	1	20020129	G	2820	168863Q01	HOSE            			NAMER 	F51   	P51D        	6402304	WP  	PCKARD	V1650 	V16507      	49001	SO  					FUEL SYSTEM	SPLIT           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	51JB					4473029A				UPON INSTALLATION OF A FUEL SELECTOR NOTICED THE OUTER COVER OF THE HOSE SPLIT AS IT WAS INSTALLED ON AN NIPPLE FITTING.	  AFTER CLOSE EXAMINATION, THE  NEW HOSE SHOWS A MARK / CUT GOING THE LENGTH OF THE HOSE.  IN SOME AREAS IT IS A MARK AN	D OTHER AREAS IT IS A CUT THROUGH THE OUTER LAYER OF THE HOSE.  THE DEFECT IS STRAIGHT WITH NO WAVERING AND APPEARS LIKE	 IT CAME FROM THE MANUFACTURES EQUIPMENT THIS WAY.  THIS MATERIAL REQUIRED REPLACEMENT OF ALL NEWLY INSTALLED HOSE ON TH	IS AIRCRAFT.		1	L	7	1 	4V	4	V	 	L113    	EXP4V				 
2002031200030	20020312	00030	EA  	2002	3	12	2002FA0000204    	2	20020116	G	8520	LW13827	CRANKCASE       			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					RT ENGINE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	502SB	2585 				61P0502207	L1784148A			CRANKCASE FAILED NEAR NR 2 CYLINDER, CRACKED FROM IN FRONT OF CYLINDER RADIALLY BELOW AND AROUND TO THE REAR OF THE CYLI	NDER.  CRACK EXTENDS MORE THAN 180 DEGREES,  ALL 3 UPPER CYLINDER BASE STUDS AND UPPER CRANKCASE THRU BOLT WERE ALL BROK	EN.  THE ONLY THING STILL HOLDING THE CYLINDER TO THE ENGINE WAS THE LOWER .5000 THRU BOLT.				1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2002031200031	20020312	00031		2002	3	12	2002FA0000205    	4	20020131	G	2300	S28701	SWITCH          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					MICROPHONE	INTERMITTENT    	B			LC1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	35331					17281037				REOCCURING INTERMITTENT PUSH TO TALK SWITCH OPERATION.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002031200032	20020312	00032		2002	3	12	2002FA0000206    	4	20020202	G	2561	KS9P0201	LIFE VEST       																	CABIN	FAILED          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED, MFG RECOMMENDED 2PSI, CELL TEST IAW 25-60-1.																			 
2002031200033	20020312	00033	SO  	2002	3	12	2002FA0000209    	2	20020123	G	8520		SLEEVE          								CONT  	O520  	GTSIO520M   	17032	SO  					LIFTER BORE	SEPARATED       	B			CQ2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15							276346R			LIFTER BORES WERE SLEEVED (12 EA) NOTE: SLEEVES CAME LOOSE IN ALL HOLES (EXCEPT 2), ROTATING AND BLOCKING OIL PASSAGE. N	O SAFETY PINS IN PLACE TO MAINTAIN SECURITY OF SLEEVES, NO OTHER MEANS OF HOLDING SLEEVES IN PLACE. ONLY THING THAT APPE	ARED TO HOLD SLEEVES WAS BURR, CREATED WHEN OIL HOLE WAS DRILLED, AND MAYBE DRAIN HOLE AT BOTTOM WAS BURRED.  (INTENDED 	TO HAVE AN INTERFERENCE FIT ONLY, BETWEEN  HOLE PREPAIRED FOR SLEEVE AND SLEEVE WAS OF VERY THIN WALL,  ALUMINUM SLEEVE 	MATERIAL HOLE FINISH SIZE IS 1.000 INCH, FOR LIFTER,  SLEEVE APPEARS TO HAVE APPROX 1.125 DIAMETER CREATING ONLY A .062 	WALL THICKNESS.  NOT ENOUGH TO MAINTAIN SECURITY WITHOUT AID OF STABILIZING PIN OR (WELD IN PLACE) OR MEANS OF SAFETY.						3	O			E7CE				 
2002031200035	20020312	00035	CE  	2002	3	12	2002FA0000211    	1	20020128	G	3230	NAS561P628	PIN             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					LT MLG	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	689AE	5026 				4410281				DUE TO PIN FAILURE ON AIRCRAFT, PINS WERE REMOVED FOR INSPECTION AND THE LEFT TO THE POINT OF FAILURE .  THE FORWARD PIN	 ON THE RIGHT SIDE WAS INTACT BUT SHOWING SIGNS OF SHEARING.  ALL FOUR MAIN LANDING GEAR PIVOT SLOTTED PINS WERE REPLACE	D WITH NEW NAS561P628.				1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2002031200039	20020312	00039	CE  	2002	3	12	2002FA0000214    	1	20020213	G	2820	1200406131	LINE            			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					FUEL VENT	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	09	711PJ	2500 				21061128				LINE DEVELOPED PINHOLE LEAK DUE TO CORROSION WHERE CABIN VENT SCEET HOSE RESTED ON TOP OF IT.						1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2002031200040	20020312	00040	CE  	2002	3	12	2002FA0000216    	1	20020212	G	3233	JE1	ACTUATOR        			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520N    	17040	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	RT MLG	BROKEN          	D				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CE	03	340TC	9000 				3400082	218720R	EB1908		RT MLG DOWN LIGHT DID NOT SHOW DOWN AND LOCK.  REMOVED RIGHT SWITCH (DOWNLOCK) 1SE1 SWITCH AND ACTUATOR SWITCH LEAF (JE1	) FELL OUT.  THE JE1 ACTUATOR WAS BROKEN AND PART OF THE ACTUATOR WAS MISSING.  ORDERED NEW PARTS,REPLACED 1SE1(SWITCH)A	ND ACTUATOR JE1 WITH MFG PART,  PART NUMBER S2112-1 (ACTUATOR) AND S2088-4(SWITCH).				1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P36EA	 
2002031200041	20020312	00041	SO  	2002	3	12	2002FA0000217    	2	20020215	G	8550	642841	LINE            			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					ENGINE OIL	WORN            	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	113VK	2620 	450  			28R7803352				ENGINE LOST OIL PRESSURE IN CRUISE FLIGHT.  THE PILOT MADE AN UNSCHEDULED LANDING.  INVESTIGATION REVEALED THAT THE OIL 	FILLER CAP HAD COME OFF AND THE ENGINE LOST OIL.  THE INTERNAL AREA OF THE OIL FILLER TUBE HAD WORN AND WOULD NO LONGER 	PUT SUFFICIENT PRESSURE ON THE OIL CAP RETAINING SPRING CLIPS.  DUE TO THE IMPACT ON SAFETY, THE OIL FILLER TUBE SHOULD 	BE REPLACED AT ENGINE TBO.			1	L	7	1 	3O	3	O	 	2A13    	E9CE				 
2002031200046	20020312	00046	CE  	2002	3	12	2002FA0000223    	1	20020206	G	5753	0523921	ROLLER          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					TE FLAP	GOUGED          	B			IB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	4206K	933  				17280751				DURING ACCOMPLISHMENT OF SB, THE LT FLAP INBOARD TRACK INBOARD AFT BEARING SUPPORT ARM WAS FOUND TO BE GOUGED .025 INCH 	DEEP MATCHING THE OUTER RADIUS OF THE ROLLER ASSEMBLY.  THE ROLLER ASSEMBLY WAS FOUND TO HAVE THE INNER ROLLER CAGE OFFS	ET ENOUGH TO ALLOW THE OUTSIDE DIAMETER OF THE ASSEMBLY TO ROTATE AGAINST THE FLAP SUPPORT ARM CAUSING THE GOUGE.  THE O	FFSET OF THE INNER CAGE WAS FOUND TO BE .025 INCH MATCHING THE DEPTH OF THE GOUGE.  PROBABLE CAUSE APPEARS TO BE IMPROPE	R CENTERING OF THE INNER BEARING CAGE AT INITIAL ASSEMBLY.  MFG HAS BEEN NOTIFIED.  RECOMMEND BEARING INSPECTION AT FLAP	 INSTALLATION AND ASSURING CLEARANCE BETWEEN THE BEARING ENDS AND THE FLAP SUPPORT ARMS.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002031200047	20020312	00047	SO  	2002	3	12	2002FA0000224    	1	20020205	G	2700	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					STABILATORS	FRAYED          	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4146D	2546 				2843153				FOUND THE RT AND LT FORWARD STABILATOR CONTROL CABLES FRAYED AND WORN DURING A 100 HOUR INSPECTION.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002031200049	20020312	00049	CE  	2002	3	12	2002FA0000226    	1	20020206	G	7120	085112120	BEAM            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT ENGINE	CORRODED        	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2696U					340A0780				FOUND RT OUTBOARD ENGINE BEAM CORRODED BEYOND LIMIT, CANTED BULKHEAD WAS ALSO CORRODED BEYOND LIMITS.  SUGGEST SHORTER I	NTERVAL BETWEEN INSPECTIONS.					1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2002031200050	20020312	00050		2002	3	12	2002FA0000227    	4	20020129	G	2561	KA9P0101103	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST CELL FAILED.  MFG RECOMMENDED 2 PSI TEST IAW MANUAL.  DOM OCT 1981.																			 
2002031200051	20020312	00051		2002	3	12	2002FA0000228    	4	20020210	G	2561	KS9P0101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED THE MFG. RECOMMENDED 2 PSI CELL TEST IAW MANUAL. DOM APRIL 1982.																			 
2002031200054	20020312	00054	SO  	2002	3	12	2002FA0000230    	2	20020110	G	8520	630393	PUSHROD         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					LT ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	91284	3197 	1371 			347970111	306764			ON ANNUAL INSPECTION OF THE LT ENGINE (TOTAL TIME 3197.9) THREE PUSH RODS WERE NOTED TO BE CRACKED ALONG ALMOST THE ENTI	RE LENGTH OF THE PUSHRODS EXTENDING FROM THE VERY TOP.  PUSHRODS REPLACED WITH NEW AND 9 OVERHAULED.  BECAUSE OF THIS FI	NDING ALL 12 PUSHRODS ON RIGHT ENGINE WERE OVERHAULED.  CAUSE UNKNOWN.  RECOMMEND MORE FREQUENT INSPECTION OF PUSHRODS. 	 CRACK IN PUSHROD EXTENDING FULL LENGTH OF ROD.			1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002031200057	20020312	00057	SW  	2002	3	12	2002FA0000234    	1	20020108	G	5711	5147L	SPAR            			BBAVIA	7     	7AC         	2110102	SW  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	82027	3528 				7AC653				RIGHT REAR SPAR CRACKED ON TOP AT OUTBOARD END OF STRUT ATTACHMENT DUBBLER.  TIP OF SPAR HAS DUBBLER PLATES.  SPAR HAS B	EEN DAMAGED BEFORE.					1	H	7	1 	3O			 	A759    					 
2002031200072	20020312	00072	SW  	2002	3	12	2002FA0000249    	1	20020201	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A65*        	17003	SO  					LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	83280					1947				DURING INSPECTION OF AD INSPECTION.  FOUND LEFT WING FORWARD SPAR CRACKED AT UNDER SIDE OF SPAR OUT BOUND OF LIFT STRUT 	ATTACH POINT.  OWNER WAS CALLED TO INFORM HIM THIS WING WILL BE REPAIRED WITH NEW SPAR INSTALLED.					1	H	7	1 	3O	3	O	 	A759    	E205				 
2002031200077	20020312	00077	SW  	2002	3	12	2002FA0000254    	1	20020222	G	5711		SPAR            			BBAVIA	7     	7EC         	2110120	SW  	CONT  	C90   	C90*        	17009	SO  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	70824					337				DURING THIS ANNUAL INSPECTION FOUND COMPRESSION CRACKS ON THE RIGHT WING REAR SPAR AT TOP LOCATION ON TOP SIDE OF SPAR. 	 THIS COMPRESSION CRACK WAS HIDDEN UNDER OLD SPAR VARNISH AND WOULD HAVE BEEN MISSED IF TOP INSPECTION HOLES WERE NOT IN	STALLED ALSO MANY OTHER CRACKS WERE SPOTTED IN SAME AREAS.  BUT WERE NR 2 PENCIL LINES THE MFG USED TO LOCATE THE GLUE L	INES.			1	H	7	1 	3O	3	O	 	A759    	E252				 
2002031200081	20020312	00081	CE  	2002	3	12	2002FA0000257    	1	20020205	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	63791					BB1100				WINDOW SHATTERED DURING FLIGHT AT ALTITUDE.  REPLACED WITH NEW UNIT USING MFG SUPPLIED INSTALLATION KIT.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002031200083	20020312	00083	SO  	2002	3	12	2002FA0000259    	1	20020115	G	3222	74381	FITTING         			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					NLG	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	588GA	940  				588				AFTER GEAR EXTENSTION, CREW HAD A LOUD BANG, AND NOTICED LOSS OF LEFT HAND HYDRAULIC FLUID.  AFTER LANDING INSPECTION SH	OWED NOSE GEAR SWIVEL FITTING CRACKED AT FORGED SEAM.					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2002031200084	20020312	00084	SW  	2002	3	12	2002FA0000260    	1	20020201	G	5710		STRUT           			BBAVIA	7     	7CCM        	21101MW	SW  	CONT  	C90   	C90*        	17009	SO  					WING	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2762E					7AC6345				WING STRUTS HAD FILLED WITH WATER FROM SITTING OUTSIDE.  RUST STAINS VISIBLE FROM OUTSIDE OF STRUT.  WHEN POKED WITH AN 	AWL IT PUSHED A HOLE INTO STRUT AND DRAINED WATER.  DRILLED A .0312 HOLE IN BOTTOM OF OTHER 3 STRUTS AND WATER CAME OUT 	IN EXCESS OF 1 CUP EACH.  OWNER NOTIFIED OF UNAIRWORTHY CONDITION.				1	H	7	1 	3O	3	O	 	A759    	E252				 
2002031200085	20020312	00085	SW  	2002	3	12	2002FA0000261    	1	20020201	G	5711		SPAR            			BBAVIA	7     	7CCM        	21101MW	SW  	CONT  	C90   	C90*        	17009	SO  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2762E					7AC6345				CRACK ON BOTTOM SURFACE OF SPAR LEFT SIDE REAR.  FOUND PRIOR TO CRACK INSPECTION AS PER AD, OWNER DISCONTINUED ANNUAL IN	SPECTION PRIOR TO FULL INSPECTION.					1	H	7	1 	3O	3	O	 	A759    	E252				 
2002031200088	20020312	00088	SO  	2002	3	12	2002FA0000266    	1	20020205	G	5280		BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG DOOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	57PA					317305081				PILOT REPORTED NOSE WHEEL WOULD NOT LOCK (UP) AND RETURNED TO BASE WITHOUT ABNORMAL INDICATION.  MAINTENANCE INSPECTION 	REVEALED THAT THE BOLTS IN THE NOSE WHEEL RIGHT DOOR WERE WORN AND WERE REPLACED.  DOOR WAS STRAIGHTENED AND RERIGGED.  	RETRACTION AND OPS CHECKED OK.  FLOWN AND RELEASED FOR SERVICE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002031200090	20020312	00090	CE  	2002	3	12	2002FA0000268    	1	20020213	G	3240	66109	LINER           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					BRAKE CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	737ES					17269366				ON INSPECTION OF BRAKE LININGS AT A 100 HOUR INSPECTION,  THE RIGHT BRAKE LININGS WERE FOUND CRACKED.  UPON REMOVAL, THE	 THEY WERE FOUND LOOSE ON THE BRAKING PLATE.  LINING RIVETS WERE FOUND TO BE IMPROPERLY SWAGED AND APPEARED TO BE COMPRE	SSED WITH IMPROPER TOOLING.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002031200091	20020312	00091	SO  	2002	3	12	2002FA0000269    	2	20020216	G	8530	654441	VALVE SPRING    			CESSNA	188   	A188B       	2073005	CE  	CONT  	O240  	IO240A      	 	SO  					CYLINDER	FAILED          	D			TPMG	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	13	731LJ	910  				18802975T	812753R			DURING ANNUAL INSPECTION, PERFORMED A COMPRESSION CHECK ON ALL ENGINE CYLINDERS.  TWO CYLINDERS FAILED THE CHECK LEAKING	 BY THE VALVES.  REMOVED CYLINDERS, DISASSEMBLED.  CHECKED VALVE SPRINGS INNER AND OUTER TENSION PER CONT OVERHAUL MANUA	L USING A VALVE SPRING TESTER AND FOUND THAT THE INNER AND OUTER VALVE SPRINGS FAILED.  TOTAL TIME ON THESE SPRINGS 910 	SINCE NEW.  REPLACED INNER AND OUTER VALVE SPRINGS WITH NEW SPRINGS AFTER CHECKING SPRING TENSIONS.			1	L	7	1 	3O	3	O	 	A9CE    	E7SO				 
2002031200092	20020312	00092	WP  	2002	3	12	2002FA0000270    	2	20020118	G	7250	30606901	BLADE           								GARRTT	TFE731	TFE7315R    	01518	WP  					TURBINE SECTION	DAMAGED         	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19		1842 	1196 				P91152			3RD LPT BLADE SEPARATED AT MID-SPAN CAUSING DAMAGE BEYOND LIMITS TO 7EA 3RD LPT BLADES.  ALSO DAMAGED THE EXHAUST NOZZLE	 AND 3RD LPT NOZZLE BEYOND LIMITS.										4	F			E6WE				 
2002031200093	20020312	00093	CE  	2002	3	12	2002FA0000272    	1	20020218	G	8120		CROSSOVER TUBE  			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					TURBOCHARGER	BROKEN          	B			YEBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	7254T	315  				CE1065	813757R			DURING AN ANNUAL INSPECTION, THE TURBOCHARGER CROSSOVER TUBE WAS FOUND DAMAGED FROM THE AIRCRAFT DRIVE PULLEY.  THIS AIR	CRAFT HAS BEEN MODIFIED BY TURBO FLITE STC SA5223NM AND SE5222NM.  UPON REMOVAL OF THE TUBE A HOLE WAS DISCOVERED BELOW 	THE DAMAGED AREA THAT WAS APPARENTLY CAUSED FROM THE INSTALLER DEFORMING THE TUBE TO GAIN CLEARANCE FOR THE DRIVE PULLEY	.  AFTER ORDERING A REPLACEMENT PART FROM THE MANUFACTURER, I WAS INSTRUCTED TO DEFORM THE TUBE TO GAIN CLEARANCE BETWEE	N THE REPLACEMENT TUBE AND AIRCRAFT DRIVE PULLEY.  THIS ACTION IS LIKELY TO CAUSE THE TUBE TO FAIL AS MENTIONED ABOVE.		1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002031200094	20020312	00094	SO  	2002	3	12	2002FA0000273    	1	20020214	G	2700	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										FWD STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4144K	2480 				2843145				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT A	ND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION.  THE WORN AND FRAYED PARTS OF THE  CABLES WERE FOUND AT P	ULLEYS, FAIR LEADS OR ANYPLACE THE CABLES CAME IN CONTACT WITH.  PROBABLE CAUSE:  SUBSTANDARD CABLE.				1	L	7	1 	3O			 	2A13    					 
2002031200095	20020312	00095	SO  	2002	3	12	2002FA0000274    	1	20020214	G	2700	62701114	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4144K	2480 				2843145				DURING A ROUTNE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT AN	D LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION.  THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PUL	LEYS, FAIR LEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.				1	L	7	1 	3O			 	2A13    					 
2002031200096	20020312	00096	SO  	2002	3	12	2002FA0000275    	1	20020214	G	2700	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4144K	2480 				2843145				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT A	ND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMULAR CONDITION.  THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PU	LLEYS, FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.  PROBABLE CAUSE: SUBSTANDARD CABLE.				1	L	7	1 	3O			 	2A13    					 
2002031200097	20020312	00097	SO  	2002	3	12	2002FA0000277    	1	20020220	G	2701	D31	SPROCKET        			MAULE 	M6    	M6235       	5460160	SO  										CONTROL YOKE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	9219Y	872  				7514C				LEFT AILERON CONTROL SPROCKETS STOP PIN WAS FOUND BROKEN OFF.  THIS ALLOWED BALANCE WEIGHTS TO HIT UPPER WING SKIN AND A	ILERON TRAVEL TO 60 BEYOND RECOMMEND UP/DOWN MOVEMENT.  SUSPECT PIN WAS BROKEN OFF WITH AIRCRAFT OUTSIDE IN WINDY CONDIT	IONS WITH NO GUST LOCK INSTALLED.				1	H	7	1 	3O			 	3A23    					 
2002031200098	20020312	00098	CE  	2002	3	12	2002FA0000278    	1	20020202	G	2800	25765362	SERVO           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	MALFUNCTIONED   	B			AP1R	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	11	2317U					17280695	L2802451A			REPORTED ENGINE LOST POWER TWICE (ENG RUNNING 1 HOUR).						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002031300001	20020313	00001	CE  	2002	3	13	2002FA0000279    	1	20020214	G	8000	S1577A1	CONTACTOR       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					STARTER	STUCK           	B			LV0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	89087	47   				15282625				STARTER ENGAGED UPON CLOSING AIRCRAFT MASTER SWITCH.  FOUND S1577A1 CONTACTOR IN THE STUCK CLOSED POSITION, WITH NO ELEC	TRICAL POWER APPLIED.  REPLACED CONTACTOR.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002031300002	20020313	00002	EA  	2002	3	13	2002FA0000282    	2	20020214	G	7414	10357584	GEAR            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					RT MAGNETO	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	9614J	1684 				283767				RT MAGNETO WAS INTERMITTENT, AND FINALLY FAILED.  DISTRIBUTOR GEAR ALMOST HALF OF THE TEETH WERE MISSING.  NO RELATED PR	OBLEMS WITH MAGNETO OR VISIBLE CAUSE.  POSSIBLY DAMAGED AT SAME PREVIOUS INSTALLATION.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002031300003	20020313	00003		2002	3	13	2002FA0000283    	4	20020218	G	3416	AR850	ENCODER         			PIPER 	PA28  	PA28181     	7102807	SO  										COCKPIT	LEAKING         	B			LV0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4143A					2843217				UPON CERTIFYING STATIC SYSTEM THAT THE ENCODER HAD AN INTERNAL LEAK, ENCODER WAS REPLACED WITH NEW.						1	L	7	1 	3O			 	2A13    					 
2002031300004	20020313	00004	SO  	2002	3	13	2002FA0000284    	1	20020218	G	3710	842CW	PUMP            			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIO541E1A4  	41536	EA  					VACUUM SYSTEM	SEIZED          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	648SC					31P7300143	L55562			BOTH PUMPS FAILED WITHIN 30 MINUTES OF EACH OTHER.  BOTH LOW TEMPERATURE PUMPS OVERLOADED.						1	L	7	2 	3O	3	O	 	A8EA    	E10EA				 
2002031300005	20020313	00005	SO  	2002	3	13	2002FA0000285    	1	20020219	G	2700	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145X	2536 				2843152				DURING A ROUTINE INSPECTION THE RT AND LT FORWARD STABILATOR CABLES WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT AND L	EFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION.  THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEY	S FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002031300006	20020313	00006	SO  	2002	3	13	2002FA0000286    	1	20020219	G	2700	62701114	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145X	2536 				2843152				DURING A ROUTINE INSPECTION THE RT AND LT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT AND LE	FT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION.  THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS	 FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.  PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MA	NUFACTURER.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002031300007	20020313	00007	SO  	2002	3	13	2002FA0000289    	1	20020215	G	2700	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STAILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4164Y	1258 				2843317				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN FRAYED.  THE AILERON RIGHT AND L	EFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION.  THE WORN ANDFRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS	 FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.				1	L	7	1 	3O			 	2A13    					 
2002031300008	20020313	00008	CE  	2002	3	13	2002FA0000293    	1	20020226	G	8120	63272913	TURBOCHARGER    			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	LEAKING         	B			EKGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	234PT	56   				EA662	527458			TURBOCHARGER WAS FOUND TO BE LEAKING OIL INTO INDUCTION SYSTEM.  CHECKED SYSTEMS AS PER MFG AND MM.  THIS IS NR 1 OF SEV	ERAL REPLACED ON THIS ENGINE.					1	L	7	1 	3O	3	O	 	3A15    	E8CE				 
2002031300010	20020313	00010	CE  	2002	3	13	2002FA0000295    	1	20020122	G	5751	0322709	BRACKET         			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	R7559       	35003	EA  					AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195DH					7588				INBOARD AILERON HINGE BRACKET, THESE MAGNESIUM BRACKETS WERE SEVERELY CORRODED AND CRACKED UNDER THE PAINT AND COULD ONL	Y BE SEEN AFTER BEAD BLASTING.  THESE BRACKETS ARE THE ATTACH FOR THE AILERONS AND ARE CRACKING  COMPLETELY ACROSS THE R	ETAINING BOSS FOR THE BEARING.  SUGGEST PAINT REMOVAL AND INSPECTION OF BRACKET OR REPLACE WITH STC`S ALUMINUM BRACKETS.	  APPROXIMATELY 80 PERCENT OF THE ORIGINAL BRACKETS WE HAVE INSPECTED HAVE BEEN SEVERELY CORRODED/ CRACKED.			1	H	7	1 	3R	3	R	 	A790    	TC121				 
2002031300011	20020313	00011	CE  	2002	3	13	2002FA0000296    	1	20020122	G	5751	03227091	BRACKET         			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	R7559       	35003	EA  					AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195DH					7588				INBOARD AILERON HINGE BRACKET, THESE MAGNESIUM BRACKETS WERE SEVERLY CORRODED AND CRACKED UNDER THE PAINT AND COULD ONLY	 BE SEEN AFTER BEAD BLASTING.  THESES BRACKETS ARE THE ATTACH FOR THE AILERONS AND ARE CRACKING COMPLETELY ACROSS THE RE	TAINING BOSS FRO THE BEARING.  SUGGEST PAINT REMOVAL AND INSPECTION OF BRACKET OR REPLACE WITH STC`S ALUMINUM BRACKETS. 	 THE ORIGINAL BRACKETS, WE HAVE INSPECTED, HAVE BEEN SEVERELY CORRODED/ CRACKED.			1	H	7	1 	3R	3	R	 	A790    	TC121				 
2002031300012	20020313	00012	SO  	2002	3	13	2002FA0000297    	1	20020225	G	2910	1776604	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					HYD SYSTEM	DAMAGED         	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	11	4106F	6363 				318252034				HOSE ASSEMBLY FAILED AFTER TAKE-OFF AND NOSE GEAR WOULD NOT RETRACT.  PILOT TRIED TO HAND PUMP THE MANUAL HYDRAULIC PUMP	 WITH SO SUCCESS.  INSPECTION NOTED LINE BLEW A HOLE BELOW THE TSO TAG AREA.  IT IS RECOMMENDED THAT ON ANNUAL INSPECT B	OTH ACTUATOR HOSE ASSEMBLY SHOULD BE INSPECTED BELOW THE TSO TAG AND SPIRAL WRAP FOR DAMAGE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002031300015	20020313	00015		2002	3	13	2002FA0000300    	4	20020204	G	6113	C5046	PLATE           			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C218   	GL  	PROP SPINNER	CRACKED         	B			OF1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	4770T	750  				R18201758	L2392340A	993189		DURING A 50 HOUR INSPECTION THE SPINNER ASSEMBLY WAS DETECTED TO BE VERY LOOSE ON THE PROP.  UPON FURTHER EXAMINATION BO	TH SPINNER ATTACH PLATES WERE FOUND CRACKED ALL THE WAY AROUND FOUR OF SIX PROP ATTACH BOLT HOLES.  CRACKS EMANATED FROM	 THE CORNER OF EACH BOLT HEAD AND WENT IN EACH DIRECTION ALL THE WAY TO THE EDGE OF THE ATTACH PLATES (3 CRACKS ON ONE P	LATE AND ONE ON THE OTHER).  AFTER CHECKING THE PARTS CATALOG IT WAS DETERMINED THAT THE SIX WASHERS REQUIRED FOR THE AT	TACH BOLTS HAD BEEN OMITTED DURING THE PROPELLER ASSEMBLY.  DURING REPAIR OF AC, INSTALLED THE SIX WASHERS REQUIRED BY T	HE MFG CATALOG.  BELIEVE IT WILL PREVENT FUTURE REOCCURRENCE.	1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2002031300016	20020313	00016	CE  	2002	3	13	2002FA0000303    	1	20020207	G	8120	63272913	TURBOCHARGER    			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	LEAKING         	B			EKGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	234PT	21   				EA662	527458			TURBOCHARGER LEAKING OIL IN INDUCTION.  THIS UNIT WAS REMOVED AND RETURNED DIRECTLY TO MFG FOR INVESTIGATION.  THIS IS N	R 3 FOR THIS ENGINE.  NO WORD FROM MFG ON CAUSE OF PROBLEM.  ENGINE IS TO BE REPLACED BY MFG.					1	L	7	1 	3O	3	O	 	3A15    	E8CE				 
2002031100110	20020311	00110	EU  	2002	3	11	2002FA0000306    	1	20020117	G	2435	M20014	BRUSHES         			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					STARTER GEN	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	255SD	300  			1618XL	1102	34117			DEFECT FOUND DURING SCHEDULED MAINTENANCE, 100 HOUR INSPECTION.  STARTER GENERATOR HAD PRIOR OVERHAUL AND MODIFICATION T	O (XL) CONFIGURATION.  FOUND 4 BRUSHES WORN LIMIT, 4 WITH UNDER 10 HOURS APPROXIMATE TIME LEFT.  STARTER REPAIRED, NEW B	RUSHES INSTALLED.  POSSIBLE WRONG OR TOO SOFT CARBON COMPOUND.				1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2002031300018	20020313	00018	CE  	2002	3	13	2002FA0000307    	1	20020304	G	5610	511604202	WINDSHIELD      			CESSNA	421   	421B        	2076014	CE  	CONT  	O360  	TSIO360*    	17025	SO  					COCKPIT	DEPARTED        	D				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	01	421LP					421B0323				AT APPROXIMATELY 17,000 FEET CO-PILOTS WINDSHIELD DEPARTED AIRCRAFT, RECOMMEND LARASCOPE INSPECTION OF WINDSHIELD HOLES.	  TOTAL TIME ON PART 6,234.9.					1	L	7	2 	3O	3	O	 	A7CE    	E9CE				 
2002031100111	20020311	00111	WP  	2002	3	11	2002FA0000308    	1	20020209	G	3246	369A795149	BEARING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					MLG	INOPERATIVE     	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				FOUND LEFT FRONT MAIN LANDING GEAR KEEL BEARING AND RETAINER BACKED OUT OF KEEL FITTING.  IT IS NORMALLY RETAINED WITH A	 CIRCLIP BUT IT WAS NOT ENGAGED BUT IT WAS CAPTURED BY THE BOLT.  THE LIMIT OF REMOVAL WAS DEFINED BY THE FORK ON THE EN	D OF THE LANDING GEAR LEG.  THE ID OF THE BORE IN THE KEEL FITTING WAS WITHIN LIMITS AND A NEW RETAINER AND BEARING WERE	 INSTALLED WITH A NEW CIRCUP.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002031100112	20020311	00112	WP  	2002	3	11	2002FA0000309    	1	20020212	G	3210	369HG20073	GUIDE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					MLG	BROKEN          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING 100/300 ROUTINE INSPECTION THE GUIDE TUBE FOR THE SPRING LOADED FILLETS WERE FOUND BROKEN ON (3) THREE LANDING GE	AR.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002031300019	20020313	00019	SO  	2002	3	13	2002FA0000310    	1	20020222	G	3110	587837	MASTER SWITCH   			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					COCKPIT	BROKEN          	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3054K					347970102	307788			THE MASTER SWITCH IS DIVIDED INTO TWO SWITCHES A THAT ARE COUPLED TOGETHER WITH A PLASTIC TAB.  THE HALF OF THE SWITCH T	HAT CONTROLS THE ALTERNATOR FIELDS IS HIDDEN UNDER THE SIDE PANEL.  WHEN THE TAB THAT COUPLES THE TWO TOGETHER BROKE, TH	E ALTERNATORS DROPPED OFF LINE.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002031100161	20020311	00161	SO  	2002	3	11	2002FA0000311    	1	20020311	G	2700		COTTER PIN      			PIPER 	PA28  	PA28161     	7102803	SO  										BRAKE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11						2842096				DURING ROUTINE CABIN INSPECTION THE COTTER PIN THAT CONNECTS THE PILOT RT PEDAL AND THE TOE BRAKE CLEVIS TO THE BRAKE MA	STER CYLINDER WAS FOUND MISSING AT THE TOP OF THE ASSEMBLY.  UPON FURTHER INSPECTION THE WASHER WAS ALSO MISSING AND THE	 PIN WAS BACKING OUT.  THE COTTER PIN WAS DISCOVERED ON THE FLOOR ALONG WITH THE WASHER, THE CONDITION OF THE COTTER PIN	 WAS WORN SUGGESTING THAT THE PILOTS FEET HAD COME INTO CONTACT WITH THE COTTER PIN REPETIVATILY CAUSING THE PIN TO FAIL	 AND BACK OUT.  THE FLAT HEAD PIN WAS REINSTALLED TOWARD THE CENTER OF THE CABIN, PREVENTING FEET FROM COMING IN CONTACT	 WITH THE COTTER PIN, AND THE COTTER PIN WAS REPLACED WITH THE WASHER.  SUBMITTER SUGGESTS THAT PA28-161 WARRIOR III'S B	1	L	7	1 	3O			 	2A13    					 
2002031100162	20020311	00162	SO  	2002	3	11	2002FA0000312    	1	20020311	G	2720		COTTER PIN      			PIPER 	PA28  	PA28161     	7102803	SO  										PEDAL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11						2842098				DURING ROUTINE CABIN INSPECTION IT WAS DISCOVERED THAT THE COTTER PIN WHICH HOLDS THE PILOTS RIGHT PEDAL AND CLEVIS ASSE	MBLY TO THE BRAKE CYLINDER WAS DAMAGED AND BACKING OUT.  THE DAMAGE WAS APPENTLY CAUSED BY THE PILOTS RIGHT FOOT COMING 	IN CONTACT WITH THE COTTER PIN AND RUBBING IT.  SUBMITTER SUGESTS INSTALLING THE FLAT HEAD PIN SO THAT THE COTTER PIN WI	LL BE TO THE CENTER OF THE AIRCRAFT AND FEET WILL NO LONGER COME INTO CONTACT WITH IT.			1	L	7	1 	3O			 	2A13    					 
2002031100164	20020311	00164	SO  	2002	3	11	2002FA0000315    	1	20020225	G	7160	8624534	AIR BOX         			PIPER 	PA44  	PA44180     	7104402	SO  										ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	7707B	122  	60   			4496090				THE CARBURETOR AIR BOX AIR INLET TUBE BROKE OFF. THE WELD ON THE INSIDE OF THE BOX HAD BEEN GROUND OFF AT THE FACTORY. T	HE BOX ASSY NR  WAS 86245-34 AND THE PART THAT BROKE OFF HAD A NR  OF 86245-035.					1	L	7	2 	3O			 	A19S0   					 
2002031100165	20020311	00165	CE  	2002	3	11	2002FA0000316    	1	20020208	G	3240	5100106159	LINE            			CESSNA	414   	414A        	2075907	CE  										BRAKE SYSTEM	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	11	27340					414A0462				DURING MAXIMUM POWER MAINTENANCE GROUND RUNUP AFTER ROUTINE OIL CHANGE, THE RIGHT BRAKE FAILED. QUICK ACTION BY THE MECH	ANIC RUNNING THE AIRCRAFT AVOIDED A POTENTIAL ACCIDENT. FOUND BRAKE LINE UNDER COPILOTS FLOORBOARD TO HAVE A HOLE CORROD	ED IN IT. THIS ALUMINUM TUBE RUNS BELOW A SECTION OF STEEL WIRE SUPPORTED SCAT HOSE. SUSPECT THAT THE CONTACT WAS MADE B	ETWEEN THE TUBE AND HOSE CAUSING CORROSION. AREA WHERE DAMAGE OCCURED IS NOT VISUALLY ACCESSABLE, EXCEPT BY BORESCOPE. R	EPLACED TUBE & MADE SURE NO FURTHER CONTACT IS MADE BETWEEN THE HOSE & TUBE. SUBMITTED BY: JOHN D. TOBIN A&P 2250313 EPP	S AIR SERVICE INC.	1	L	7	2 	3O			 	A7CE    					 
2002031100168	20020311	00168	EA  	2002	3	11	2002FA0000317    	2	20020225	G	8520		BEARING         			MOONEY	M20   	M20M        	5870222	SW  	LYC   	0540  	TIO540AF1B  	41532	EA  	MCAULY	3D32C	B3D32C417   	GL  	ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	355RZ	399  								DURING A REGULER OIL CHANGE INTERVAL. METAL CONTAMINATS WER NOTED IN THE FOLDS OF THE OIL FILTER. THEY APPEARED TO BE OF	 ALUMINUM. FURTHER INVESTIGATION INTO THE PICK UP SCREEN FOUND A LARGER AMOUNT OF DEBRIS. SIZE OF THE DEBRIS APPEARED TO	 BE AROUND 1/16 OF AN INCH IN SIZE. IN ACCORDANCE WITH TEXTRON LYCOMING SERVICE INSTRUCTION THE AIRCRAFT WAS GROUNDED. S	AMPLEL FROM BOTH THE FILTER AND PICK UP SCREEN WERE PACKAGED SEPERATLY AND SENT TO TEXTRON LYCOMING IN THE SAME PACKAGE 	BUT SEPERATED. TEXTRON CALLED BACK AND SAID THE CONTENS OF THE SAMPLE WERE BEARING MATERIAL. AT THE SAME TIME AS THE OIL	 WAS DRAINED FROM THE ENGINE, A SAMPLE WAS TAKEN FOR ANALYSIS. THE OIL SAMPLE WAS SHIPPED TO AOA. THE OIL ANALYSIS CAME 	1	L	7	1 	3O	3	O	RT	2A3     	E14EA	5	C	P58GL	 
2002031300020	20020313	00020	CE  	2002	3	13	2002FA0000318    	1	20020208	G	3240	5100106159	LINE            			CESSNA	414   	414A        	2075907	CE  										BRAKE SYSTEM	CORRODED        	D				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	11	27340					414A0462				DURING MAXIMUM POWER RUNUP, AFTER ROUTINE OIL CHANGE, THE RIGHT BRAKE FAILED. QUICK ACTION BY THE MECHANIC RUNNING THE A	IRCRAFT AVOIDED A POTENTIAL ACCIDENT. FOUND BRAKE LINE UNDER COPILOTS FLOORBOARD TO HAVE A HOLE CORRODED IN IT. THIS ALU	MINUM TUBE RUNS BELOW A SECTION OF STEEL WIRE SUPPORTED SCAT HOSE. SUSPECT THAT THE CONTACT WAS MADE BETWEEN THE TUBE AN	D HOSE CAUSING CORROSION. AREA WHERE DAMAGE OCCURED IS NOT VISUALLY ACCESSABLE, EXCEPT BY BORESCOPE. REPLACED TUBE & MAD	E SURE NO FURTHER CONTACT IS MADE BETWEEN THE HOSE & TUBE.		1	L	7	2 	3O			 	A7CE    					 
2002031300021	20020313	00021	CE  	2002	3	13	2002FA0000320    	1	20020226	G	3397	TTGCTA201TWB	SWITCH          			CESSNA	172   	172N        	2072434	CE  										INSTRUMENT PANEL	FAILED          	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			WP	07	739LD					17270620				DURING LANDING APPROACH SMOKE WAS DETECTED IN THE COCKPIT COMING FROM THE LOWER PILOT SIDE INSTRUMENT PANEL FROM THE LAN	DING / TAXI LIGHT COMBINATION SWITCH.  THIS IS AN ONGOING PROBLEM WITH THESE SWITCHES.					1	H	7	1 	3O			NT	3A12    					 
2002031300022	20020313	00022	SO  	2002	3	13	2002FA0000323    	1	20020227	G	5753	6559100	STRUCTURE       			PIPER 	PA28  	PA28R180    	7102809	SO  										RT WING FLAPS	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	953CA					28R30214				CORROSION INSIDE FLAPS.  CORROSION SEEMS TO BE AGGRAVATED WHERE THE ALUMINUM RIBS BUTT UP AND ARE RIVETED TO THE FLAP ST	EEL MATERIAL HINGES.					1	L	7	1 	3O			 	2A13    					 
2002031300033	20020313	00033	CE  	2002	3	13	2002FA0000324    	1	20020228	G	2842	C6680500802	TRANSMITTER     			CESSNA	172   	172P        	2072436	CE  										FUEL QUANTITY	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	6601K	2941 				17274218				FUEL QUANTITY TRANSMITTER REMOVED TO REPLACE LEAKING BASE GASKET.  FOUND COMPOSITE FLOAT ON TRANSMITTER ARM WAS DETERIOR	ATED DUE TO CONTACT WITH THE TOP OF FUEL TANK WHEN FULL.  APPROXIMATELY 1/4 INCH OF FLOAT DETERIORATED ON ONE CORNER.  S	UBSEQUENTLY FOUND FINE BLACK RESIDUE IN FUEL STRAINER.  TRANSMITTER WAS INSTALLED PROPERLY AND NO ADJUSTMENT PROVISIONS 	ALLOWED.			1	H	7	1 	3O			NT	3A12    					 
2002031300036	20020313	00036	GL  	2002	3	13	2002FA0000325    	3	20020225	G	6110	1A105SCM7153	PROPELLER       			AMRGEN	AA1   	AA1         	0630610	SO  	LYC   	O235  	O235C       	41505	EA  	MCAULY	1A105	1A105SCM    	GL  	NOSE	SEPARATED       	G				A				UNSCHED LANDING         				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CR	CRUISE         	1			EA	21	5999L	2642 	142  			AA10299		G7005		WHILE CRUISING AT 5000 FEET THE PILOT REPORTED SEVERE VIBRATION. AFTER PERFORMING AN UNEVENTFUL LANDING AND ENGINE SHUT 	DOWN, THE PILOT OBSERVED THAT APPROXIMATELY 4 INCH INCHES OF ONE BLADE TIP WAS MISSING.  FURTHER INVESTIGATION REVEALED 	THAT A SMALL STONE HAD LEFT A SMALL NICK IN THE LEADING EDGE OF THE PROPELLER BLADE WHICH IS WHERE THE TIP SEPPARATED FR	OM THE REST OF THE BLADE.			1	L	7	1 	3O	3	O	 	A11EA   	E223	5	N	P918	 
2002031300037	20020313	00037	SO  	2002	3	13	2002FA0000326    	2	20020226	G	8530	CN635448FC	CYLINDER        			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  					RT ENGINE	BROKEN          	B				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			SO	11	986CB		1401 			3400328	R21752771K			PILOT REPORTED PARTIAL LOSS OF POWER AND VIBRATION FROM RIGHT ENGINE ON CLIMB-OUT.  UPON INSPECTION FOUND RIGHT ENGINE N	R 2 CYINDER HEAD BROKEN IN THE AREA OF THE FOURTH AND FIFTH COOLING FINS.  HEAD WAS COMPLETELY SEPARATED FROM THE BARREL	 AND WAS HELD IN PLACE ONLY BY THE ENGINE COOLING BAFFLES.				1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2002031200001	20020312	00001	CE  	2002	3	12	2002FA0000327    	1	20020306	G	3500	120041787	LINE            			CESSNA	206   	T206H       	2073303	CE  										OXYGEN SYS	DAMAGED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	2647U	148  				T20608105				OXYGEN LINE WAS PERFORATED BY AN UPHOLSTERY TRIM SCRE.  DURING THE PROCESS OF A ROUTINE ANNUAL INSPECTION, THE LEFT SIDE	 TRIM PANES WAS REMOVED AND THE HOLE WAS DISCOVERED.  THE LINE SHOULD HAVE BEEN RUN LOWER AND TIED TO A GLUED ON SKIN AT	TACH POINT, BUT WAS NOT, PRESUMABLE FROM THE FACTORY SINCE THIS PANEL HAD MOST LIKELY NOT PREVIOUSLY BEEN REMOVED.				1	H	7	1 	3O			RT	A4CE    					 
2002031200002	20020312	00002	CE  	2002	3	12	2002FA0000328    	1	20020307	G	2822		PUMP            			BEECH 	35    	V35         	1151538	CE  										FUEL BOOST	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05										FUEL PUMP WOULD NOT PRODUCE FUEL FLOW OR PRESSURE. ENGINE WOULD NOT IDLE BELOW 1000 RPM AND WOULD NOT PRODUCE POWER.						1	L	7	1 	3O			 	3A15    					 
2002031300038	20020313	00038	NE  	2002	3	13	2002FA0000329    	2	20020215	G	7310	3037088	LINE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					FUEL BYPASS	LEAKING         	B			PB8R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	15	999AD					5600136				LT ENGINE HAD A FUEL LEAK.  FOUND FUEL BYPASS TUBE LEAKING.  LEAK AT SOLDIER JOINT, CRACK OR OTHER DEFECT.  INSTALLED NE	W TUBE.					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2002031300039	20020313	00039	CE  	2002	3	13	2002FA0000330    	1	20020220	G	2720	100600012	BELLCRANK       			BEECH 	100   	B100        	1152919	CE  										RUDDER	CORRODED        	B			QRXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	568K	6662 				BE106				REMOVED RUDDER FROM AIRCRAFT FOR OTHER MAINTENANCE.  DISCOVERED RUDDER BELLCRANK SEVERELY CORRODED IN THE AREA BENEATH T	HE RUDDER ATTACH FITTING.  REPLACED PART WITH NEW ITEM.					1	L	7	2 	4T			 	A14CE   					 
2002031300040	20020313	00040	CE  	2002	3	13	2002FA0000331    	1	20020207	G	1400		NUT             			CESSNA	210   	210D        	2073414	CE  	CONT  	O520  	IO520*      	17032	SO  					ELT ANTENNA	LOOSE           	B			W1NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	375HW	157  				21058251				THE ELT ANTENNA WAS FOUND TO BE LOOSE ON VISUAL INSPECTION.  REMOVED ELT ANTENNA ASSEMBLY,  FOR PROGRESSIVE INSPECTION. 	 FOUND SHIELD LOCKING NUT SECURING METAL RADIATING ROD TO ANTENNA BASE ASSEMBLY WAS LOOSE.  WHEN RADIATING ROD WAS REMOV	ED FROM ANTENNA BASE ASSEMBLY, THE FEMALE BNC BARREL CONNECTOR SOLDIER JOINT WAS BROKEN.  THE SECURING OF THE 24 INCH RA	DIATING ROD IS ACCOMPLISHED ONLY BY MEANS OF AN INSULATING PLASTIC HOUSING AT THE ANTENNA BASE IN A COMPRESSION NUT.  TH	E FEMALE BNC BARREL SHOULD HAVE BEEN CRIMPED.		1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2002031300041	20020313	00041	CE  	2002	3	13	2002FA0000332    	1	20020207	G	3710	442CW12	PUMP            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					VACUUM SYS	INOPERATIVE     	B			ODAR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	21	58WC					TH766				PILOT EXPERIENCED DUAL VACUUM PUMP FAILURE IN FLIGHT IN VFR CONDITIONS.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002031300042	20020313	00042	CE  	2002	3	13	2002FA0000333    	1	20020207	G	3700	442CW12	PUMP            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					VACUUM PUMP	INOPERATIVE     	B			ODAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	58WC					TH766				PILOT EXPERIENCED DUAL VACUUM PUMP FAILURE IN FLIGHT IN VFR CONDITIONS.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002031300062	20020313	00062	SO  	2002	3	13	2002FA0000334    	1	20020110	G	2140	A23D0475	SHUTOFF VALVE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUEL REGULATOR	LEAKING         	B			DQIR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	07	4089Y	4    				318152101				CREW REPORTED FUEL PRESSURE FOR RIGHT ENGINE WOULD DROP INTERMITTENTLY, THE HEATER FUEL SUPPLY COMES FROM FUEL FOR RIGHT	 ENGINE.  TURNED HEATER ON, AND FUEL LEAKED FROM FUEL REGULATOR/SHUTOFF VALVE.  THIS WAS A NEW VALVE THAT REPLACED A NEW	 VALVE PER THE REQUIREMENTS OF AD.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002031300118	20020313	00118	CE  	2002	3	13	2002FA0000335    	1	20020308	G	1420	A60088	AMMETER         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	MCAULY	4HFR34	4HFR34C660  	NE  	INST PANEL	BLEW OUT        	G				H				DEACTIVATE SYST/CIRCUITS				P			NO WARNING INDICATION     			CR	CRUISE         	1			WP	17	442HA	960  				4410243				N442HA A CESSNA 441 WAS DECENDING THROUGH APPROX. 12000 FT WHEN THE PROPELLER DE-ICE AMP METER EXPLODED SENDING BROKEN G	LASS INTO THE PILOT FACE JUST MISSING HIS EYES. PRIOR TO THE FAILURE THE PILOT HAD SELECTED THE PROPELLER DE-ICE SYSTEM 	TO THE ON POSITION. TO CYCLE THE SYSTEM PRIOR TO LANDING. THE PILOT SHUT DOWN THE PROPELLER DE-ICE SYSTEM FOLLOWING THIS	 INCIDENT.  THE CIRCUIT PROTECTOR DID NOT OPEN WITH THIS FAILURE.  THE GAGE WAS REMOVED AND INSPECTED THE SHUNT LOCATED 	IN THE BACK OF THE GAGE HAD BURNED AND MELTED OPENING THE CIRCUIT.		1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	5	C	3PNE	 
2002031300119	20020313	00119		2002	3	13	2002FA0000336    	4	20020305	G	2330		CONNECTOR       			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6*        	52043	EA  					WIRE HARNESS	LOOSE           	B			G1KR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	703QD					129				OPERATOR REPORTED INTERMITTENT DME AND HEADPHONE JACK PROBLEMS.  UPON TROUBLESHOOTING, TECHNICIAN DISCOVERED 21 LOOSE CO	NNECTORS ON THE SYMBOL GENERATOR DUE TO BAD CRIMPING TECHNIQUES.  WIRING WAS REPAIRED AND OPERATIONAL CHECKED OK.					1	L	7	1 	3T	3	T	RT	A60EU   	E2NE				 
2002031300120	20020313	00120	CE  	2002	3	13	2002FA0000337    	1	20020304	G	3240	9638003425	MASTER CYLINDER 			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					BRAKE SYS	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8242T					CE1610	820462R			BRAKE MASTER CYLINDER WILL NOT HOLD PRESSURE, WHEN PRESSURE IS APPLIED TO THE BRAKE IT BLEEDS DOWN.  REMOVED AND INSTALL	ED NEW MASTER CYLINDER, OPERATION CHECKED NORMAL.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002031400003	20020314	00003	NE  	2002	3	14	2002FA0000341    	2	20020226	G	7314	025323150	PUMP            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					FUEL SYSTEM	SHEARED         	D				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	11	121HA					208B0069				ENGINE FAILED IN FLIGHT DUE TO SHEARED FUEL PUMP DRIVE, AIRCRAFT LANDED SAFELY IN FARMERS FIELD.  NO AIRCRAFT DAMAGE.  S	UGGEST MANDATORY DRIVE REPLACEMENT AT EACH OVERHAUL.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2002031400004	20020314	00004	SW  	2002	3	14	2002FA0000342    	1	20020219	G	3232	4196001C	ACTUATOR        			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	17	79830					494				AC MADE GEAR UP LANDING DUE TO FAILURE OF GEAR TO EXTEND EITHER ELEC OR MAN.  FAILURE TO OPERATE ELEC WAS NOT DETERMINED	 BUT PROBABLY IN AC GEAR CONTROL SYS.  FAILURE TO EXTEND WITH MAN SYS (EMERGENCY) WAS CAUSED BY A STRIPPED GEAR IN MAN D	ISENGAGE ASSY MOUNTED ON THE GEAR ACT.  WHEN ENGAGEING MAN SYS A LEVER IS MOVED AT DISENGAGE UNIT TO SLIDE FEMALE SPLINE	D GEAR ONTO SPLINED MALE END OF EXTEN CABLE ALLOWING GEAR TO BE EXTENDED WITH HAND CRANK.  ENGAGE LEVER IN CABIN OR LEVE	R ON DISENGAGE ASSY WAS LOOSE IT WOULD ALLOW FEMALE GEAR TO PARTIALLY ENGAGE CABLE AND DURING ELEC OP FEMALE GEAR WOULD 	GRIND AGAINST END OF EXTEN CABLE TO POINT THERE WOULDN`T BE ENOUGH TEETH LEFT FOR EMER SYS TO OP.	1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2002031400002	20020314	00002	SO  	2002	3	14	2002FA0000343    	1	20020313	G	7910		SUMP            			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE OIL	CRACKED         	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	137JT	1300 				4622151	L946761A			OIL SUMP CRACKED AT TURBOCHARGER MOUNTING BRACKET ATTACHMENT POINT.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2002032700093	20020327	00093	CE  	2002	3	27	2002FA0000346    	1	20020226	G	5712	082217569	RIB             			CESSNA	310   	310P        	2074238	CE  	CONT  	O470  	IO470*      	17026	SO  					LT WING	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	310GR	8825 				310P0064				NR 8 RIB, LT WING SIDE BRACE LOCATION HAD CRACK THAT PROPAGATED THE FULL UPPER AREA OF THE SIDE BRACE.  THE FORWARD ATTA	CH BOLT WAS MISSING AND EVIDENCE OF SPINNING ON THE SURFACE OF THE RIB.  AFT BOLT WAS HELD BY 2 THREADS.  INSPECTED AREA	 AT ANNUAL.				1	L	7	2 	3O	3	O	 	3A10    	E1CE				 
2002032700095	20020327	00095	SO  	2002	3	27	2002FA0000348    	1	20020305	G	7603	1159P200597	THROTTLE CABLE  			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					NR 2 ENGINE	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	949NA					221	8974			DURING NORMAL MAINTENANCE INSPECTION THE NR 2 ENGINE THROTTLE CABLE (FS-512 R) WAS FOUND TO BE SEVERELY FRAYED WITH APPR	OXIMATELY 50 PER CENT OF THE STRANDS BROKEN.  THE OTHER CABLES DID NOT HAVE ANY BROKEN STRANDS BUT DID HAVE SOME WIRES B	ROKEN.				2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2002032700096	20020327	00096	EU  	2002	3	27	2002FA0000349    	1	20020128	G	6520	350A33109100	GEAR            			SNIAS 	350   	AS350B2     	8680813	EU  										T/R GEARBOX	ROUGH           	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11										TEETH ON RING AND PINION DO NOT HAVE A POLISHED SURFACE ON FACE OF TEETH.  SURFACE IS NOT SMOOTH.						1	G	7	1 	3U			 	H9EU    					 
2002032700097	20020327	00097	EU  	2002	3	27	2002FA0000350    	1	20020129	G	6520	350A33109100	PINION GEAR     			SNIAS 	350   	AS350B2     	8680813	EU  										T/R GEARBOX	ROUGH           	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11										TEETH ON RING AND PINION DO NOT HAVE A POLISHED FINISH ON FACE OF TEETH.  SURFACE IS NOT SMOOTH.						1	G	7	1 	3U			 	H9EU    					 
2002032700098	20020327	00098	SO  	2002	3	27	2002FA0000351    	1	20020301	G	5711	28018	SPAR            			LUSCOM	8     	8A          	8190104	SO  	CONT  	A65   	A65*        	17003	SO  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	134K	1821 				4072				DURING ANNUAL INSPECTION OF THE CARRY THROUGH SPARS, INTER GRANULAR CORROSION WAS FOUND IN THE BOTTOM WEB OF THE AFT SPA	R, NONE FOUND IN THE FORWARD SPAR.  PROBABLE CAUSE WAS IN MANUFACTURING.  RECOMMEND CONTINUED INSPECTION OF OLD SPARS.					1	H	7	1 	3O	3	O	 	A694    	E205				 
2002032700099	20020327	00099	SO  	2002	3	27	2002FA0000352    	1	20020301	G	5312	28007	BULKHEAD        			LUSCOM	8     	8A          	8190104	SO  	CONT  	A65   	A65*        	17003	SO  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	1345K	1821 				4072				BULKHEAD WAS FOUND CRACKED DURING THE REPLACEMENT OF THE VERTICAL ATTACH FITTING PER AD.  PROBABLE CAUSE WAS AN EARLIER 	GROUND LOOP THIS AIRCRAFT SUFFERED IN 1959.  THE CRACK WAS IN BETWEEN TWO BOLT HOLES AND WAS UNNOTICEABLE UNLESS THE VER	TICAL FIN WAS REMOVED.				1	H	7	1 	3O	3	O	 	A694    	E205				 
2002032700110	20020327	00110	EA  	2002	3	27	2002FA0000355    	2	20020201	G	8500	B1741	WHEEL           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE FAN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	2359T	3646 				2359	1438039A			DURING REMOVAL OF FAN ASSEMBLY WHICH IS MOUNTED ON A TAPERED SHAFT, THE FAN MOUNTING WAS FOUND TO BE CRACKED THROUGH.  A	LSO THE REINFORCEMENT PLATE WHICH IS USED TO STRENGTHEN THE FAN ASSEMBLY WAS FOUND TO BE SEVERELY CRACKED.  THIS SIDE OF	 THE FAN ASSEMBLY MOUNTS TO THE FAN NUT WAS OVER TORQUED CAUSING UNDUE STRESS ON THE TAPERED SHAFT CAUSING THE FAILURE. 	 THIS AREA IS HARD TO INSPECT WITHOUT FAN REMOVAL, THEREFORE IT WENT UNDETECTED WHICH EVENTUALLY LEAD TO THE REINFORCEME	NT PLATE CRACKING.  SUGGEST USING APPROPRIATE TORQUE ON RETENTION NUT.		1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002032700112	20020327	00112	SW  	2002	3	27	2002FA0000356    	1	20020318	G	5711		SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  	CONT  	O200  	O200*       	17020	SO  					RT WING	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	9571S					7ECA379				WHILE RECOVERING WINGS FOUND NUMEROUS LOOSE RIBS THAT HAD RUBBED GROVES IN THE SPARS.  SOME SMALL CRACKS ORIGINATING FRO	M THE NAIL HOLES.  AIRPLANE HAD BEEN USED IN AEROBATICS.  REPLACED ALL FOUR WING SPARS.					1	H	7	1 	3O	3	O	 	A759    	E252				 
2002032000012	20020320	00012	CE  	2002	3	20	2002FA0000363    	1	20020319	G	3010		DUCT            			CESSNA	750   	750         	2076810	CE  										WING	OUT OF POSITION 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	551AM	365  				7500155				LEADING EDGES REMOVED FOR INSPECTION IT WAS DISCOVERED THE BLEED AIR TUBE IN BOTH SIDES, P/N UNAVAILABLE, HAD MIGRATED O	UTBOARD.  THE RETAINING SHEET METAL DIFFUSER WAS GOUGING INTO THE WELDED -T-.					2	L	7	2 	4J			RT	T00007WI					 
2002032700116	20020327	00116	CE  	2002	3	27	2002FA0000364    	1	20020228	G	5610	5116052	WINDOW          			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A60      	52043	NE  					FUSELAGE	CRACKED         	B			CTYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	83GF					4250132				WINDOW, LOCATED IN UPPER CABIN DOOR, WAS FOUND TO HAVE 4 CONSECUTIVE MOUNTING HOLES BROKEN ALONG LOWER EDGE.  A RETAININ	G RING,  CALLED OUT IN PARTS BOOK, WAS NOT INSTALLED ON THIS WINDOW.  THE INSTALLATION APPEARS TO HAVE BEEN DONE AT THE 	FACTORY, DUE TO DATE ON WINDOW.  NOTE:  OTHER WINDOWS ON THIS AIRCRAFT USE RETAINING RINGS.				1	L	7	2 	3T	4	T	RT	A7CE    	E4EA				 
2002032700118	20020327	00118	CE  	2002	3	27	2002FA0000365    	1	20020214	G	3230	50810323	LANDING GEAR    			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					MLG	FAILED          	B			QH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	727MT					LW271				MAIN LANDING GEAR A LOWER TORQUE KNEE, FAILED.						1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2002032700119	20020327	00119	CE  	2002	3	27	2002FA0000366    	1	20020319	G	3397	TTGCTA201TWB	SWITCH          			CESSNA	172   	172N        	2072434	CE  										INSTRUMENT PANEL	BURNED          	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			WP	07	9963E					17272301				SWITCH WAS STUCK IN THE OFF POSITION DURING PREFLIGHT.MAINTENANCE FOUND SWITCH INTERNALLY BURNED. UNKNOWN TIME ON SWITCH	.					1	H	7	1 	3O			NT	3A12    					 
2002032700120	20020327	00120	SO  	2002	3	27	2002FA0000368    	1	20020307	G	2730	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O540  	TIO540*     	41532	EA  					FWD STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149A	2234 				2843189				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT A	ND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION.  THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PU	LLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.  PROBABLE CAUSE:  SUBSTANDARD CABLE AND IMPROPER ALIGNMENT	 BY MANUFACTURER.			1	L	7	1 	3O	3	O	 	2A13    	E14EA				 
2002032700121	20020327	00121	SO  	2002	3	27	2002FA0000369    	1	20020307	G	2730	627701114	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O540  	TIO540*     	41532	EA  					STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149A	2234 				2843189				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT A	ND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION.  THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PU	LLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.  PROBABLE CAUSE- SUBSTANDARD CABLE AND IMPROPER ALIGNMENT 	BY MANUFACTURER.			1	L	7	1 	3O	3	O	 	2A13    	E14EA				 
2002032700122	20020327	00122	SO  	2002	3	27	2002FA0000370    	1	20020307	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O540  	TIO540*     	41532	EA  					AILERON	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149A	2234 				2843189				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT A	ND LEFT BALANCE CABLES WERE ALSO FOUND A SIMILAR CONDITION.  THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLE	YS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.  PROBABLE CAUSE:  SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY	 MANUFACTURER.			1	L	7	1 	3O	3	O	 	2A13    	E14EA				 
2002032700123	20020327	00123	SO  	2002	3	27	2002FA0000371    	1	20020307	G	2710	62701124	CABLE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O540  	TIO540*     	41532	EA  					AILERON	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149A	2234 				2843189				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED.  THE AILERON RIGHT A	ND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION.  THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PU	LLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH.  PROBABLE CAUSE:  SUBSTANDARD CABLE AND IMPROPER ALIGNMENT	 BY MANUFACTURER.			1	L	7	1 	3O	3	O	 	2A13    	E14EA				 
2002032700124	20020327	00124	SO  	2002	3	27	2002FA0000372    	1	20020227	G	2730	62701113	CABLE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					FWD STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4146R	2592 				2843160				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN.  THE LEFT AILERON BALANCE CABL	E WAS ALSO FOUND IN A SIMILAR CONDITION.  THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS.  PROBABLE CAUSE:	  SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002032700125	20020327	00125	SO  	2002	3	27	2002FA0000373    	1	20020227	G	2730	62701114	CABLE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					FWD STABILATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4146R	2592 				2843160				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN.  THE LEFT AILERON BALANCE CABL	E WAS ALSO FOUND IN A SIMILAR CONDITION.  THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS.  PROBABLE CAUSE:	  SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002032700126	20020327	00126	SO  	2002	3	27	2002FA0000374    	1	20020227	G	2710	62701123	CABLE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					LT AILERON	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4146R	2592 				2843160				DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN.  THE LEFT AILERON BALANCE CABL	E WAS ALSO FOUND IN A SIMILAR CONDITION.  THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002032700128	20020327	00128	EA  	2002	3	27	2002FA0000376    	2	20020301	G	7322	MA4SPA	TUBE            			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320*       	41508	EA  					CARB DISCHARGE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	3326P					231277				ENGINE WILL NOT START,  FOUND ACCELERATING PUMP DISCHARGE TUBE IN AIR BOX.  REMOVE CARBURETOR FOR OVERHAUL.						1	L	7	2 	3O	3	O	 	1A10    	E274				 
2002032700131	20020327	00131	CE  	2002	3	27	2002FA0000377    	1	20020302	G	5550	354051303	FITTING         			BEECH 	35    	B35         	1151506	CE  	CONT  	E185  	E185*       	17014	SO  					STAB ATTACH	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5208C					D2553				LOOKED AT RUDDERVATORS MOVEMENT, THIS FITTING WAS MOVING, CALLED MANUFACTURER FOR INFORMATION ON THIS FITTING.						1	L	7	1 	3O	3	O	 	A777    	E246				 
2002032700134	20020327	00134	EA  	2002	3	27	2002FA0000378    	2	20020301	G	8500	56A2263401	BOSS            			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					RT TURBO STUD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	727MC	460  				4636085	L978661A			INSPECTOR FOUND LOOSE RIGHT TURBO BOTTOM ATTACHMENT STUD, CAUSED BY CRACKED MOUNTING BOSS IN MAGNESIUM OIL SUMP ASSEMBLY	.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2002032700135	20020327	00135	CE  	2002	3	27	2002FA0000380    	1	20020321	G	3397	CM358910	SWITCH          			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					TAXI LIGHT	FAILED          	B				K				NONE                    				L			NO TEST                   			TX	TAXI/GRND HDL  	1			WP	07	502ER	2845 				172S8002				TAXI LIGHT SWITCH FAILED IN THE OFF POSITION.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002032700136	20020327	00136	CE  	2002	3	27	2002FA0000381    	1	20020319	G	2150	M5862AR6B	MOTOR           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ACM BLOWER	MISOVERHAULED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	6001L		9    			5500169				NR 1 ACM BLOWER MOTOR WAS REPLACED WITH A FRESH OVERHAULED UNIT. THE OVERHAULED BLOWER MOTOR FLEW 9.1 HOURS BEFORE FAILI	NG. WHILE PREPARING TO REPLACE UNIT, IT WAS DISCOVERED THAT THERE HAD BEEN SEVERE ELECTRICAL ARCING TAKING PLACE, AFTER 	INITIAL INSTALLATION & INSPECTION. THE BLOWER MOUNT CRADLES AND RETENTION STRAPS WERE BURNT IN HALF. DISASSEMBLY OF THE 	BLOWER MOTOR REVEALED THAT THE POSITIVE WIRE INSIDE THE MOTOR HAD BEEN PINCHED BETWEEN HOUSING LUGS AND HAD CHAFED THRU 	DURING OPERATION AND HAD GROUNDED TO THE MOTOR CASE. IT WAS FOUND THAT DURING OVERHAUL, THE MOTOR HAD BEEN INCORRECTLY A	SSEMBLED.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002032700137	20020327	00137	WP  	2002	3	27	2002FA0000382    	1	20020213	G	5313		STINGER         			LKHEED	1011  	10113851    	5265010	WP  										FUSELAGE	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	188AT	70757				193C1078				FORWARD FUSELAGE SECTION, FORWARD E/E, SURFACE CORROSION ON TOP OF STRINGER 38, FS 297 TO FS 312, BL 45.  MAINTENANCE RE	PAIRED STRINGER AT FS 297 TO 312 IAW SB.					2	L	7	3 	4F			 	A23WE   					 
2002032700138	20020327	00138	EA  	2002	3	27	2002FA0000383    	2	20020201	G	8500	B1741	WHEEL           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE FAN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	2359T	3646 				2359	L1438039A			DURING REMOVAL OF FAN ASSEMBLY WHICH IS MOUNTED ON A TAPERED SHAFT,  THE FAN MOUNTING HUB WAS FOUND TO BE CRACKED THROUG	H.  ALSO THE REINFORCEMENT PLATE WHICH IS USED TO STRENGTHEN THE FAN ASSEMBLY WAS FOUND TO BE SEVERELY CRACKED.  THIS SI	DE OF THE FAN ASSEMBLY MOUNTS TO THE FAN SHAFT BEARING ASSEMBLY.  SUSPECT THAT TAPERED SHAFT RETAINING NUT WAS OVERTORQU	ED CAUSING UNDUE STRESS ON THE TAPERED SHAFT CAUSING THE FAILURE.  THIS AREA IS HARD TO INSPECT WITHOUT FAN REMOVAL, THE	REFORE IT WENT UNDETECTED WHICH EVENTUALLY LEAD TO THE REINFORCEMENT PLATE CRACKING  SUGGEST USING  APPROPRIATE TORQUE O	N RETENTION NUT.	1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002032700139	20020327	00139	CE  	2002	3	27	2002FA0000384    	1	20020321	G	3397	TTGCTA201TWB	SWITCH          			CESSNA	172   	172N        	2072434	CE  										TAXI LIGHT	BURNED          	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			WP	07	38ER					17270698				LANDING/TAXI LIGHT SWITCH QUIT WORKING.  SWITCH STUCK IN THE ON POSITION.  SWITCH BURNED INTERNALLY.						1	H	7	1 	3O			NT	3A12    					 
2002032700140	20020327	00140	CE  	2002	3	27	2002FA0000385    	1	20020311	G	2841	0023810025	GAUGE           			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					FUEL SIGHT GAUGE	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	872AN					TH1679				WHILE REPLACING LEFT WING FUEL SIGHT GAUGE IT WAS FOUND THE NEW PART HAD FLOAT ARM INDEXED 180 DEGREE FROM ORIGINAL GAUG	E.  THIS DIFFERENCE CAUSED FLOAT ARM TO CONTACT LEADING EDGE CURVE AND GAUGE WOULD NOT READ BELOW 45 GALLONS.  WHEN ADDI	TIONAL PART WAS ORDERED, ANOTHER GAUGE WAS ALSO INDEXED WRONG.  PARTS RETURNED TO FACTORY.				1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2002032700141	20020327	00141	CE  	2002	3	27	2002FA0000386    	1	20020204	G	8120	63272913	TURBOCHARGER    			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					INDUCTION SYSTEM	LEAKING         	B			W45R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	234PT					EA662	527458			TURBOCHARGER LEAKING OIL IN INDUCTION SYSTEM.  RECHECKED SYSTEMS AS PER MFG. AND MM.  THIS IS NR2 OF SEVERAL ON THIS ENG	INE.					1	L	7	1 	3O	3	O	 	3A15    	E8CE				 
2002032700142	20020327	00142	CE  	2002	3	27	2002FA0000387    	1	20020319	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A11      	52043	NE  					COCKPIT	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	969WB					BB969				INNER PANE OF PILOT WINDSHIELD SHATTERED IN CRUISE FLIGHT.  AIRCRAFT LANDED WITHOUT INCIDENT.  WINDSHIELD HEAT CONTROLLE	R CHANGED IN CONJUNCTION WITH WINDSHIELD.					1	L	7	2 	4T	3	T	 	A24CE   	E4EA				 
2002032700143	20020327	00143	CE  	2002	3	27	2002FA0000389    	1	20020311	G	2822	64621216A2	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL SYSTEM	INACCURATE      	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1568P	1    				CE1298	825776R			UNABLE TO ADJUST FUEL PUMP PRESSURE.  PRESSURE IS TO HIGH AT LOW RPM AND THE ADJUSTMENT SCREW BACK ALL THE WAY OUT.  PUM	P REMOVED AND SENT IN FOR WARRANTY.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002032700144	20020327	00144		2002	3	27	2002FA0000391    	4	20020305	G	6113	055036711	SPINNER         			CESSNA	172   	172S        	2072439	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER	CRACKED         	B			FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	35339	149  				172S8891				DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED A .7500 INCH CRACK IN THE CORNER OF SPINNER (PN 0550367-1) AND BULKHEAD (	PN 0550321-11).					1	H	7	1 	3O			NT	3A12    		5	N	P910	 
2002032700145	20020327	00145	SO  	2002	3	27	2002FA0000393    	2	20020313	G	8520	639292	COTTER PIN      			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360LB   	17025	SO  					CONNECTING ROD	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	231NJ	207  				250324	247358R			DURING ANNUAL INSPECTION FOUND COTTER PIN IN THE OIL SUCTION SCREEN.  THE COTTER PIN WAS BROKEN INTO THREE PIECES.  FURT	HER INSPECTION OF THE ENGINE FOUND THE COTTER PIN MISSING FROM CYLINDER NUMBER FOURS LOWER CONNECTING ROD BOLT.  I BELIE	VE THE COTTER PIN WAS IMPROPERLY INSTALLED DURING A PROPELLER STRIKE INSPECTION WHICH ALLOWED THE COTTER PIN TO MOVE WEA	RING THE PIN TO THE POINT OF FAILURE.			1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2002032700146	20020327	00146	CE  	2002	3	27	2002FA0000395    	1	20020319	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A11      	52043	NE  					COCKPIT	BROKEN          	F				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	969WB					BB969				INNER PANE OF PILOT WINDSHIELD SHATTERED IN CRUISE FLIGHT.  AIRCRAFT LANDED WITHOUT INCIDENCE.  WINDSHIELD HEAT CONTROLL	ER CHANGED IN CONJUNCTION WITH WINDSHIELD.  NO PROBABLE CAUSE FOR BREAKAGE.					1	L	7	2 	4T	3	T	 	A24CE   	E4EA				 
2002032700147	20020327	00147	GL  	2002	3	27	2002FA0000396    	2	20020315	G	7261	222065505161	OIL TANK        			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE OIL	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	19	430Q	1570 				49002				OIL LEAKING AROUND NR 1 INPUT DRIVE ON MAIN TRANSMISSION.  DISCOVERED CRACK IN THE BOTTOM OF NR 1 ENGINE OIL TANK APPROX	IMATELY 1.5000 INCHES LONG AT THE BOTTOM OUTLET.					1	G	7	2 	3U	3	U	RT	H9SW    	E4CE				 
2002032700148	20020327	00148	CE  	2002	3	27	2002FA0000397    	1	20020307	G	7920	30725911	TUBE            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					OIL SYSTEM	CRACKED         	B				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			EA	25	84BA	2110 				258313	P107191			ON APPROACH PBI, THE RIGHT ENGINE OIL PRESSURE STARTED TO DROP, OIL TEMP WAS NORMAL.  ENGINE WAS SHUTDOWN BY CREW WHEN O	IL PRESSURE DROPPED TO 20 PSI.  TOUCH DOWN AND DROPPED TO 20 PSI.  TOUCH DOWN AND ROLLOUT WAS UNEVENTFUL.  FOUND OIL TRA	NSFER TUBE CRACKED AT FLARE.  REMOVED AND REPLACED TUBE (PN 30725911).  OIL SERVICED AND LEAK CHECKED.  CRACKED TUBE SHO	WED NO SIGNS OF IMPROPER INSTALLATION.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002032700150	20020327	00150	CE  	2002	3	27	2002FA0000398    	1	20020301	G	2897	57181061	WIRE            			CESSNA	441   	441         	2076020	CE  										BOOST PUMP	CHAFED          	B			PAZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	441SX	8332 				4410248				FOUND RT WING AUXILLARY BOOST PUMP WIRING, CHAFING ON BOOST PUMP HOUSING CAUSING AN ELECTRICAL ARCING INSIDE OF FUEL BAY	.					1	L	7	2 	3T			RT	A28CE   					 
2002032700070	20020327	00070	CE  	2002	3	27	2002FA0000399    	1	20020326	G	3710	1H525	MANIFOLD        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					VACUUM SYSTEM	DETACHED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	482ER	2921 				17280631	L2780151A			THIS AIRCRAFT USES DUAL VACUUM PUMPS. THESE PUMPS ARE CONNECTED TO THE VACUUM SYSTEM VIA A MANIFOLD ASSEMBLY. THIS MANIF	OLD PERFORMS TWO IMPORTANT FUNCTIONS, ONE TO ALLOW FOR A COMBINED SOURCE OF VACUUM FROM THESE TWO PUMPS, AS WELL AS PROV	IDE AN ISOLATION FUNCTION SHOULD ONE PUMP FAIL. THIS MANIFOLD VALVE, IS ASSEMBLED USING SMALL ALUMINUM RIVETS. THEY HAVE	 BEEN FAILING ALLOWING THE MANIFOLD VALVE TO SEPARATE WHILE MOUNTED ON THE FIREWALL. THIS RENDERS THE ENTIRE VACUUM SYST	EM INNOPERATIVE, AND COMPLETELY DISCONNECTS THE TWO PUMPS FROM THE SYSTEM.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002032800003	20020328	00003	SW  	2002	3	28	2002FA0000400    	1	20020315	G	2720	5420014157	TORQUE TUBE     			GULSTM	560   	560         	0141402	SW  	LYC   	O480  	GO480*      	41527	EA  					RUDDER	WORN            	D			UUMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	2705B	6247 				205	L115628			DURING AN ANNUAL INSPECTION, WHILE MEASURING RUDDER TRAVELS IT WAS FOUND THAT IF A LITTLE EXTRA PRESSURE WAS APPLIED TO 	THE RUDDER TRAILING EDGE, ONCE IT HAD REACHED ITS STOP, THE RUDDER TRAVELED AN EXTRA INCH PAST THE SPECIFIED TRAVELS.  W	HILE THE STOP REMAINED STATIONARY UPON INSPECTION, IT WAS FOUND THAT ALL THE RIVETS ON THE TOP AND BOTTOM OF THE RUDDER 	TORQUE TUBE WERE LOOSE AND WORN.  THE CAUSE IS MORE THAN LIKELY FROM WIND DAMAGE.  RECOMMENDATIONS:  MAKE SURE THAT THE 	RUDDER GUST LOCK IS INSTALLED AFTER A FLIGHT.		1	H	7	2 	3O	3	O	 	6A1     	E275				 
2002032800004	20020328	00004	SO  	2002	3	28	2002FA0000401    	1	20020206	G	2720	66661000	ARM             			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540*       	41532	EA  					RUDDER TRIM	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2147D					287911034				RUDDER TRIM ARM BROKEN OFF WHERE PILOTS TRIM CONTROL ASSY IS CONNECTED.  PEDAL TORQUE TUBE ASSY. HAS EXCESSIVE WEAR AND 	SCORING AT PIVOT BEARING POINTS DUE TO LACK OF LUBRICATION.  BROKEN ARM ASSY. SUGGESTED DUE TO OPERATING TRIM CONTROL ON	 GROUND PREVENTING NLG STEERING FROM MOVING PUTTING EXCESSIVE LOADS ON TRIM ARM.  SUGGEST TRIM BE NEUTRALED FRO TAKEOFF 	WHILE TAXING ALLOWING STEERING TO MOVE FREELY.  DEFECT FOUND DURING ANNUAL INSPECTION.			1	L	7	1 	3O	3	O	 	2A13    	E295				 
2002032800005	20020328	00005	SO  	2002	3	28	2002FA0000402    	1	20020311	G	3222	3503002	ACTUATOR        			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320*       	41508	EA  					NLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	3285P	1572 				231233				PILOT WAS TAXIING OFF OF RUNWAY ON AN UNIMPROVED AREA.  THE NOSE GEAR DOWN LOCK WAS RELEASED DUE TO ROUGH TERRAIN AND TH	E NOSE GEAR ACTUATOR ROD WAS BENT APPROXIMATELY 60 DEGREES.					1	L	7	2 	3O	3	O	 	1A10    	E274				 
2002032900152	20020329	00152	SO  	2002	3	29	2002FA0000403    	1	20020110	G	3230	HP70310052711	CONTROL VALVE   			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					MLG	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	33PJ					57	L8618			THE VALVE DESCRIBED AT LEFT, WAS INSTALLED DUE TO THE UNIT INSTALLED PRIOR HAVING AN EXTERNAL LEAK.  DURING INSTALLATION	 THE VALVE WAS ADJUSTED TO THE SPECIFICATION DESCRIBED IN THE CMP CODE (ATA CODE) ABOVE.  THE AIRCRAFT WAS THEN PUT THRO	UGH A GEAR SWING (10) TEN TIMES WITH THE UNIT OPERATING NORMALLY.  THE AIRCRAFT AND PART DESCRIBED WERE INSPECTED AND TH	E AIRCRAFT DISPATCHED.			2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2002032900154	20020329	00154	CE  	2002	3	29	2002FA0000405    	1	20020307	G	3610	CM36914	TUBE            			CESSNA	425   	425         	2076018	CE  										PNEUMATIC TUBE	MELTED          	D			CNQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	71HE					4250085				RIGHT INSTRUMENT AIR PRESSURE WAS AT ZERO ON THE GROUND AND WOULD INCREASE AS CABIN PRESSURE INCREASED IN FLIGHT.  FOUND	 PNEUMATIC SUPPLY LINE FROM COMMON TEE TO FORWARD PRESSURE BULKHEAD MELTED.  REPLACED TUBING.					1	L	7	2 	3T			RT	A7CE    					 
2002032900155	20020329	00155	CE  	2002	3	29	2002FA0000406    	1	20020307	G	3610	CM36914	TUBE            			CESSNA	425   	425         	2076018	CE  										PNEUMATIC TUBE	MELTED          	D			CNQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	425GM					4250033				RIGHT INSTRUMENT AIR PRESSURE WAS AT ZERO ON THE GROUND AND WOULD INCREASE AS CABIN PRESSURE INCREASED IN FLIGHT.  FOUND	 PNEUMATIC SUPPLY LINE FROM COMMON TEE TO FORWARD PRESSURE BULKHEAD MELTED.  REPLACED TUBING.					1	L	7	2 	3T			RT	A7CE    					 
2002032900156	20020329	00156	CE  	2002	3	29	2002FA0000407    	1	20020307	G	3610	CM36914	TUBE            			CESSNA	425   	425         	2076018	CE  										PNEUMATIC TUBE	MELTED          	D			CNQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	168MA					4250155				RIGHT INSTRUMENT AIR PRESSURE WAS AT ZERO ON THE GROUND AND WOULD INCREASE AS CABIN PRESSURE INCREASED IN FLIGHT.  FOUND	 PNEUMATIC SUPPLY LINE FROM COMMON TEE TO FORWARD PRESSURE BULKHEAD MELTED.  REPLACED TUBING WITH SUPERSEDED (PN P610051	) TWICE.  BOTH TIMES THE LINE MELTED ON POWER APPLICATION.				1	L	7	2 	3T			RT	A7CE    					 
2002032900158	20020329	00158	EU  	2002	3	29	2002FA0000408    	1	20020207	G	3397	3057992	TRANSFORMER     			AIRBUS	320   	A320232     	3930326	EU  										LANDING LIGHT	ARCED           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	437UA					655				OUTPUT TERMINALS ON THE TRANSFORMER ASSEMBLY SHOWS A CLEAR EVIDENCE OF ARCING ONE OF THE TERMINALS HAD BURNED OFF.  MFG 	HAS A SIL.  REGARDING THIS CONDITION.					2	L	7	2 	4F			RT	A28NM   					 
2002032900160	20020329	00160	SO  	2002	3	29	2002FA0000409    	1	20020328	G	5711	620540062054	SPAR            			PIPER 	PA28  	PA28180     	7102808	SO  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	5160S	5277 				287105014				REAR SPAR SEVERELY CORRODED UNDER STEEL ATTACH PLATES, P/N 66762-00. DAMAGE WAS FOUND WITH A FLASHLIGHT AND MIRROR, LOOK	ING AT THE FORWARD SIDE OF THE SPAR THROUGH THE INBOARD RIB LIGHTENING HOLES AND WAS SO FAR PROGRESSED THAT THE EXFOLITA	TION PROCESS HAD BULDGED AND SPLIT THE SPAR MAKING IT VISIBLE FROM INSIDE THE WING. NO EXTERNAL CORROSION WAS NOTED DUE 	TO A SIX YEAR OLD PAINT JOB. STEEL PLATES ON FUSELAGE CARRY-THROUGH STRUCTURE ALSO REMOVED TO REVEAL SIMILAR CORROSION W	HICH WAS LESS SERVERE.		1	L	7	1 	3O			 	2A13    					 
2002032900162	20020329	00162	EU  	2002	3	29	2002FA0000410    	1	20020307	G	6730	AC67032	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	CRACKED         	B			QH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										SERVO BODY, CRACKED EXTENSION END.						1	G	7	1 	3U			 	H9EU    					 
2002032900163	20020329	00163	SO  	2002	3	29	2002FA0000411    	2	20020115	G	7414	441	MAGNETO         			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200*       	17020	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3539L					15062339				INSTALLED NEW CONDENSER DURING MAGNETO INSPECTION.  RUN-UP WAS NORMAL.  FULL POWER DURING TAKE-OFF SHOWED ROUGH RUNNING 	ENGINE.  FURTHER INSPECTION OF MAGNETO REVEALED THAT NEW M3064 CONDENSER HAD FAILED.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002032900164	20020329	00164	SO  	2002	3	29	2002FA0000412    	1	20020223	G	2420		VOLT REGULATOR  			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					ELECTRICAL	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	9395J					283499				OWNER COMPLAINED OF OVERVOLTAGE.  FOUND REGULATOR HAD BEEN REMOVED FROM SYSTEM.  ALTERNATOR RECENTLY REPLACED.  OLD ALTE	RNATOR MAY HAVE BEEN AUTOMOTIVE WITH INTERNAL REGULATOR.  PREVIOUS OWNER PERFORMED MUCH OF THE MAINTENANCE.  SUGGEST VER	IFYING AIRCRAFT, COMPLETE CHARGING SYSTEM WHEN REPLACING COMPONENTS.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002032900165	20020329	00165	SO  	2002	3	29	2002FA0000413    	2	20020221	G	7414	M3050	IMPULSE COUPLING			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520*      	17032	SO  					MAGNETOR	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	1003V	483  				U20602388				THE WOODRUFF KEY (M2536) THAT LOCKS THE IMPULSE COUPLING ON THE SHAFT WAS FOUND LODGED UNDERNEATH THE IMPULSE COUPLING P	AWL, RENDERING ONE OF THE TWO PAWLS IMMOBILE.  THE PIN ATTACHING THE PAWL WAS BENT AND THE GAP BETWEEN THE PAWL BOSS AND	 PLATE WAS NEAR LIMITS.  A POSSIBLE CAUSE WAS THAT WOODRUFF KEY WAS NOT PROPERLY SEATED, AND INSTALLATION OF IMPULSE COU	PLING DISLODGED THE WOODRUFF KEY.  EVENTUALLY THE WOODRUFF KEY LODGE ITSELF UNDER THE PAWL.			1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2002032900149	20020329	00149	EA  	2002	3	29	2002FA0000419    	2	20020329	G	7322	36596	CHECK VALVE     	PRECISION   	HA6         	SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360C1A   	41514	EA  					CARBURETOR	BACKED OUT      	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SO	19	2039Y	927  			75114110	0115	L3765036A			AIRCRAFT EXPERIENCED A PARTIAL POWER FAILURE ALONG WITH A SUDDEN VIBRATION.  DURING THE SUBSEQUENT INSPECTION, THE ACCEL	ERATOR PUMP DISCHARGE CHECK VALVE IN THE CARBURETOR WAS FOUND TO HAVE BACKED OUT OF ITS CHAMBER.  RECOMMEND REDESIGNING 	ALL THE CHECK-VALVES AND JETS IN THE CARBURETOR TO INCORPORATE A PERMANENT NYLON THREAD LOCK IN THE THREADS.				1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2002032900151	20020329	00151	CE  	2002	3	29	2002FA0000420    	1	20020326	G	2710		TURNBUCKLE      	BEECH       		BEECH 	35    	S35         	1151532	CE  										AILERON CABLE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	2JX	5050 				D7811				WHILE IN LEVEL FLIGHT AT 5500FT MSL, ATTEMPTING TO TURN THE AIRCRAFT LEFT WITH THE AILERON A SMALL BUMP/BANG WAS FELT. T	HE CONTROL WHEEL WENT FULL LEFT,AND THE AIRCRAFT COMMENCED ROLLING TO THE RIGHT. APPLICATION OF HARD RIGHT RUDDER STOPPE	D THE ROLL AT ABOUT 70 DEGREES RIGHT WING DOWN. AIRCRAFT WAS RECOVERED AFTER LOSING 2200FT. FLEW TO RSW BY KEEPING 20 TO	 25 DEGREES LEFT YAW, WITH THE RUDDER, AND 12 TO 15 DEGREES RT WING DOWN. LANDING WAS ACCOMPLISHED USING THE SAME TECHNI	QUE. ON GROUND, RIGHT AILERON WAS HELD FULL UP AND LEFT AILERON FULL DOWN BY SPRING TENSION.		1	L	7	1 	3O			 	3A15    					 
2002040200023	20020402	00023	CE  	2002	4	2	2002FA0000421    	1	20020325	G	5312	50351101	BULKHEAD        			WTHRLY	620   	620B        	9630605	CE  	PWA   	R985  	R985*       	52008	NE  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	90275	1015 				1637				DURING ANNUAL INSPECTION FOUND FUSELAGE BELLY PAN BULKHEAD (PN 50351-101) CRACKED UPPER LEFT AND RIGHT CORNER.  THIS ARE	A IS HARD TO SEE WITHOUT FLASHLIGHT AND MIRROR.  ALSO FOUND TAIL CONE BULKHEADS (PN 50351-105) AND (PN 50351-133) CRACKE	D AND TABS WHERE BULKHEAD IS RIVETED TO THE BELLY SKIN BROKEN.  SUGGEST A THROUGH INSPECTION OF THIS AREA USING A FLASHL	IGHT AND MIRROR.			1	L	7	1 	3R	3	R	NC	A26WE   	5E1				 
2002040200024	20020402	00024	CE  	2002	4	2	2002FA0000422    	1	20020325	G	5312	50351105	BULKHEAD        			WTHRLY	620   	620B        	9630605	CE  	PWA   	R985  	R985*       	52008	NE  					TAIL CONE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	90275	1015 				1637				DURING ANNUAL INSPECTION FOUND FUSELAGE BELLY PAN BULKHEAD (PN 50351-101) CRACKED UPPER LEFT AND RIGHT CORNER.  THIS ARE	A IS HARD TO SEE WITHOUT FLASHLIGHT AND MIRROR.  ALSO FOUND TAIL CONE BULKHEADS (PN 50351-105) AND (PN 50351-133) CRACKE	D AND TABS WHERE BULKHEAD IS RIVETED TOT HE BELLY SKIN BROKEN.  SUGGEST A THOROUGH INSPECTION OF THIS AREA USING A FLASH	LIGHT AND MIRROR.			1	L	7	1 	3R	3	R	NC	A26WE   	5E1				 
2002040200025	20020402	00025	CE  	2002	4	2	2002FA0000423    	1	20020325	G	5312	50351133	BULKHEAD        			WTHRLY	620   	620B        	9630605	CE  	PWA   	R985  	R985*       	52008	NE  					TAIL CONE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	90275	1015 				1637				DURING ANNUAL INSPECTION FOUND FUSELAGE BELLY PAN BULKHEAD (PN 50351-101) CRACKED UPPER LEFT AND RIGHT CORNER.  THIS ARE	A IS HARD TO SEE WITHOUT FLASHLIGHT AND MIRROR.  ALSO FOUND TAIL CONE BULKHEADS (PN 50351-105) AND  (PN 50351-133) CRACK	ED AND TABS WHERE BULKHEAD IS RIVETED TO THE BELLY SKIN BROKEN.  SUGGEST A THROUGH INSPECTION OF THIS AREA USING A FLASH	LIGHT AND MIRROR.			1	L	7	1 	3R	3	R	NC	A26WE   	5E1				 
2002040200001	20020402	00001	CE  	2002	4	2	2002FA0000424    	1	20020228	G	3340	C4559X	LIGHT           			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	545   	PW545A      	 	NE  					LANDING LIGHT	EXPLODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	398RS	650  				5605009				THE LANDING LIGHT IN AIRCRAFT BELLY FAILED.						2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2002040400070	20020404	00070	EA  	2002	4	4	2002FA0000429    	2	20020401	G	7321	3011849	LINE            			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUEL CONTROL	DAMAGED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07	107AJ	6208 				LA189				RIGHT ENGINE, FUEL RETURN TUBE TO FCU CRACKED AT B-NUT AND FUEL WAS BEING PUMPED OUT.  FORWARD END OF LINE GOES TO A TEE	 AND IT LOOKS LIKE, WHEN THE LINE COMING IN FROM THE TOP WAS TIGHTENED THE TEE, WAS NOT HELD AND THE TUBE WAS BENT AND C	RACKED.  INSPECTED LEFT ENGINE AND FOUND THIS SAME TUBE BENT BY TEE FITTING AND REPLACED IT ALSO.				1	L	7	2 	4T	4	T	 	A31CE   	E4EA				 
2002040400071	20020404	00071	CE  	2002	4	4	2002FA0000430    	1	20020314	G	3213	998201005	CYLINDER        			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					MLG	CORRODED        	B			S1FR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	6749E	7201 				LA43				WHILE PERFORMING 6 YEAR LANDING GEAR INSPECTION IAW MFG SPECIAL INSPECTION, FOUND CYLINDER ASSEMBLY IN NOSE GEAR HAD SEV	ERE CORROSION ON INTERNAL BORE.					1	L	7	2 	4T	4	T	 	A31CE   	E4EA				 
2002040500004	20020405	00004	SO  	2002	4	5	2002FA0000431    	1	20020326	G	7160	99047000	ADAPTER         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					ALT AIR DOOR	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	53276	513  				2844049				INSPECTED AND FOUND AIR DOOR AND HINGE BENT AND ALLOWING UNFILTERED AIR TO ENTER THE INTAKE SYSTEM.						1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002040500005	20020405	00005	CE  	2002	4	5	2002FA0000437    	1	20020207	G	3220		LINK            			CESSNA	210   	210D        	2073414	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	3806Y					21058306	112765R			NOSE GEAR FAILED TO EXTEND FOR LANDING, DAMAGING ENGINE, PROPELLER, GEAR DOORS AND NOSE TIRE.  AFTER JACKING AIRCRAFT IT	 WAS DISCOVERED THAT ROLLER ON MECHANICAL LINKAGE FOR NOSE GEAR DOORS HAD MOVED ON MECHANICAL LINKAGE FOR NOSE GEAR DOOR	S HAD MOVED FORWARD AND LOCKED ITSELF UNDER NOSE GEAR FORK.  THIS LINKAGE IS ALSO SPRING LOADED.  IT WAS ALSO FOUND THAT	 THIS LINKAGE HAD ANOTHER LINK ADDED TO IT WHICH LOWER ROLLER AND ALLOWED ROLLER TO CONTACT NOSE GEAR FORK EARLY.  EXTRA	 LINK WAS ATTACHED WITH ONLY ONE BOLT AND THIS ALLOWED LINK AND ROLLER TO MOVE FORWARD, GETTING LOCKED UNDER NOSE GEAR F	ORK WHEN GEAR WAS RETRACTED.	1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2002040500006	20020405	00006	CE  	2002	4	5	2002FA0000439    	1	20020221	G	7830	4510000501	THRUST REVERSER 			LEAR  	55    	55LEAR      	5170702	CE  										ENGINE	MISINSTALLED    	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	55HL	7052 				046				DOOR POSITION INDICATOR WIRING HARNESS WAS CUT AT RECEPTACLE.  DOOR POSITION INDICATOR RECEPTACLE INSTALLED UPSIDE DOWN,	 CAUSING DAMAGE TO MALE PINS IN RECEPTACLE.  DOOR POSITION INDICATOR WIRING HARNESS RETAINING CLAMP RIVET REPLACED WITH 	SCREW AND NUT.  DISCREPANCIES DISCOVERED DURING 1400 HOUR INSPECTION.				2	L	7	2 	4F			 	A10CE   					 
2002040500102	20020405	00102	NE  	2002	4	5	2002FA0000444    	2	20020104	G	7310	30366441	FLOW DIVIDER    			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					DUMP VALVE	LEAKING         	B			ML2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	520DG					BB1753	PCBPJ0491			RECEIVED NEW FLOW DIVIDER TO REPLACE FLOW DIVIDER WITH SUSPECTED LEAKING DUMP VALVE.  AT MFG REQUEST, A LEAK CHECK WAS P	ERFORMED ON THE NEW FLOW DIVIDER.  IT WAS FOUND THAT THE NEW FLOW DIVIDER LEAKED AT THE DUMP VALVE AND IS NOT SERVICEABL	E.  THIS IS SECOND FLOW DIVIDER RECEIVED THAT HAS FAILED THIS LEAK CHECK.  NO CAUSE OF LEAKAGE KNOWN AT THIS TIME.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002040500103	20020405	00103	CE  	2002	4	5	2002FA0000445    	1	20020319	G	2510	551900921	SEAT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	778JM					5500072				UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS.  (PHOTOS)  STRESS ON CHAIR BACK AND METAL FATIQUE PROBABLE CA	USE.  CHAIR WAS REPAIRED.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002040500104	20020405	00104	CE  	2002	4	5	2002FA0000446    	1	20020312	G	3060	6592SW	BOOT            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520*      	17032	SO  					LT PROP BOOT	DESTROYED       	D				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CE	03	4264J	479  				310R0201				DURING FLIGHT, ONE PROP BOOT DEPARTED AIRCRAFT.  UPON INSPECTION IT WAS DETERMINED THAT THE PAINT DID NOT ADHERE TO THE 	BLADE PROPERLY AND THE BOOT CAME LOOSE.					1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2002040500002	20020405	00002	NM  	2002	4	5	2002FA0000447    	1	20020404	G	5530	600N38001	STABILIZER      			DOUG  	600N  	600N        	3027377	NM  											CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	957SD	2348 				RN011				DURING A ROUTINE INSPECTION WE FOUND THE UPPER AND LOWER VERTICAL STABILIZERS TO HAVE CRACKS IN THE MOUNTING BORE EMANAT	ING FROM THE BOLT HOLES THAT ATTACH THE STABILIZER TO THE TORQUE TUBE.THE BORE HAS A CASTED LOOKING FITTING FOR EACH OF 	THE TWO MOUNTING BOLTS AND APPEARS TO BE A PLASTIC OR COMPOSITE TYPE MATERIAL. IT IS THIS CASTING THAT IS CRACKED, AND B	OTH UPPER AND LOWER CASTINGS IN SOME CASES.WE HAVE ORDERED 4 EACH REPLACEMENT STABILIZERS AND NOTIFIED MDHI.            			1	G	7	1 	3U			NC	H3WE    					 
2002040500003	20020405	00003	NM  	2002	4	5	2002FA0000449    	1	20020404	G	5530	600N38001	STABILIZER      			DOUG  	600N  	600N        	3027377	NM  										TAIL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	959SD	2193 				RN019				DURING A ROUTINE INSPECTION WE FOUND THE UPPER AND LOWER VERTICAL STABILIZERS TO HAVE CRACKS IN THE MOUNTING BORE EMANAT	ING FROM THE BOLT HOLES THAT ATTACH THE STABILIZERS TO THE TORQUE TUBE.THE BORE HAS A CASTED LOOKING FITTING FOR EACH OF	 THE TWO MOUNTING BOLTS AND APPEARS TO BE A PLASTIC OR COMPOSITE TYPE MATERIAL. IT IS THIS CASTING THAT IS CRACKED, BOTH	 UPPER AND LOWER IN SOME CASES. WE HAVE NOTIFIED MDHI AND HAVE ORDERED REPLACEMENT STABS.			1	G	7	1 	3U			NC	H3WE    					 
2002040500101	20020405	00101	CE  	2002	4	5	2002FA0000450    	1	20020405	G	5540	10164001419	HINGE           			BEECH 	200   	A200        	1152921	CE  										RUDDER	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1547	12787				BC50				THE CENTER RUDDER HINGE ASSEMBLY WAS REMOVED FROM THE AIRCRAFT FOR REPLACEMENT DUE TO VISIBLE CORROSION NEAR THE EDGE OF	 THE LOWER RIGHT HAND BOLT HOLE ON THE TEE. WHEN THE TEE WAS DERIVETED FROM THE HINGE SUBSTANTIAL EXFOLIATION WAS FOUND 	ON THE TEE SURFACE WHICH BUTTS UP AGAINST THE HINGE. SUBSTANTIAL PITTING WAS FOUND ON THE ADJOINING SURFACE OF THE HINGE	. THE EXFOLIATED AND PITTED AREAS ARE NOT VISIBLE WHEN THE HINGE IS IN THE ASSEMBLED POSITION. EXFOLIATION AND PITTING C	OULD HAVE PROPAGATED UNDETECTED TO THE POINT OF HINGE FAILURE. THE HINGE/TEE INTERFACE SHOULD BE SEALED UPON ASSEMBLY TO	 PREVENT CORROSION.	1	L	7	2 	4T			 	A24CE   					 
2002040800001	20020408	00001	CE  	2002	4	8	2002FA0000451    	1	20020327	G	2150	MCB69738150	COUPLING        			CESSNA	500   	560CESSNA   	2076750	CE  										ACM	LOOSE           	B			PAZR	B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CE	03	592M					5600338				DURING CRUISE FLIGHT, AFTER PHASE INSPECTIONS WERE COMPLETED, FLIGHT CREW REPORTED A "BUMP" AT AN ALTITUDE OF 31,000 FT,	 CABIN ALT STARTED TO CLIMB UNCONTROLLABLY, WARNING ANNUNCIATOR SHOWING "CABIN ALT. 10,000 FT.". CREW PERFORMED AN EMERG	ENCY DESCENT TO 15,000 FT. AND CONTINUED FLIGHT TO DESTINATION AIRPORT.  AFTER LANDING, MECHANIC FOUND A COUPLING LOOSE 	ON THE REFRIGERATION PACK (ACM) WHICH SHOWED EVIDENCE OF LEAKING. ALSO, THE MECHANIC FOUND TWO AN737TW58 CLAMPS LOOSE ON	 THE ACM.		2	L	7	2 	4F			RT	A22CE   					 
2002041100044	20020411	00044	SO  	2002	4	11	2002FA0000452    	2	20020322	G	8530	SA52000A1	CYLINDER        			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520E    	17040	SO  					LT ENGINE	FAILED          	B			CTUR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	21	234PS					340A0368				IN FLIGHT, PILOT NOTICED REDUCTION IN MANIFOLD PRESSURE.  PILOT DESCENDED WHEN COMPLETE FAILURE AND SEPARATION OF THE NR	 4 CYLINDER ON THE LEFT ENGINE OCCURRED.  CYLINDER HEAD SEPARATED FROM BARREL.  ENGINE WAS SECURED AND SHUT DOWN.  PROP 	WAS FEATHERED.  THE AIR CRAFT LANDED SAFELY.				1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2002041100045	20020411	00045	SO  	2002	4	11	2002FA0000453    	1	20020326	G	7160		HINGE           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					INDUCTION SYSTEM	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	730X	98   				2844066				DURING 100 HOUR INSPECTION NOTED ALTERNATE AIR DOOR AND HINGE BENT AND ALLOWING UNFILTERED AIR TO ENTER THE INTAKE SYSTE	M.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002041100046	20020411	00046	SO  	2002	4	11	2002FA0000454    	1	20020301	G	7120		BOLT            			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A11      	52043	NE  					ENGINE MOUNT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	75FL	4455 				428301002				UPON INSPECTION, FOUND RIGHT TOP ENGINE MOUNT BOLT BROKEN AT FIREWALL.						1	L	7	2 	4T	3	T	 	A23SO   	E4EA				 
2002041100047	20020411	00047	CE  	2002	4	11	2002FA0000455    	1	20020403	G	3233	35810083	SHAFT           			BEECH 	36    	A36TC       	1151603	CE  										MLG ACTUATOR	OVERSIZED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05	3872W	3049 	3049 			EA225				THE ORIGINAL LANDING GEAR ACTUATOR GEARBOX WAS BEING REMOVED AND DISASSSMBLED FOR A ROUTINE OVERHAUL.  DIFFICULTY WAS EN	COUNTER WHEN TRYING TO REMOVE THE ACTUATOR SHAFT FROM THE GEARBOX HOUSING.  IT WAS NOTED THAT THE FORCE REQUIRED TO SLID	E THE SHAFT OUT WAS UNUSUAL.  NO DAMAGE TO THE SHAFT WAS VISABLE.  THE ENTIRE ASSMBLY WAS FORWARDED TO AN APPROVED OVERH	AUL FACILITY.  FURTHER INSPECTION REVEALED THAT THE SPLINED END OF THE SHAFT HAD BEEN MANUFACTURED TO APPROXIMATELY .002	 - .003 OVERSIZE.  THE SHAFT WILL BE REPLACED DURING THIS OVERHAUL.  IT APPEARS THAT THIS IS THE ORIGINAL GEARBOX INSTAL	LED AT MANUFACTURE AS THERE IS NO RECORD INDICATING PRIOR REPLACEMENT.	1	L	7	1 	3O			 	3A15    					 
2002041100048	20020411	00048	CE  	2002	4	11	2002FA0000456    	1	20020408	G	8011	642087A10	ADAPTER         			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07		493  				TJ372	274383R			PILOT REPORTED ENGINE WOULD NOT START.  FOUND THAT PROP WOULD NOT TURN BACKWARDS. REPLACED STARTER ADAPTER WITH A REBUIL	T AND OPS CHECKED OK. THIS IS THE SECOND ADAPTER REPLACED ON THIS ENGINE. THE FIRST ONE FAILED ON A FACTORY REBUILT/ZERO	 TIME ENGINE WITH 402 HOURS ON IT. THE SECOND ONE,WHICH WAS A FACTORY REBUILT ADAPTER,FAILED WITH 493 HOURS ON IT.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2002041100049	20020411	00049	CE  	2002	4	11	2002FA0000457    	1	20020408	G	7160	ASSYBA2405	AIR FILTER      			CESSNA	210   	T210K       	2073447	CE  										AIR INLET	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	8251M					21059251				FOUND (BRACKETT) AIR FILTER ASSEMBLY (NR-BA-2405) INSTALLED BACKWARDS.  THE MESH SAFTEY SCREEN WAS AT THE FRONT OF THE F	OAM FILTER, AND THE INLET GRID WAS INSTALLED AT THE BACK OF THE ASSEMBLY.   INSPECTED ONE OTHER FILTER ASSEMBLY ON LIKE 	AIRCRAFT AND FOUND IT WAS ALSO MISINSTALLED.				1	H	7	1 	3O			 	3A21    					 
2002041100050	20020411	00050	CE  	2002	4	11	2002FA0000458    	1	20020401	G	3260	204101744	SUPPORT         			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					RT DOWNLOCK	BROKEN          	B			A5OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	8253G					177RG0153				PILOT REPORTED THAT THE LANDING GEAR PUMP MOTOR CONTINUED TO RUN AFTER THE GEAR WAS PUT IN THE DOWN POSITION AND THAT TH	E GEAR DOWN LIGHT DID NOT COME ON.  THE PILOT MADE AN UNEVENTFUL LANDING AFTER A LOW PASS AND GROUND PERSONNEL VERIFIED 	THE LANDING GEAR APPEARED TO BE DOWN.  TROUBLESHOOTING FOUND THAT THE RIGHT LANDING GEAR DOWN LOCK SWITCH WAS NOT MAKING	 DUE TO A BROKEN DOWN LOCK SUPPORT BRACKET.  THE BROKEN SUPPORT BRACKET ROTATED IN THE HOUSING AND DID NOT ALLOW THE RIG	HT MAIN LANDING GEAR TO LOCK DOWN.  REPLACED THE BROKEN PART WITH A NEW MFG PART AND RIGGED IAW SM.  OPS CHECKED GOOD.  	THE BROKEN PART HAD THE LOWER PIN SHEARED OFF.  IT ALSO SHOWED SIGNS OF HEAT WHERE IT WAS WELDED.	1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2002041100051	20020411	00051	SO  	2002	4	11	2002FA0000459    	2	20020401	G	8530	653816A7BP	CYLINDER        								CONT  	O200  	O200A       	17020	SO  					NR 1 ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25							627926A			USING COMPLETE CYLINDER AND VALVE ASSEMBLYS, ENGINE SCREEN PLUGGED WITH BLACK FLAKES AND STARVED ENGINE IN INITIAL HOUR 	OF BREAKING.  RESULTED IN OIL STARVATION TO MAINS, ROD BEARINGS, CYLINDER WALLS, CAMSHAFT, ROCKERS AND TAPPETS.  OIL PUM	P DAMAGED DUE TO ABRASION.  RINGS LOST MATERIAL, ROD BEARINGS LOST PLATING, ONE ROD BEARING SPUN.  CRANKSHAFT SEVERELY U	NDERCUT.  ANOTHER ENGINE REBUILT USING SAME ASSEMBLYS, ON BREAKING, AFTER TWO RUNS TOTALING 15 MINUTES SCREEN CHECKED AN	D FOUND WITH BLACK FLAKING, CLEANED AND ANOTHER RUN MADE.  MORE PARTICLES OF BLACK FLACK FOUND.  OIL REMOVED AND ENG FIL	LED WITH MORE FRESH BREAKIN OIL, ENGINE RUN, SCREEN CHECKED AND CLEANED.  TEST FLIGHT MADE.						3	O			E252				 
2002041100052	20020411	00052	GL  	2002	4	11	2002FA0000461    	1	20020328	G	3210	MM6	ROD END         			AMTR  	VIPER 	VIPERJET    	05607UF	GL  										MLG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	520VF	150  				0001				ROD END FAILED DUE TO SIDE LOADS AFTER LANDING (OR DURING).						1	L	7	1 	4U			RT	EXPA1L71					 
2002041100053	20020411	00053	WP  	2002	4	11	2002FA0000462    	1	20020322	G	3213	161909	STRUT           			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	R182082     	 	EA  					MLG	DAMAGED         	C			F1DM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	404DF		215  			455	BL516924			DURING A FLEETWIDE NDT INSPECTION OF OUR MAIN LANDING GEAR STRUTS, FOLLOWING A STRUT FAILURE ON T-86 (N433DF  SN 149855)	 A CRACK WAS FOUND IN THIS HOUSING.  IT WAS INSTALLED ON THE RIGHT SIDE STRUT ASSEMBLY.  IT WAS FOUND BY INSPECTION OF T	HE DISASSEMBLED STRUT ASSEMBLY.				2	H	7	2 	4R	4	R	 	A25WE   	 				 
2002041100054	20020411	00054	SO  	2002	4	11	2002FA0000463    	2	20020410	G	8540	649866	SHAFT           			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	TSIO550B    	17043	SO  					ENGINE	FAILED          	G				A				UNSCHED LANDING         				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			GL	03	29TC					E2644				AIRCRAFT ENGINE EXPERIENCED A LOSS OF OIL PRESSURE AND SUBSEQUENT LOSS OF POWER. ENGINE TEARDOWN INSPECTION REVEALED A F	AILURE OF THE STARTER ADAPTER SHAFT.   					1	L	7	1 	3O	3	O	 	3A15    	E5SO				 
2002041100043	20020411	00043	CE  	2002	4	11	2002FA0000464    	1	20020410	G	3010	PO67L015	PRESSURE SWITCH 			CESSNA	500   	S550        	2076607	CE  										DEICE SYSTEM	FAILED          	B				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			NE	05	126QS					S5500126				TKS DEICE SYSTEM PRESSURE SWITCHES ARE FAILING IN THE OPEN POSTION. WHEN THE SWITCHES FAIL OPEN THEY CAN NOT ILLUMINATE 	THE DEICE PRESSURE FAIL LIGHTS ON THE ANNUCIATOR. THE LIGHTS ILLUMINATE TO INDICATE LOW PRESSURE. THERE IS NO WAY TO TEL	L LOW PRESSURE IN THE SYSTEM WITH THESE SWITCHES FAILED OPEN. WE HAVE REPLACED THREE SWITCHES IN THE ENGINE DEICE SYSTEM	, ALL FAILED IN THE OPEN POSITION ON THIS TKS DEICE SYSTEM.			1	L	7	2 	4F			RT	A22CE   					 
2002041200064	20020412	00064	SO  	2002	4	12	2002FA0000465    	1	20020227	G	3213	170420	STRUT           			MARSH 	S2F   	S2F3S       	3951007	SO  	GARRTT	TPE331	TPE33114GR  	01514	NE  					MLG	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	433DF					149855	P104026			DURING A MAINTENANCE RUN-UP OF THE ENGINES, THE RIGHT STRUT OUTER HOUSING  FAILED CAUSING THE STRUT TO COLLAPSE.  DAMAGE	 WAS CAUSED TO THE PROPELLER, ENGINE, NACELLE, WING, AND FUSELAGE.					2	H	7	2 	4O	4	T	RT	A51NM   	E18NE				 
2002041200065	20020412	00065	CE  	2002	4	12	2002FA0000467    	1	20020401	G	2421	X610007	CONTACTOR       			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ALTERNATOR	FAILED          	B			AI4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	447SP	116  				172S8311				ALTERNATOR FIELD C/B POPPED DURING FLIGHT.  TROUBLESHOT ALTERNATOR AND RELATED COMPONENTS.  DISCOVERED DEFECTIVE ALTERNA	TOR CONTACTOR.  (RESISTANCE CHECK OF ENERGIZED CONTACTOR (ACROSS LARGE TERMINALS)  INDICATED AS HIGH AS 150 OHMS.  LIGHT	LY TAPPING THE CONTACTOR REDUCED RESISTANCE TO .6 OHMS).  THIS COMPONENT WAS IN SERVICE 116.8 HOURS.  RECOMMEND HEAVIER 	DUTY CONTACTOR.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002041200066	20020412	00066	EA  	2002	4	12	2002FA0000469    	2	20020401	G	7414	M3525	COIL            	SLICK       		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					LEFT MAGNETO	BURNED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NE	05	80657					17266693	L2853627A			DURING ROUTINE FLIGHT ENGINE BECAME ROUGH.  PILOT CONTINUED TOWARDS AIRPORT,  WITH NO OTHER OPTIONS, AND LANDED SAFELY. 	 ONCE ON THE GROUND, THE PILOT/ MECHANIC DID AN ENGINE RUN-UP AND FOUND LEFT MAGNETO DEAD.  FURTHER INSPECTION REVEALED 	A HOLE BURNED THROUGH THE COIL CASE INSIDE THE MAGNETO.  NEW COIL AND INSPECTION PUT AIRCRAFT BACK IN SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002041800057	20020418	00057	SO  	2002	4	18	2002FA0000470    	2	20020402	G	7414		BRUSHES         	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO CAP	WORN            	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8268T	475  			01090978	CE1547	825755R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBTOR BLOCK FROM MAGNET	O AND FOUND THE CARBON BRUSH WORN.  CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP.  THE WEARER ON THIS BRUSH IS ABOV	E NORMAL FOR 500 HRS.  (PN M3004 BRUSH).				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002041800058	20020418	00058	SO  	2002	4	18	2002FA0000471    	2	20020402	G	7414		BRUSHES         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO CAP	WORN            	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8268T					CE1547				MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE	TO AND FOUND THE CARBON BRUSH WORN.  CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP.  THE WEARER ON THIS BRUSH IS ABO	VE NORMAL FOR 500 HOURS (PN M3004 BRUSH).				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002041800059	20020418	00059	CE  	2002	4	18	2002FA0000472    	1	20020405	G	2720	04115261	TORQUE TUBE     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					LT RUDDER PED	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4725B	5941 				15283599				PILOT LEFT RUDDER PEDAL TORQUE TUBE BROKE AT WELD FOR PEDAL ARM.  RESULTING IN PILOT HAVING REDUCED OR NO LEFT RUDDER OR	 NOSE STEERING.  POSSIBLY CAUSED BY A DEFECTIVE WELD.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002041800060	20020418	00060	CE  	2002	4	18	2002FA0000473    	1	20020402	G	3600	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					AIR SYSTEM	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5609S	370  				CE1454	825756R			LOW OUT PUT FROM PUMP TO AIRCRAFT, REMOVED PUMP AND INSTALLED NEW PUMP, OPERATION WAS NORMAL.  PUMP SENT IN FOR WARRANTY	.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002041800061	20020418	00061	EA  	2002	4	18	2002FA0000474    	2	20020402	G	7414	103572101	SWITCH          			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					MAGNETO	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	865AF	6    				85005	L2826448A			MAGNETO SWITCH FAILED TO START ENGINE, FOUND BAD SWITCH.  NEW SWITCH INSTALLED, OPERATIONAL CHECKED NORMAL.  PART SENT I	N FOR WARRANTY.					1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002041800062	20020418	00062	SO  	2002	4	18	2002FA0000475    	2	20020402	G	7414		BRUSHES         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO CAP	WORN            	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6322A					CE998	820466R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE	TO AND FOUND THE CARBON BRUSH WORN.  CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP.  THE WEARER ON THIS BRUSH IS ABO	VE NORMAL FOR 500 HOURS. (PN M3004 BRUSH)				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002041800063	20020418	00063	SO  	2002	4	18	2002FA0000476    	2	20020402	G	7414		BRUSHES         	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DISTRIBUTOR	WORN            	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6322A	504  			01051685	CE998	820466R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE	TO AND FOUND THE CARBON BRUSH WORN.  CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP.  THE WEARER ON THIS BRUSH IS ABO	VE NORMAL FOR 500 HOURS.  (PN M3004 BRUSH)				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002041800064	20020418	00064		2002	4	18	2002FA0000477    	4	20020401	G	3120		PIN             			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					CLOCK	BROKEN          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	116  				85001	L2802348A			LEFT HAND STOP PIN BROKEN OFF,  REMOVED AND INSTALLED NEW CLOCK.  PART SENT IN FOR WARRANTY.						1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002041800065	20020418	00065	EU  	2002	4	18	2002FA0000478    	1	20020401	G	3600	1U128006	PUMP            			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					DRY AIR	DAMAGED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	116  				85001	L2802348A			METAL SHAFT SHEARED IN PUMP.  REMOVED AND INSTALLED NEW PUMP, SYSTEM OPERATIONAL CHECKED NORMAL.  PUMP SENT IN FOR WARRA	NTY.					1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002041700091	20020417	00091	CE  	2002	4	17	2002FA0000479    	1	20020406	G	3244	178K431	TIRE            			LEAR  	60    	60LEAR      	5170707	CE  										LANDING GEAR	SEPARATED       	E				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	15	60UJ		102  			007				TREAD SEPARATED ON LANDING.  CARCUS REMAINED IN TACT.						2	L	7	2 	4F			RT	A10CE   					 
2002041800066	20020418	00066	EU  	2002	4	18	2002FA0000480    	1	20020401	G	2711	G1204105	SERVO           			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					AILERON TRIM	STICKING        	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	862AF	59   				85002	L2802448A			TRIM SERVO STICKING IN OPERATION AND FAILS TO MOVE THE AILERON TRIM TAB.  REMOVED AND INSTALLED NEW TRIM SERVO ASSEMBLY.	  PART SENT IN FOR WARRANTY.					1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002041800067	20020418	00067	EU  	2002	4	18	2002FA0000481    	1	20020402	G	3233	1145	ACTUATOR        			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					MLG	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	862AF	59   				85002	L2802448A			NOSE LANDING GEAR HYDRAULIC ACTUATOR BOTTOM SEAL AROUND SHAFT BLOW OUT AND LEAKING FLUID FROM CYLINDER.  ACTUATOR REMOVE	D AND A NEW ACTUATOR INSTALLED.  ACTUATOR SENT IN FOR WARRANTY.					1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002041800068	20020418	00068	EU  	2002	4	18	2002FA0000482    	1	20020401	G	2913	X030001	PUMP            			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					HYD SYSTEM	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	863AF	36   				85003	L2802548A			ELECTRIC MOTOR SLOW IN FLIGHT, OVER 25 TO 30 SECONDS TO RETRACT AND EXTENT THE LANDING GEAR.  NEW HYDRAULIC PUMP ASSEMBL	Y INSTALLED, CYCLED GEAR IAW MAINTENANCE MANUAL, LANDING GEAR OPERATIONAL CHECKED NORMAL.  PART SENT IN FOR WARRANTY.					1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002041800069	20020418	00069		2002	4	18	2002FA0000483    	4	20020401	G	2300	02908000062	FILTER          			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					RADIO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	863AF	35   				85003	L2802548A			FEED BACK IN THE RADIOS, NEW FILTER INSTALLED, OPERATIONAL CHECK NORMAL.  PART SENT IN FOR WARRANTY.						1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002041800070	20020418	00070	EU  	2002	4	18	2002FA0000484    	1	20020405	G	3150	120A913150	AUDIO PANEL     			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					COCKPIT	FAILED          	B			VJ3R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			WP	07	863AF	18   				85003	L2802548A			AUDIO PANEL FAIL INTERNALLY GIVING AND UNSAFE GEAR INDICATION LIGHT, AND WHEN THE THROTTLE WAS PULLED TO IDLE, THE HYDRA	ULIC PUMP WOULD START TO RUN.  REMOVED AND INSTALLED NEW AUDIO PANEL.  THE LANDING GEAR OPERATIONAL CHECKED NORMAL.  PAR	T SENT IN FOR WARRANTY.				1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002041800071	20020418	00071	CE  	2002	4	18	2002FA0000485    	1	20020404	G	3211	22411001	FITTING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					RT MLG	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	5227U	8288 				172RG0290				THIS FITTING, WITH 3 CRACKS,  IS PART OF THE RIGHT MAIN LANDING GEAR SPRING WHICH ATTACHES TO THE AXLE.						1	H	7	1 	3O	3	O	 	3A17    	E286				 
2002041800056	20020418	00056	EA  	2002	4	18	2002FA0000488    	2	20020415	G	7414	103572101	SWITCH          			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					MAGNETO	DEFECTIVE       	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			EA	23	5002T	54   	54   			287205237				PILOT REPORTED THE ENGINE WAS DIFFICULT TO "TURN OVER". PROBLEM WAS FOUND TO BE THE START POSITION OF THE MAG SWITCH. IG	NITION FUNCTIONS OF THE SWITCH WERE NORMAL. THIS SWITCH WAS REPLACED 54.49 HOURS EARLIER FOR THE SAME PROBLEM. INSTALLED	 A NEW SWITCH. OPERATIONAL CHECK WAS O.K.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002041900004	20020419	00004	GL  	2002	4	19	2002FA0000491    	2	20020408	G	7414	67542	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAG DRIVE	WORN            	B			MY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	675M	1063 				2894				BOTH MAGNETO DRIVE BEARINGS WERE LOOSE, REMOVED AND FOUND BOTH BEARINGS WORN AND ROUGH.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002041900005	20020419	00005	SW  	2002	4	19	2002FA0000492    	1	20020312	G	2720	26720025	BELLCRANK       			SWRNGN	SA226 	SA226TB     	8780406	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					RUDDER PEDAL	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	999MM	4792 				T309				HOLE IN RUDDER PEDAL ARM WHERE RUDDER PEDAL PIVOT POST GOES IS CRACKED.						2	L	7	2 	4T	3	T	RT	A5SW    	E2WE				 
2002041900006	20020419	00006	SW  	2002	4	19	2002FA0000493    	1	20020401	G	5712	2731023016	RIB             			SWRNGN	SA227 	SA227AC     	8780603	SW  										RT WING	CRACKED         	B			XVIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	787C					AC550				LOCATED AND MARKED END OF CRACKS AT WS 81.174 ON RIGHT AND LEFT WINGS IN THE LOWER RADIOUS OF THE WING RIBS.  BOTH CRACK	S WERE APPROX. 6 INCHES LONG AND FOLLOWED THE RADIUS FORWARD AND AFT.					2	L	7	2 	4T			RT	A8SW    					 
2002041900007	20020419	00007	SO  	2002	4	19	2002FA0000495    	2	20020412	G	8530	SA24122	BUSHING         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ROCKER ARMS	FAILED          	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	8778U	14   				15077986				EIGHT BUSHINGS FAILED WITHIN 15 HOURS OF OPERATION.  THE PROBLEM WAS INDICATED BY BRASS METALIC DUST IN THE OIL FILTER. 	 THIS LOOKED SIMILAR TO METALIC PAINT FLAKE SUSPENDED IN THE OIL.  THE ROCKER ARMS WERE REMOVED AND BUSHING CLEARANCE WA	S MEASURED.  THE WEAR WAS BETWEEN .006 AND .009.  MANUFACTURERS NEW LIMIT IS .0025 AND SERVICE LIMIT IS .004.  PROBABLE 	CAUSE MAY BE DEFECTIVE MATERIAL.			1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002041900008	20020419	00008		2002	4	19	2002FA0000497    	4	20020402	G	3421	060001700	GYRO            			PIPER 	PA31  	PA31350     	7103110	SO  										COCKPIT	FAILED          	B			C42R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	275CF					318252017				GYRO FAILURE.						1	L	7	2 	3O			 	A20SO   					 
2002041900009	20020419	00009		2002	4	19	2002FA0000498    	4	20020402	G	3422	060001700	GYRO            			BEECH 	58    	58          	1152740	CE  										COCKPIT	FAILED          	B			C42R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6726S	134  				TH1390				GYRO FAILURE.						1	L	7	2 	3O			 	3A16    					 
2002041900010	20020419	00010		2002	4	19	2002FA0000499    	4	20020402	G	3421	060001700	GYRO            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					COCKPIT	FAILED          	B			C42R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6726S					TH1390				GYRO FAILURE.						1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2002041900011	20020419	00011		2002	4	19	2002FA0000500    	4	20020402	G	3421	060001700	GYRO            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					COCKPIT	FAILED          	B			C42R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6726S	93   				TH1390				GYRO FAILURE.						1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2002041900012	20020419	00012		2002	4	19	2002FA0000501    	4	20020402	G	3421	060001700	GYRO            			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540*     	41532	EA  					COCKPIT	FAILED          	B			C42R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	41018	41   				318212006				GYRO FAILURE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002041900013	20020419	00013		2002	4	19	2002FA0000502    	4	20020402	G	3421	060001700	GYRO            			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540*     	41532	EA  					COCKPIT	FAILED          	B			C42R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	41018					318212006				GYRO FAILURE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002041900001	20020419	00001	NE  	2002	4	19	2002FA0000503    	2	20020418	G	7261	AE7013002K024	HOSE            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  					ENGINE OIL	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	23	50JN	365  				4250232				HOSE WAS INSTALLED ON 10-15-99 1869.1TT. CURRENT AIRCRAFT TIME 2234.8 HRS. THIS HOSE LASTED 365.7 HRS. THIS HAS BEEN AN 	ON GOING PROBLEM WITH THIS AIRCRAFT. CESSNA SUPERSEEDED THE ORIGNAL HOSE P/N AS705976-1 TO THE AE7013002K024 WHICH IS SL	IGHTLY LONGER,IN HOPES TO CORRECT THE PROBLEM,BUT THE PROBLEM STILL EXIST. THESE HOSES ARE BLOWING OUT AT THE BEND RADIO	US. THE HOSES NEED TO BE LONGER OR A DIFFERENT STYLE. THIS IS THE SECOND M&D REPORT ON THIS AIRCRAFT.			1	L	7	2 	3T	3	T	RT	A7CE    	E4EA				 
2002041900002	20020419	00002	SO  	2002	4	19	2002FA0000504    	1	20020418	G	7430	103572101	SWITCH          			PIPER 	PA28  	PA28180     	7102808	SO  										IGNITION SYS	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5002T	102  	102  			287205237				PILOT REPORTED DIFFICULTY IN STARTING (CRANKING) OF ENGINE. PROBLEM WAS DISCOVERED TO BE THE START POSITION OF THE IGNIT	ION SWITCH. THIS IS THE THIRD SWITCH FAILURE FOR THE SAME PROBLEM IN THE LAST 157HRS OF OPERATION. THE FIRST REPLACEMENT	 SWITCH LASTED 54HRS BEFORE FAILURE AND THE SECOND SWITCH LASTED 102.81HRS. UPON RECEIVING THE NEW SWITCH, IT WAS TESTED	 AND FOUND TO BE FAULTY ACROSS THE START CONTACTS AS WELL. THE LATEST NEW SWITCH WAS ALSO TESTED AND FOUND TO BE ACCEPTA	BLE AND WAS INSTALLED. POSSIBLE POOR MANUFACTURER QUALITY CONTROL OR POSSIBLE FAULTY MATERIALS ARE SUSPECTED.		1	L	7	1 	3O			 	2A13    					 
2002042200033	20020422	00033	CE  	2002	4	22	2002FA0000505    	1	20020403	G	7160	LW18101	HOSE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					INDUCTION SYS	SATURATED       	B			VIB3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	739BP	61   				17270415	L272276			THE RUBBER INDUCTION COUPLING HOSES ON THE ENGINE WERE FOUND TO BE SATURATED WITH FUEL.  IT APPEARS THE FUEL WAS PERMEAT	ING RIGHT THROUGH THE HOSE.  FOUND THEY WERE REPLACED AT 62 FLIGHT HOURS AND 9 MONTHS EARLIER.  INSTALLED LW18101 HOSES 	AT THIS TIME.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002042200034	20020422	00034	CE  	2002	4	22	2002FA0000506    	1	20020403	G	7332	UMA33112	INDICATOR       			CESSNA	182   	R182        	2072734	CE  										FUEL PRESSURE	MISREPAIRED     	B			VIB3	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03	7139T					R18200025				A FUEL PRESSURE GAUGE WAS RETURNED TO MFG. FOR REPAIR.  THEY SENT A REPLACEMENT GAUGE IN ITS PLACE.  THE NEW GAUGE CAME 	WITH AN AN816-2D NIPPLE THREADED IN THE PRESSURE INLET PORT.  THE PROBLEM IS THE TEFLON THREAD TAPE WAS IMPROPERLY APPLI	ED.  NOT ONLY DID IT COVER ALL THE THREADS, IT COVERED ABOUT 75 PERCENT OF THE HOLE IN THE END OF THE FITTING.  THERE WE	RE ALSO SMALL TORN PIECES THAT WOULD HAVE BROKEN OFF AND ENTERED THE GAUGE.			1	H	7	1 	3O			RT	3A13    					 
2002042200035	20020422	00035	CE  	2002	4	22	2002FA0000507    	1	20020401	G	5730		SKIN            			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					LT WING	CRACKED         	B			DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	2384U	590  				17280708				CRACKS DEVELOPED IN TOP T/E LT WING SKIN AT EXTREME IB END OF WING AROUND 4 OF AN426AD4 RIVETS WHICH JOIN T/E STIFFENER 	TO UPPER AND LOWER WING SKINS JUST ABOVE FLAP.  CRACKS RANGED FROM .500 INCH TO 1 INCH AND ONLY 1 PENETRATED A RIVET HOL	E.  ONE OF RIVETS, JOINING EXTREME IB RIB TO UPPER SKIN HAD CRACK NEXT TO IT 1 INCH LONG.  CAUSED BY THE EXTREME AFT WIN	G ROOT FAIRING SCREW CONTACTING THE UPPER SKIN (SCREW INSTALLED WAS TOO LONG).  FLUSH PATCH APPROX 9 INCH X 4 INCH, WITH	 DOUBLER, WAS INSTALLED AFTER REMOVING THE WING TO GAIN ACCESS TO AREA.  WING REMOVAL NECESSARY DUE TO FILLET ASSY OF TH	E FUSELAGE WHICH OVERLAPS WING AND COVER THE RIVET LINE OF EXTREME IB RIB.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002042200036	20020422	00036	CE  	2002	4	22	2002FA0000508    	1	20020330	G	3260	13771	SWITCH          			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG UPLOCK	FAILED          	C				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	05	732YK	3121 				21061879				GEAR FAILED TO INDICATE UP AND LOCKED ON RETRACTION.						1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2002042300024	20020423	00024	CE  	2002	4	23	2002FA0000509    	1	20020320	G	2421	E0FF10300BA	ALTERNATOR      			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	2177S	4    				21061138				ALTERNATOR UNIT FAILED ENROUTE.						1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2002042300025	20020423	00025	SO  	2002	4	23	2002FA0000511    	1	20020322	G	3010	210174	POPPET VALVE    			LKHEED	1329  	132923E     	5263116	SO  	GARRTT	TFE731	TFE731*     	01518	WP  					NR 4 ENGINE	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	511TS	14   				5101				VALVE JUST REPLACED AFTER OVERHAUL.  VALVE INOPERATIVE, POPPET VALVE FROZEN OR STIFF TO MOVE .  CAN FEEL IT GRIND AND NO	T GOING CLOSE AFTER PUSHING POPPET.  OVERHAUL PROCESS NOT CORRECT OR NOT ENOUGH CLEAR INTERNALLY.					2	L	7	4 	4J	4	F	 	2A15    	E6WE				 
2002042300026	20020423	00026	SO  	2002	4	23	2002FA0000512    	1	20020415	G	3260		SWITCH          			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360A1A    	41514	EA  					MLG DOWN	BROKEN          	D				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			SO	16	3788T	4000 				28R30101				NOSE AND RIGHT MAIN GEAR COLLAPSED ON LANDING.  GEAR SWING AFTER INCIDENT APPEARED NORMAL WITH FAA OBSERVER.  FURTHER IN	SPECTION FOUND RIGHT MAIN SWITCH DAMAGED AND COMING ON EARLY.  NOSE SWITCH INTERMITTENTLY EARLY.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002042300027	20020423	00027	CE  	2002	4	23	2002FA0000513    	1	20020319	G	2110		COMPRESSOR      			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					AIR CONDITIONER	BROKEN          	B			EHHR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			EA	17	74VR	1000 				LW135				AFTER LANDING AND ENGINE SHUTDOWN, AIRCRAFT OBSERVED TO HAVE SMOKE COMING OUT OF NOSE SECTION.  ON INSPECTION, FOUND AIR	 CONDITIONER COMPRESSOR SEIZED.  SMOKE WAS CAUSED BY COMPRESSOR DRIVE MOTOR BELTS DRIVING THE SEIZED PULLEY ON COMPRESSO	R, MELTING THE BELTS.  OPENING COMPRESSOR FOUND CONNECTING ROD PIECES IN BOTTOM OF CRANKCASE.				1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2002042400034	20020424	00034	EU  	2002	4	24	2002FA0000514    	1	20020412	G	3234	GH115TA	HANDLE          			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					MLG	FAILED          	G			VJ3R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	07	862AF	87   				85002	L2802448A			LANDING GEAR WAS CYCLED TO THE DOWN POSITION IN FLIGHT, BOTH MAIN GEAR DOWN LIGHTS CAME ON AND THE NOSE GEAR DOWN LIGHTS	 CAME ON AND THE NOSE GEAR DOWN LIGHTS FAILED TO COME ON.  THE SYSTEM WAS TESTED IAW FLIGHT MANUAL PROCEDURES AND THE LI	GHTS FOR THE NOSE GEAR DOWN HAD FAILED.  A SAFE LANDING WAS MADE.  INSPECTION OF THE GEAR SYSTEM FOUND THAT BOTH LIGHTS 	IN THE GEAR HANDLE HAD FAILED.  NEW GEAR HANDLE CONTROL ASSEMBLY WAS INSTALLED, SYSTEM CHECKED NORMAL.			1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002042400035	20020424	00035	EU  	2002	4	24	2002FA0000515    	1	20020415	G	2913	X030001	PUMP            			GROB  	ASTIR 	G102ASTIR   	1660104	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					HYD SYSTEM	FAILED          	G			VJ3R	O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	865AF	14   				85005	L2826448A			THE LANDING GEAR WAS SWLECTED IN FLIGHT TO THE DOWN POSITION; THE RIGHT MAIN GEAR LIGHT FAILED TO COME ON IN THE DOWN AN	D LOCKED POSITION.  THE AIRCRAFT WAS YAWED AND THE DOWN AND LOCK GEAR LIGHT CAME ON.  A SAFE LANDING WAS MADE.  AIRCRAFT	 WAS TAKEN TO MAINTENANCE AND PLACED ON JACKS, THE SYSTEM CHECKED AND FOUND THE GEAR HYDRAULIC MOTOR HAD FAILED (BURNED 	UP), A NEW HYDRAULIC ASSEMBLY WAS INSTALLED.  THE LANDING GEAR WAS CYCLED IAW MM, SYSTEM CHECKED NORMAL.			1	K	0	0 	  	3	O	 	G33EU   	1E4				 
2002042400036	20020424	00036	SO  	2002	4	24	2002FA0000517    	1	20020416	G	3213	6682000	NUT             			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360A1A    	41514	EA  					MAIN AXLE	MISINSTALLED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8288L	5554 				28R8118011				DURING ANNUAL INSPECTION, MAIN AXLE NUTS WERE INSTALLED BACKWARDS.  ONLY WAY COTTER KEY HOLES WOULD ALIGN, WAS TO BACK O	FF NUT TO WHERE MAIN WHEEL WAS NOT TIGHT ON AXLE.  ONLY THING RETAINING WHEEL ONTO AXLE WAS BRAKE ASSEMBLY.  MAIN AXLE T	ABS WERE DEEPLY GROOVED BY WHEEL BEARINGS.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002042400037	20020424	00037	SO  	2002	4	24	2002FA0000518    	1	20020416	G	3220	6705403	TRUNNION        			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8288L	5554 				28R8118011				DURING ANNUAL INSPECTION, FOUND NOSE STRUT HOUSING BOSS WHERE LOWER DRAG LINK ATTACHES, BROKEN.  HALF OF BOSS WAS MISSIN	G, THE ASSEMBLY WAS SO COVERED WITH GREASE, MISSING PORTION OF BOSS WASNT VISABLE UNTIL CLEANED OFF.  UNKNOWN HOW LONG H	AD BEEN WHEN, SPECULATE, HARD LANDING OR MISRIGGED SYSTEM COULD HAVE CONTRIBUTED TO FAILURE.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002042400038	20020424	00038	SO  	2002	4	24	2002FA0000519    	1	20020416	G	7820	6751700	MUFFLER         			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360A1A    	41514	EA  					ENG EXHAUST	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8288L	1409 				28R8118011				DURING ANNUAL INSPECTION, CRACK AROUND REAR MUFFLER LEFT HAND STEEL TUBE FOUND.  STEEL TUBE AND MUFFLER INTERNAL FLAME T	UBE COULD BE PULLED OUT OF MUFFLER END.  BOTH MUFFLER INTERNAL FLAME TUBES FOUND DISTORTED,  WHEN VIEWED FROM TAIL PIPE.	  REAR MUFFLER TT IN SERVICE IS 1409 HOURS.  FRONT MUFFLER TT IN SERVICE IS 1306 HOURS.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002042400050	20020424	00050	SO  	2002	4	24	2002FA0000520    	1	20020416	G	7920	LCV13775660746	IMPELLER        			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					OIL PUMP	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8288L	2690 				28R8118011	L2208451A			DURING ANNUAL INSPECTION, FOUND OIL PUMP ASSEMBLY CONTAINED ALUMINUM DRIVEN IMPELLER AND INTERNAL IRON DRIVEN IMPELLER. 	AD REQUIRES REPLACEMENT OF THESE IMPELLERS. TBO, HAD MISTAKENLY BEEN CARRIED FORWARD. REPLACEMENT PAST DUE BY 690 HOURS 	AND 18 MONTHS.  MODERATE TO SEVERE WEAR ON DRIVE IMPELLERS AND SHAFT.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002042400051	20020424	00051	EU  	2002	4	24	2002FA0000521    	1	20020319	G	2435	410965	BEARING         			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE7312B    	 	WP  					STARTER GEN	OVERHEATED      	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	138M	253  								THE SUBJECT STARTER-GEN WAS TEMPORARILY REMOVED FROM SERVICE FOR A PRECAUTIONARY BEARING INSPECTION.  NEW BEARINGS, FROM	 AN AUXILEC APPROVED VENDOR, WERE INSTALLED DURING THAT OVERHAUL. INSPECTION OF THE SUBJECT BEARING BY THE OVERHAUL FACI	LITY FOUND IT STIFF TO ROTATE AND FELT  VERY ROUGH WHEN ROTATED. THE SEALS WERE REMOVED AND THE GREASE (WHITE COLOR) APP	EARED NORMAL. THE BEARING HAD NO RADIAL CLEARANCE, AND THE INNER RACE WAS OVERHEATING AS INDICATED BY LOCALIZED DARK PUR	PLE TO LIGHT BLUE COLOR. THE COLOR OF THE BEARING RETAINERS ALSO INDICATED OVERHEATING. THE ARMATURE SHAFT SHOWED NO EVI	DENCE OF THE BEARING RACE SPINNING. A NEW BEARING WAS INSTALLED AND THE PART WAS RETURNED TO SERVICE.	2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2002042500052	20020425	00052	CE  	2002	4	25	2002FA0000522    	1	20020311	G	5320		SUPPORT         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	3246M	18394				402C0294				CRACKS IN PILOTS SEAT PEDESTAL SUPPORTS FOUND AT ANNUAL INSPECTION.  SUPPORTS AREA BOX STRUCTURE AND CRACKS CANNOT BE SE	EN ON NORMAL VISUAL INSPECTION.  A CRACK IN THE FLOOR SKIN COVERING THESE SUPPORTS WAS FOUND.  WHEN FLOOR WAS CUT AND FO	LDED UP, THE SEVERITY OF THE PROBLEM WAS REVEALED.  INSPECT FOR EXCESS MOVEMENT WHERE THE PEDESTAL ATTACHES THROUGH THE 	FLOOR.  THIS MAY INDICATE PROBLEMS BELOW THE FLOOR.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002042500053	20020425	00053	CE  	2002	4	25	2002FA0000523    	1	20020311	G	5320		SUPPORT         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	3246M	18394				402C0294				CRACKS IN PILOTS SEAT PEDESTAL SUPPORTS FOUND AT ANNUAL INSPECTION.  SUPPORTS AREA BOX STRUCTURE AND CRACKS CANNOT BE SE	EN ON NORMAL VISUAL INSPECTION.  A CRACK IN THE FLOOR SKIN COVERING THESE SUPPORTS WAS FOUND.  WHEN FLOOR WAS CUT AND FO	LDED UP, THE SEVERITY OF THE PROBLEM WAS REVEALED.  INSPECT FOR EXCESS MOVEMENT WHERE THE PEDESTAL ATTACHES THROUGH THE 	FLOOR.  THIS MAY INDICATE PROBLEMS BELOW THE FLOOR.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002042500055	20020425	00055	CE  	2002	4	25	2002FA0000525    	1	20020401	G	2750	14601007	CABLE           			CESSNA	336   	336         	2075602	CE  	CONT  	IO360 	IO360*      	17025	CE  					RT BELLCRANK	BROKEN          	G				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			EA	09	108RJ	2892 				3360067				ON FINAL APPROACH, AIRCRAFT EXPERIENCED A SPLIT FLAP CONDITION, CAUSED BY BROKEN CABLE ASSEMBLY.  FLAP ACTUATOR INBOARD 	(PN 14601007).  CABLE HAD BROKEN ON RIGHT SIDE, 1 INCH FROM CABLE END, AT BELLCRANK ENTRY POINT.  INSPECTION OF LEFT SID	E FLAP CABLE ASSEMBLY WITH A MIRROR, REVEALED NO NOTICEABLE DAMAGE.  ALL CABLES FOR RIGHT AND LEFT FLAP SYSTEM WERE REMO	VED AND INSPECTED.  LEFT CABLE ASSEMBLY.  FLAP ACTUATOR INBOARD, WAS FRAYED AT SAME CONTACT POINT AS RIGHT, (NOT DETECTE	D BY MIRROR INSPECTION).  DUE TO AREA OF BREAKAGE, HAVING LIMITED POSSIBLY FOR VISUAL INSPECTION, RECOMMEND SET TIME PER	IOD FOR CABLES TO BE REMOVED FOR INSPECTION OR TIME IN SERVICE REQUIREMENTS SET FOR REMOVAL.	1	H	7	2 	3O	3	O	 	A2CE    	E1CE				 
2002042500056	20020425	00056	SO  	2002	4	25	2002FA0000526    	1	20020326	G	7160	99047000	ADAPTER         			PIPER 	PA28  	PA28R201    	7102816	SO  										INDUCTION SYSTEM	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	670X	272  				2844055				THE ALTERNATE AIR DOOR HINGE IS ATTACHED BY 3 (AN470AD3) SOLID RIVETS.  THE 3 RIVETS SHEARED AND THE AIR DOOR BECAME LOD	GED IN THE FUEL CONTROL SERVO THROTTLE BODY.  THIS OCCURRED ON TAKEOFF AND THE PILOT WAS ABLE TO SET THE AIRCRAFT BACK D	OWN SAFELY.  RECOEND LARGER SUPPORT FOR HINGE AND MORE RIVETS OF LARGER SIZE.				1	L	7	1 	3O			 	2A13    					 
2002042500057	20020425	00057	SW  	2002	4	25	2002FA0000528    	1	20020313	G	5711		SPAR            			BBAVIA	7     	7GC         	2110126	SW  	LYC   	O290  	O290*       	41506	EA  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7587E	1725 				7GC19				WHIN WAS INSPECTED PRIOR TO RECOVER.  THIS INSPECTION SHOWED NO CRACKS.  WING WAS RECOVERED AND STORED PRIOR TO SINTALLA	TION.  THE WIND BLEW WING AND STORAGE RACK OVER.  THE RACK FELL ONTO THE WING.  AN INSPECTION WAS DONE.  INSPECTION FOUN	D TWO CRACKS AT THE BUTT END OF THE SPAR, ONE  CRACK WAS UNDER THE WING ATTACH FITTING AND ONE CRACK JUST BELOW THE FIRS	T.  BOTH CRACKS IN LINE WITH THE BOLT HOLES AS SHOW IN SL406, THE SPAR WAS CRACKED BADLY ENOUGH THAT  A .006 FEELER GAUG	E COULD BE PUSHED IN ABOUT 1 INCH.  THE SPAR MUST BE REPLACED.		1	H	7	1 	3O	3	O	 	A759    	E229				 
2002042500058	20020425	00058		2002	4	25	2002FA0000529    	4	20020411	G	3417	7000700964	ADC             			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					COCKPIT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	63MU					1152				DIGITAL AIR DATA COMPUTER, INOPERATIVE.						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2002042500059	20020425	00059		2002	4	25	2002FA0000530    	4	20020411	G	3417	5224701001	ADC             			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					COCKPIT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	668JT					162				AIR DATA COMPUTER, INTERMITTENT, FAILED.						2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2002042500060	20020425	00060	EU  	2002	4	25	2002FA0000531    	1	20020220	G	6220	350A31190703	STARFLEX        			SNIAS 	350   	AS350B3     	8680954	EU  										M/R HEAD	DEBONDED        	D			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	105LN	1157 				3249				BUSHING ON END OF STARFLEX HAVE DEBONDED.						1	G	7	1 	3U			 	H9EU    					 
2002042500061	20020425	00061	EU  	2002	4	25	2002FA0000532    	1	20020327	G	6700		BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										YAW CONTROL	FROZEN          	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6103X	3849 				2723				DURING A SCHEDULED INSPECTION ON THIS AIRCRAFT, AEC SL WAS BEING COMPLIED WITH.  THIS LETTER HAS LOOKING FOR OUT OF ROUN	D HOLE CONDITION ON THE YAW CONTROL LOAD COMPENSATOR LEVER.  THE ARM ONLY MOVES APPROXIMATELY .30 DEGREES.  WHEN THE CON	TROL WAS REMOVED, IT WAS FOUND THAT THE BEARING HAD FROZEN.  IT STILL MOVED IN ITS .30 DEGREE RANGE BUT THE REST OF THE 	BEARING WAS FROZEN AND ROUGH.			1	G	7	1 	3U			 	H9EU    					 
2002042500062	20020425	00062	CE  	2002	4	25	2002FA0000533    	1	20020325	G	2742		BUSHING         	BEECH       		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ACTUATOR	LOOSE           	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	311MP	3246 			BB1112	BB1112				DURING A SCHEDULED CORROSION INSPECTION THE RIGHT ELEVATOR WAS REMOVED.  UPON REMOVAL THE BUSHING IN THE END OF THE ACTU	ATOR WAS FOUND TO BE LOOSE ON THE SHAFT.  WITH THIS BUSHING NOT INSTALLED THE POSSIBILITY OF TAB FLUTTER OR NOT ALLOWING	 THE TAB ITS FULL MOVEMENT IS POSSIBLE.  MFG SHOULD INSTALL A ROLL PIN TO HOLD THIS BUSHING IN PLACE.  A ONE-TIME INSPEC	TION SHOULD BE DOEN ON THESE ACTUATORS TO MAKE SURE THIS IS IN PLACE AS THIS IS A HARD AREA TO SEE ON A DAILY INSPECTION	.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002042600031	20020426	00031	CE  	2002	4	26	2002FA0000534    	1	20020402	G	2150	10138001313	A/C PACK        			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					CABIN	MALFUNCTIONED   	B			DFZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	87SA					BB1089				FLOW PACK HAS LOW FLOW TO CABIN.						1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2002042600032	20020426	00032	CE  	2002	4	26	2002FA0000535    	1	20020206	G	2910		WIRE            			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					POWERPACK	CUT             	B			Y4MR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	09	6359Y					21064351				AIRCRAFT HAD THE LEFT GEAR COLLAPSE ON ROLLOUT.  PLACED AIRCRAFT ON JACKS AND CHECKED RETRACT SYSTEM.  FOUND POWER PACK 	NOT RUNNING DUE TO A CUT WIRE IN THE NOSE WHEEL WELL.  THE WIRING TO THE NOSE DOWN LOCK SWITCH WAS MISROUTED AND WAS CUT	 IN THE DOWN LOCK ASSEMBLY.  DUE TO THE CUT WIRE, THE LANDING GEAR MOTOR STOPPED RUNNING, THE GEAR POSITION GREEN LIGHTS	 FAILED AND THE WARNING HORN DID NOT SOUND.  ALL THESE SYSTEMS ARE CONTROLLED BY THE SAME CIRCUIT BREAKER.  REPAIRED WIR	ING AND CHECKED SYSTEMS AND FOUND THEM ALL OPERATING NORMALLY.		1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2002042600033	20020426	00033		2002	4	26	2002FA0000536    	4	20020416	G	3418	45150320	SENSOR          																	AOA SENSOR	MISINSTALLED    	B			OZRR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	11										AOA SENSOR, AN ANGLE OF ATTACK (AOA) SENSOR WAS IMPROPERLY INSTALLED ON AN  AIRCRAFT BY INSTALLING IT ONE HOLE OFF IN TH	E COUNTER CLOCKWISE DIRECTION.  THE IMPROPER INSTALLATION OF THE AOA SENSOR RESULTED IN A FALSE STALL WARNING INDICATION	 DIRECTLY AFTER TAKEOFF.  DISPARITIES BETWEEN THE A320 AMM 34-11-19, AND THE PHYSICAL CONDITION OF THE AIRFRAME AND THE 	PART, DIRECTLY CONTRIBUTED TOT THE IMPROPER INSTALLATION.  THE AMM INDICATES THAT THE SENSOR ITSELF HAS ONLY ONE COUNTER	 SUNK HOLE, HOWEVER, THE SENSOR ACTUALLY HAS EIGHT MOUNTING HOLES IN THE AIRFRAME STRUCTURE THAT WOULD ALLOW FOR THE INS	TALLATION OF THE ALIGNMENT PINS, HOWEVER THIS TOO IN INCORRECT.														 
2002042600034	20020426	00034	EU  	2002	4	26	2002FA0000537    	1	20020308	G	2520	5048284011544185	SEAT BELT       			ISRAEL	GALAXY	GALAXY      	4500307	EU  										CABIN	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	83EJ					009				PASSENGER SEAT BELT BUCKLE FALLS APART.  THIS IS THE 4TH INSTANCE OF THIS.						2	L	7	2 	4F			RT	A53NM   					 
2002042600065	20020426	00065	EA  	2002	4	26	2002FA0000538    	2	20020402	G	7322		FLOAT           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					CARBURETOR	INOPERATIVE     	B			ECQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	611FT					2841223	L809339A			CARBURETOR WAS FOUND INOPERABLE CONDITION ON AIRCRAFT.  UPON INSPECTION, A PARK FUEL STAIN WAS NOTED DEAR AIRBOX IN THE 	CARBURETOR THROAT.  CLOSER INSPECTION REVEALED A SMALL HOLE IN THROAT PASSING INTO BOWL.  OTHER SMALL CRACKS AND A VERY 	ROUGH CASTING WAS NOTICED IN SAME AREA OF THROAT.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002050600056	20020506	00056	SO  	2002	5	6	2002FA0000539    	1	20020330	G	2750	552615	MOTOR           			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					TE FLAPS	INOPERATIVE     	B			FCPR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	09	4163E	352  				3257136				FLAPS INOPERATIVE, TROUBLESHOOTING, FOUND FLAP MOTOR INOPERATIVE.  REPLACED MOTOR ASSEMBLY.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2002050600057	20020506	00057	EA  	2002	5	6	2002FA0000540    	2	20020402	G	8550	CP48110	OIL FILTER      								LYC   	O360  	O360A4M     	41514	EA  					ENGINE	MISMANUFACTURED 	B			UC2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19										DURING A PREINSTALLATION INSPECTION ON A MFG. SPIN ON OIL FILTER THE CENTER ATTACH STUD WAS FOUND TO BE ONLY FINGER TIGH	T.  THIS DEFECT COULD HAVE CAUSED LOSS OF ENGINE OIL AND POSSIBLY ENGINE FAILURE IF THE DEFECT GOES UNDETECTED.										3	O			E286				 
2002050600058	20020506	00058	EU  	2002	5	6	2002FA0000541    	1	20020417	G	2720	27220	CONTROL CABLE   			AIMM  	AMT200	AMT200      	05630AZ	EU  										RT RUDDER PEDAL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	757DM	900  				200047				RIGHT RUDDER PEDAL CABLE, BROKEN.						1	L	7	1 	3I			NC	        					 
2002050600059	20020506	00059	CE  	2002	5	6	2002FA0000542    	1	20020426	G	2710	0510105224	CONTROL CABLE   			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320A2D     	41508	EA  					AILERON	BROKEN          	G				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			SO	15	75908	7000 				17268032				LEFT AILERON DIRECT CONTROL CABLE SEPARATED IN FLIGHT RESULTING IN A FATAL ACCIDENT.  THE CABLE P/N 0510105-224 WAS VERY	 BADLY RUSTED AT THE POINT OF FAILURE LOCATED ABOVE THE RIGHT DOORPOST WHERE THE CONTROL CABLE RIDES OVER A PULLEY.  THE	 PULLEY IN THIS AREA WAS VERY STIFF DUE TO A BADLY CORRODED BEARING.  THIS APPEARS TO BE A RESULT OF POOR INSPECTION PRO	CEDURES.  THE DOORPOST TRIM MUST BE REMOVER AND THE HEADLINER MUST BE OPENED TO PROPERLY INSPECT THIS AREA.  IT IS A REQ	UIREMENT OF THE ANNUAL INSPECTION TO INSPECT THE FLIGHT CONTROL SYSTEMS, THE ENTIRE SYSTEM, NOT JUST THE EASY PART.  THI	NK TWICE BEFORE YOU SIGN OFF YOUR NEXT INSPECTION.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002050600096	20020506	00096	GL  	2002	5	6	2002FA0000544    	2	20020322	G	7532		BLEED VALVE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	ERRATIC         	B			EOOR	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			AL	03	5074R		450  			1151D	CAE830448			DURING FLIGHT THE COMPRESSOR STALLED A COUPLE OF TIMES.  BOTH DURING A POWER CHANGE AND IN A STABLE POWER SETTING.  REMO	VED BLEED VALVE AND REPLACED WITH A SERVICEABLE UNIT AND THE PROBLEM WAS CORRECTED.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002050600097	20020506	00097	WP  	2002	5	6	2002FA0000545    	1	20020315	G	3213	369H600152	STRUT           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					MLG	BROKEN          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90431					1100833D				FOUND LANDING STRUT BROKEN AT THE DRAG BRACE BOLT HOLE.  REMOVED AND REPLACED STRUT.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002050600098	20020506	00098	CE  	2002	5	6	2002FA0000546    	1	20020416	G	2432	G35	BATTERY         			BEECH 	35    	M35         	1151526	CE  	CONT  	O470  	IO470*      	17026	SO  					MAIN	SHORTED         	B			NM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	711DU					D6538				LANDING GEAR FAILED TO EXTEND ALL THE WAY.  AIRCRAFT LOST ELECTRICAL POWER.  REMOVED BATTERY AND FOUND LOW VOLTS WITH NO	 CAPACITY, BATTERY WOULD NOT CHARGE ON BENCH INTERNALLY SHORTED INSTALLED NEW BATTERY, AIRCRAFT AND FOUND.  FIELD CIRCUI	T BREAKER POPPED RESET AND CHARGING SYSTEM OPS CHECK NORMAL.  GEAR SWING WAS NORMAL AFTER REPLACING BENT LEFT GEAR PUSH 	ROD EMERGENCY EXTENSION NORMAL.			1	L	7	1 	3O	3	O	 	3A15    	E1CE				 
2002050600099	20020506	00099	WP  	2002	5	6	2002FA0000547    	1	20020221	G	6330	369A2029	STUD            			HUGHES	369   	369D        	4470706	WP  										XMSN MOUNT	CRACKED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	CGPHC	9759 				180257D				FOUND ON OF THE FOUR MAIN ROTOR TRANSMISSION MOUNTING STUDS CRACKED IN THE RADIUS OF THE SHOULDER TO THE WRENCHING FLAT 	FLANGE.  REMOVED AND REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U			 	H3WE    					 
2002050600110	20020506	00110	CE  	2002	5	6	2002FA0000549    	1	20020329	G	5314	11498002412	KEELBEAM        			BEECH 	1900  	1900D       	1154162	CE  										FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	08	61HA					UE175				SMALL CRACK FOUND ON RIGHT HAND FORWARD OUTBOARD WHEEL WELL KEEL AT UPPER GEAR FENDER SUPPORT ANGLE (SUPPORT ANGLE IS PA	RT OF KEEL CASTING).					2	L	7	2 	4T			RT	A24CE   					 
2002050600115	20020506	00115	GL  	2002	5	6	2002FA0000550    	3	20020422	G	6114	D6382	HUB             			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	HARTZL	H3B3M	HCB3M       	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	701SE	3450 	3063 			208B0701				PROPELLER WAS DISASSEMBLED AND INSPECTED FOR OVERHAUL.  PROPELLER HUB WAS STRIPPED, ETCHED AND DYE PENETRANT INSPECTED. 	 INDICATIONS OF CRACKS WERE APPEARANT AT 5 LOCATIONS ON THE REAR HALF OF THE HUB NEXT TO THE REAR BETA ROD BUSHING SOCKE	TS.  EDDY CURRENT INSPECTION VERIFIED ALL LOCATIONS WERE CRACKED.  PART WAS RETIRED FROM SERVICE.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P9NE	 
2002050600116	20020506	00116	EA  	2002	5	6	2002FA0000551    	2	20020401	G	8550	S33461	GASKET          			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					VACUUM PUMP	FAILED          	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AL	03	7254H	670  				20608036				DURING CRUISE FLIGHT LOST OIL PRESSURE INDICATION, MADE A PRECAUTIONARY LANDING ON A SNOW COVERED REMOTE RUNWAY, AIRCRAF	T NOSED DOWN AND HAD A PROP STRIKE, BENDING BLADES.  THE MECHANIC REMOVED THE ENGINE, DISCOVERED THE LOWER VACUUM PUMP G	ASKET WAS BLOWN OUT.  THIS BLOWN GASKET ALLOWED OIL TO BE PUMPED OUT PAST THE DRIVE ASSEMBLY INTO THE LOWER COWL.  LOSS 	OF OIL CAUSED NO OIL PRESSURE CONDITION.  NOTE: A ONE TIME INSPECTION OF THE LOWER VACUUM PUMP INSTALLATION  1) PROPER G	ASKET  2) PROPER NUT TORQUE.		1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2002050600117	20020506	00117		2002	5	6	2002FA0000554    	4	20020409	G	2561	KSD35P0723105	LIFE VEST       																	CABIN	FAILED          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED, MFG ECOMMENDED PRESSURE TEST.  DOM: FEB 1985																			 
2002050600118	20020506	00118	SO  	2002	5	6	2002FA0000555    	2	20020404	G	8530	SA52000A20P	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENGINE	LEAKING         	D			JZRR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	323GB	63   				E647	280914R			NOTICED OIL SEEPAGE BETWEEN THE HEAD AND BARREL OF THE NR 5 CYLINDER BETWEEN THE PUSH ROD TUBES DURING THE FIRST OIL CHA	NGE.  DURING THE SECOND OIL CHANGE, NOTICED A SUBSTANTIAL INCREASE IN OIL LEAKAGE AT THE SAME PLACE ON THE NR 5 CYLINDER	, ALSO NOTICED OIL LEAKING FROM THE NR 3 CYLINDER IN THE SAME AREA.  BOTH CYLINDER REPLACED AND RETURNED TO MFG.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002050600119	20020506	00119	SO  	2002	5	6	2002FA0000556    	2	20020404	G	8530	SA52000A2OP	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENGINE	LEAKING         	B			JZRR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	323GB	63   				E647	280914R			NOTICED OIL SEPPAGE BETWEEN THE HEAD AND BARREL OF THE NR 5 CYLINDER BETWEEN THE PUSH ROD TUBES DURING THE FIRST OIL CHA	NGE.  DURING THE SECOND OIL CHANGE, NOTICED A SUBSTANTIAL INCREASE IN OIL LEAKAGE AT THE SAME PLACE ON THE NR 5 CYLINDER	, ALSO NOTICED OIL LEAKING FROM THE NR 3 CYLINDER IN THE SAME AREA.  BOTH CYLINDERS REPLACED AND RETURNED TO MFG.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002050600120	20020506	00120	NE  	2002	5	6	2002FA0000557    	2	20020429	G	7240	9824053225	BOLT            								TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	4068W	1931 	1931 				9444			AFTER A MAINT FLIGHT, FOLLOWING THE CLEANING OF THE NR 4 BEARING, THE MAINT TECH FOUND THE OUTSIDE OF THE ENGINE COWLING	 DELAMINATED. DURING INSPECTION TO DETERMINE THE CAUSE, THE MECHANIC NOTICED THE ENGINE SPLIT LINE BETWEEN MO3 AND MO4 D	EVELOPED A BLEED AIR LEAK. UPON EXAMINATION OF THE ATTACHMENT FLANGE BOLTS ONE WAS FOUND TO BE BROKEN IN THE AREA OF THE	 LEAK.  THE BOLT HAD BROKEN FAR ENOUGH INTO THE CASE THAT THE MODULES WHERE REMOVED AND SENT TO TURBOMECA TO ELIMINATE T	HE POSSIBILITY OF FURTHER DAMAGE. THE ENGINE WAS REASSEMBLED IAW MM CHAPTER 72 AND ALL PROCEDURES WHERE FOLLOWED, QUALIT	Y CONTROL WAS ON HAND AND VERIFIED ALL PROCEDURES WHERE FOLLOWED DURING THE ASSEMBLY PROCESS.						3	U			E19EU				 
2002050600147	20020506	00147	CE  	2002	5	6	2002FA0000566    	1	20020430	G	3233	98820152	HOUSING         			CESSNA	172   	172RG       	2072438	CE  										MLG ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5169V	7794 	496  			0458				ACCOMPLISHED 500 HR REINSPECTION OF THE LANDING GEAR ACTUATOR HOUSINGS.  FOUND THE LEFT AND RIGHT HOUSINGS TO BE CRACKED	.  THE RIGHT HOUSING WAS REPLACED AT THE INITIAL INSPECTION WITH A USED, SERVICEABLE HOUSING P/N: 9882015-2.  REPLACED B	OTH HOUSINGS WITH NEW STYLE HOUSINGS P/N: 1281001-6.				1	H	7	1 	3O			 	3A17    					 
2002050600148	20020506	00148	CE  	2002	5	6	2002FA0000567    	1	20020501	G	2497		WIRE            			CESSNA	172   	172S        	2072439	CE  										VOLTAGE REG	SHORTED         	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	07						172S8202				ALTERNATOR FIELD C/B POPED IN FLIGHT. PILOT RESET C/B, SMELLED SMOKE IN THE COCKPIT, C/B POPED AGAIN. THE PILOT MADE A P	RECAUTIONARY LANDING AT MNN.  AN INVESTIGATION OF THE PROBLEM DETERMINED THAT THE RED VOLTAGE REGULATOR WIRE HAD SHORTED	 ON THE GROUNDING POST OF THE RELAY BELOW CAUSING A SHORTED WIRE FROM THAT POINT TO THE 5 AMP C/B, ALTERNATOR FIELD.				1	H	7	1 	3O			NT	3A12    					 
2002050600052	20020506	00052	EA  	2002	5	6	2002FA0000568    	2	20020501	G	7230	T102401100A	BLADE           			AIRTRC	AT500 	AT502       	0390303	SW  	PWA   	PT6   	PT6A34      	52043	EA  					COMPRESSOR DISK	FAILED          	G				C				ABORTED TAKEOFF         				G			MULTIPLE FAILURE          			TO	TAKEOFF        	1			SO	07	9185F	29   				5020206	PCE56893			DURING TAKE OFF THE ENGINE LOST ALL POWER.  ENGINE WAS SHIPPED TO CERTIFIED REPAIR STATION.  THE PRELIMINARY ANALYSIS IS	 IN THE ENGINE TURBINE SECTION:  THE COMPRESSOR TURBINE DISC P/N 3013411, S/N 2P609, HAD SEVERAL BLADES (BLADES 9,11 THR	U 19, 21, 44, AND 45) FRACTURED AT THERE ROOTS.  UNDER UNAIDED VISUAL AND MACROSCOPIC INSPECTION THE ROUTE FRACTURE SURF	ACES DISPLAYED COURSE GRANULAR FEATURES. THE BLADE P/N (T-102401-100A) BEING PREFIXED WITH A "T" DENOTES THE BLADES TO B	E NON-PWC MANUFACTURED UNITS.THESE BLADES WERE CHANGED AT LAST HSI ON 6 FEBRUARY 2002 AND HAD ONLY 28.7 HOURS TO THIS FA	ILURE.	1	L	7	1 	3T	4	T	NC	A9SW    	E4EA				 
2002050600054	20020506	00054	SO  	2002	5	6	2002FA0000569    	1	20020502	G	2711		COTTER PIN      			MAULE 	MX7   	MX7235      	5460180	SO  	LYC   	O540  	IO540*      	41532	EA  					TRIM WHEEL	MISSING         	C				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			EA	21		149  								PILOT REPORTED HE COULD NOT TRIM ALERIONS. REMOVED COVER AND FOUND BOLT HOLDING LARGE,  GEARED TRIM WHEEL WAS MISSING CO	TTER KEY AND NUT HAD BACKED OFF,  ALLOWING LARGE GEAR TO SLIDE TO SIDE ABOUT 3/8 IN.  HAD TO COME FROM FACTORY THIS WAY.	 TIGHTENED NUT AND PLACED COTTER KEY IN SLOT.				1	H	7	1 	3O	3	O	NC	3A23    	1E4				 
2002050700003	20020507	00003	CE  	2002	5	7	2002FA0000570    	1	20020416	G	3213		SNAP RING       			BEECH 	50    	D50         	1152512	CE  										MLG STRUT	FAILED          	D			MJ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	632Z					DH113				AIRCRAFT WAS PARKED IN HANGAR, NO MAINTENANCE BEING PERFORMED.  UPON 1ST INVESTIGATION LT MAIN LANDING GEAR STRUT WAS BO	TTOMED.  UPON FURTHER INVESTIGATION UPPER STRUT CAP SNAP RING HAD COME LOOSE AND CAP EJECTED THROUGH UPPER  WING SKIN CA	USING A 3 INCH HOLE IN UPPER WING SKIN.  NO OTHER DAMAGE NOTED ON AIRCRAFT.  UPON FURTHER INSPECTION NO SIGN OF COMPONEN	T FAILURE TO LEFT MAIN LANDING GEAR STRUT NOTED.			1	L	7	2 	3O			 	5A4     					 
2002050700001	20020507	00001	EU  	2002	5	7	2002FA0000575    	1	20020506	G	5730	ER863072500	SKIN            			RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  					WING	DELAMINATED     	B				A				UNSCHED LANDING         				K			FLUID LOSS                			AB	AEROBATIC      	1			WP	28	161FC	504  				133				WING SKIN DELAMINATION OCCURRED IN FLIGHT.  CRACKS IN PAINT AND FUEL SEEPAGE FROM AREA WAS REASON FOR DISCOVERY.  DELAMI	NATION AREA IS 72 INCHES OUTBOARD ON TOP SIDE OF RIGHT WING AND EXTENDS APPROXIMATELY 30 INCHES FURTHER OUTBOARD.  DELAM	INATION AREA STARTS 2.25 INCHES AFT OF THE LEADING EDGE AND EXTENDS 11.5 INCHES AFT CORDWISE.  THIS PROBLEM IS ALSO DEVE	LOPING IN TWO OTHER AIRCRAFT OF THE SAME MODEL, AND OPERATED BY THE SAME OWNER.  CAUSE UNKNOWN AT THIS TIME, BUT COULD B	E FUEL TANK-RELATED DUE TO THE AREA OF DAMAGE.  AIRCRAFT IS GROUNDED AND AWAITING REPAIR INSTRUCTIONS FROM THE MANUFACTU	RER.	1	M	7	1 	3O	3	O	NC	EA67U   	1E4				 
2002050700002	20020507	00002	EU  	2002	5	7	2002FA0000577    	1	20020506	G	5700	ER863072500	SKIN            			EXTRA 	EA300 	EA300       	70218DI	EU  										WING	DELAMINATED     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	477SF	210  				088				POSSIBLE WING SKIN DELAMINATION DISCOVERED.  CRACKS IN PAINT IS REASON FOR DISCOVERY.  POSSIBLE DELAMINATION AREA IS 72"	 OUTBOARD ON TOP SIDE OF RIGHT WING AND EXTENDS APPROXIMATELY 30" FURTHER OUTBOARD.  DELAMINAITON AREA STARTS 2.25" AFT 	OF THE LEADING EDGE AND EXTENDS 11.5" AFT CORDWISE.  ACTUAL DELAMINATION FOUND IN TWO OTHER AIRCRAFT OF THE SAME MODEL, 	AND OPERATED BY THE SAME OWNER.  CAUSE UNKNOWN AT THIS TIME, BUT COULD BE FUEL TANK RELATED DUE TO THE AREA OF DAMAGE.			1	M	7	1 	3O			NC	A67EU   					 
2002051400036	20020514	00036	GL  	2002	5	14	2002FA0000578    	1	20020419	G	7810		BAFFLE          			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360A1D     	41514	EA  					EXHAUST DUCT	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	37HY	588  				2037				REMOVED MUFFLER/ EXHAUST DUCT ASSEMBLY INTERNAL BAFFLES MISSING,  AND NR 4 CYLINDER LOWER SLIP JOINT LEAKING.						1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2002051400037	20020514	00037	GL  	2002	5	14	2002FA0000579    	1	20020419	G	7810	35651	SLIP JOINT      			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360A1D     	41514	EA  					EXHAUST DUCT	LEAKING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	37HY	588  				2037				REMOVED MUFFLER/ EXHAUST DUCT ASSEMBLY INTERNAL BAFFLES MISSING, AND NR 4 CYLINDER LOWER SLIP JOINT LEAKING.						1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2002051400038	20020514	00038	EU  	2002	5	14	2002FA0000580    	1	20020412	G	2910	F10A751108	LINE            			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HYD SYSTEM	CHAFED          	B			UO2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19	42EH					28				NR 1 HYDRAULIC SYSTEM LOST ALL FLUID ON FLIGHT.  DISCOVERED HYDRAULIC LINE CHAFFED THROUGH.  LINE HAD CHAFFED AGAINST AN	OTHER LINE (PN F10A751127) IN AFT BAY.  INSPECT SYSTEM COMPONENTS FOR POTENTIAL DAMAGE.					2	L	7	2 	4F	4	F	 	A33EU   	E6WE				 
2002051400040	20020514	00040	SO  	2002	5	14	2002FA0000583    	2	20020402	G	7314		SPRING          			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					FUEL PUMP	MISINSTALLED    	B			G6NR	K				NONE                    				L	W		NO TEST                   	INADEQUATE Q C            		IN	INSP/MAINT     	1			CE	09	246MF					421C1406				AUXILIARY FUEL PUMP  WAS RECEIVED NEW FROM SUPPLIER.  ONCE INSTALLED , IT FAILED MFG SM CHECK .  WHEN REMOVED FOR BENCH 	CHECK, IT WAS DISCOVERED, SPRING IN THE OUTLET SIDE IS MISINSTALLED.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2002051400041	20020514	00041	EA  	2002	5	14	2002FA0000586    	2	20020301	G	8520		CONNECTING ROD  			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					ENGINE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	51657	200  				1097	L2006151A			NR 2 CONNECTING ROD BOLT FAILED CAUSING CONNECTING ROD TO GO THROUGH CRANK CASE CAUSING MAJOR ENGINE FAILURE.  ENGINE DE	STROYED.  TOP OF BOLT FAILED CAUSING ROD CAP TO BEND BACK AND EVENTUALLY FAIL.  THREADED END OF THE BOLT FOUND IN BOTTOM	 OF ENGINE CASE IN GOOD CONDITION.  NO SIGN OF OVERREV COULD BE FOUND IN OTHER BOLTS OR RODS.				1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2002050900059	20020509	00059	WP  	2002	5	9	2002FA0000587    	2	20020504	G	7200	30756842	RETAINER        			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					NR 1 ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	523AC	1697 				139	P101216			UPON AIRCRAFT ARRIVAL AND SUBSEQUENT SHUTDOWN, MECHANICS HEARD A SCRAPING AND A THUNKING SOUND FROM THE NR 1 ENGINE AS T	HE ENGINE WAS SPOOLING DOWN.  WHEN THE FAN ASSY WAS TURNED BY HAND, THE SAME NOISES CAN BE HEARD AND FELT.  INSPECTION O	F THE OIL FILTER REVEALED MANY FERROUS CHUNKS.  A SOAP ANALYSIS WAS PERFORMED AND THE METAL TURNED OUT TO BE 17-4PH : CH	UNKS.  TEARDOWN OF THE FRONT END REVEALED THAT THE NR 3 BEARING SEAL ROTOR RETAINER WAS BROKEN, WITH PARTS MISSING.  THE	 RETAINER EXHIBITED DISCOLORATION FROM OVERHEATING.  SOAP ANALYSIS 70 HOURS PRIOR WAS NORMAL.		2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2002051400042	20020514	00042	CE  	2002	5	14	2002FA0000588    	1	20020422	G	2421	646843	ALTERNATOR      			CESSNA	210   	T210L       	2073449	CE  	CONT  	O550  	IO550*      	 	SO  					ENGINE	FAILED          	B				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	05	1226M					21061272				ALTERNATOR FAILED IN FLIGHT.  PILOT SMELLED ELECTRICAL BURNING ODOR.  FLIGHT COMPLETED WITHOUT INCIDENT.  ALTERNATOR REP	LACEMENT CORRECTED PROBLEM.  THIS IS THE 2ND ALTERNATOR FAILURE ON THIS ENGINE WITHIN 300.7 HOURS.  FAILED ALTERNATOR NO	T DISASSEMBLED TO DETERMINE FAULT AT THIS FACILITY.  FAILED ALTERNATOR WAS RETURNED TO VENDOR.				1	H	7	1 	3O	3	O	 	3A21    	E3SO				 
2002051400044	20020514	00044	CE  	2002	5	14	2002FA0000589    	1	20020410	G	7160	075014421	AIR BOX         			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	3736U					18255136	849983			SEVERAL CRACKS IN HOUSING, BOTH IN ALUMINUM AND STAINLESS STEEL.  SERVICEABLE PART INSTALLED ABOUT 375 HOURS OPERATING T	IME.  SUGGEST MORE ATTENTION BE GIVEN THIS ITEM AND THE WAY IT IS ATTACHED, FOR SECURITY.  HIGH VIBRATION AREA.  CHECK P	ROPELLER FOR BALANCE.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002051400065	20020514	00065	SO  	2002	5	14	2002FA0000590    	1	20020508	G	3210		UPLOCK BRACKET  			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	SHEARED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	200VW	7556 				318052011				SHEAR FAILURE OF RIVETS ATTACHING PIPER UPLOCK BRACKETS TO ATTACHING RIB.						1	L	7	2 	3O			 	A20SO   					 
2002051500003	20020515	00003		2002	5	15	2002FA0000593    	4	20020308	G	3422	52D189	INDICATOR       			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540*      	41532	EA  					HSI	MALFUNCTIONED   	B			HI1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NE	05	2448Z	78   				20608141				ON AN ILS FREQUENCY, WITH A VALID SIGNAL THE UNIT WILL PULL THE FLAG BUT GIVE THE FLY DOWN COMMAND ALL THE TIME, EVEN WH	EN IT SHULD BE CENTERED.					1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2002051500004	20020515	00004	NM  	2002	5	15	2002FA0000594    	1	20020320	G	3240		HOUSING         			BOEING	737   	737         	UTILSYS	NM  										SHUTTLE VALVE	FATIGUED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										PIN HOLE IN MOUNT HOLE, FATIGUE.  REMOVED AND REPLACED.     (JN 166395)						2	L	7	2 	4F			RT	A16WE   					 
2002051500005	20020515	00005	NM  	2002	5	15	2002FA0000595    	1	20020320	G	3240		HOUSING         			BOEING	737   	737         	UTILSYS	NM  										SHUTTLE VALVE	PIN HOLE        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										SHUTTLE VALVE HAS A PIN HOLE IN MOUNT HOLE, FATIGUE.  REMOVED AND REPLACED.						2	L	7	2 	4F			RT	A16WE   					 
2002051500006	20020515	00006	NM  	2002	5	15	2002FA0000596    	1	20020320	G	2910		HOUSING         			BOEING	737   	737         	UTILSYS	NM  										RESTRICTOR	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSEING IS  BROKEN.  BODY IS TOO WEAK.						2	L	7	2 	4F			RT	A16WE   					 
2002051500007	20020515	00007	NM  	2002	5	15	2002FA0000597    	1	20020320	G	3230		HOUSING         			BOEING	737   	737         	UTILSYS	NM  										REGULATOR	ERODED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING EXTRUSION PORT IS ERODED.						2	L	7	2 	4F			RT	A16WE   					 
2002051500008	20020515	00008	NM  	2002	5	15	2002FA0000598    	1	20020320	G	3230	200496	HOUSING         			BOEING	737   	737*        	       	NM  										EXTRUSION PORT	ERODED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING EXTRUSION  PORT IS ERODED.						2	L	7	2 	4F			RT	A16WE   					 
2002051500009	20020515	00009	NM  	2002	5	15	2002FA0000599    	1	20020319	G	3230	654466925	HOUSING         			BOEING	737   	737200      	1384453	NM  										MODULE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										UNIT IS CRACKED IN BOTH PRIORTY PORTS.						2	L	7	2 	4F			 	A16WE   					 
2002051500010	20020515	00010	NM  	2002	5	15	2002FA0000600    	1	20020319	G	3230		HOUSING         			BOEING	737   	737*        	       	NM  										MODULE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING CRACKED IN (D) PRIORTY PORT.						2	L	7	2 	4F			RT	A16WE   					 
2002051500011	20020515	00011	NM  	2002	5	15	2002FA0000601    	1	20020312	G	3230	65446924	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										MODULE	PIN HOLE        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					271					PIN HOLE LEAK BELOW PORT NR 2.						2	L	7	2 	4F			RT	A16WE   					 
2002051500012	20020515	00012	NM  	2002	5	15	2002FA0000602    	1	20020311	G	3230	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										SHUTTLE VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					118559					BODY ITEM (15) IS CRACKED ON ID MOUNTING HOLE.						2	L	7	2 	4F			RT	A16WE   					 
2002051500013	20020515	00013	NM  	2002	5	15	2002FA0000603    	1	20020318	G	2923	654468311	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										HYD PACK	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					3032					HAIR LINE CRACK JUST BELOW THREADS OF PORT NR 1.  OCCURED DURING NORMAL OPERATION.						2	L	7	2 	4F			RT	A16WE   					 
2002051500014	20020515	00014	NM  	2002	5	15	2002FA0000604    	1	20020218	G	7830	122510	HOUSING         			BOEING	737   	737*        	       	NM  										SOLENDOID VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1829					HAIR LINE CRACK ON SEAM OF BODY ON PORT NR 1 NEAR MOUNTING LUG.  OCCURED DURING NORMAL OPERATION.						2	L	7	2 	4F			RT	A16WE   					 
2002051500015	20020515	00015	NM  	2002	5	15	2002FA0000605    	1	20020213	G	3230		HOUSING         	BOEING      		BOEING	737   	737200      	1384453	NM  										MODULE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		46209			1028					HOUSING IS CRACKED.						2	L	7	2 	4F			 	A16WE   					 
2002051500016	20020515	00016	NM  	2002	5	15	2002FA0000606    	1	20020206	G	3230	65446925	HOUSING         	BOEING      		BOEING	737   	737200      	1384453	NM  										MODULE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		67565			0779					HOUSING, UNIT IS CRACKED IN (D) PRIORTY PORT.						2	L	7	2 	4F			 	A16WE   					 
2002051500017	20020515	00017	NM  	2002	5	15	2002FA0000608    	1	20020211	G	3230		CAP             	SARGENT     		BOEING	727   	727*        	       	NM  										ACTUATOR	ERODED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4195CB					ACTUATOR CAP PORT HAS EROSION INTERNALLY.						2	L	7	3 	4F			RT	A3WE    					 
2002051500018	20020515	00018	NM  	2002	5	15	2002FA0000609    	1	20020211	G	3230	631415710	CAP             	SARGENT     		BOEING	727   	727*        	       	NM  										PORT C	ERODED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					3117					ACTUATOR CAP PORT (C) HAS EROSION INTERNALLY.						2	L	7	3 	4F			RT	A3WE    					 
2002051500019	20020515	00019	NM  	2002	5	15	2002FA0000610    	1	20020107	G	2740	69778552	SPRING          	BOEING      		BOEING	737   	737*        	       	NM  										HORIZONTAL STAB	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		22868			KE00511	23776				SPRINGS ARE BROKEN IN THE AUXILIARY BRAKE SYSTEMS.  IMPROPER HEAT-TREATING, AUSTENITE, FATIGUE AND INCREASED SPRING COIL	.  SPRINGS (PN 69-77855-1) ARE TO BE REPLACED WITH (PN 69-77855-2).  SPRINGS ON ACTUATOR ASSEMBLIES MANUFACTURED PRIOR T	O SERIAL NUMBER KEO1730 PER MFG SL.				2	L	7	2 	4F			RT	A16WE   					 
2002051500020	20020515	00020	NM  	2002	5	15	2002FA0000611    	1	20020123	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										SHUTTLE VALVE	PIN HOLE        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					651					SHUTTLE VALVE HAS A CRACKED HOUSING.						2	L	7	2 	4F			RT	A16WE   					 
2002051500021	20020515	00021	NM  	2002	5	15	2002FA0000612    	1	20020307	G	2761	65C268636	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		48893			1246					ACTUATOR HOUSING IS CRACKED AT THE TOP SHOULDER.						2	L	7	2 	4F			RT	A16WE   					 
2002051500022	20020515	00022	NM  	2002	5	15	2002FA0000613    	1	20020228	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										SHUTTLE VALVE	PIN HOLE        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4603					PIN HOLE IN MOUNTING LUG HOLE.  LEAKS HYDRAULIC FLUID, FATIGUED.						2	L	7	2 	4F			RT	A16WE   					 
2002051500023	20020515	00023	NM  	2002	5	15	2002FA0000614    	1	20020327	G	2822	209739WE	NUT             			BOEING	727   	727*        	       	NM  										FUEL PUMP	FRACTURED       	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										NUT FRACTURED INTO THREE PIECES UNDER NORMAL TORQUE OF (75-80 IN-LBS).						2	L	7	3 	4F			RT	A3WE    					 
2002051400052	20020514	00052	CE  	2002	5	14	2002FA0000615    	1	20020509	G	1430		RIVET           			BEECH 	B300  	B300        	1159232	CE  										WING	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	160AR					FL154				UNDERSIDE OF WINGS AT WING STATION 209 HAVE LOOSENING RIVETS (CRACKED PAINT AND SMOKING), 45 OF 66 ON LEFT WING, 30 OF 6	6 ON RIGHT WING.					2	L	7	2 	4T			RT	A24CE   					 
2002051400053	20020514	00053	CE  	2002	5	14	2002FA0000616    	1	20020509	G	1430		RIVET           			BEECH 	B300  	B300        	1159232	CE  										WING	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	272SW					FL228				UNDERSIDE OF WINGS AT WING STATION 209 HAVE LOOSENING RIVETS (CRACKED PAINT AND SMOKING).  APPROXIMATELY HALF THE RIVETS	 SHOW SYMPTOMS.					2	L	7	2 	4T			RT	A24CE   					 
2002051500024	20020515	00024		2002	5	15	2002FA0000617    	4	20020411	G	2561	GA12PO201	LIFE VEST       																	CELL	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										FLOTATION DEVICE FAILED MFG RECOMMEDNED 2 PSI PRESSURE TEST.																			 
2002051500025	20020515	00025	CE  	2002	5	15	2002FA0000618    	1	20020425	G	5720	51220466	BRACKET         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT WING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	6764C	6950 				402C0628				LOWER RIGHT FLAP BELLCRANK BRACKET BROKE DUE TO CORROSION FROM ENGINE EXHAUST.  LEFT WING INSPECTED, PARTS SHOW NO CORRO	SION.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002051500026	20020515	00026	EA  	2002	5	15	2002FA0000619    	2	20020418	G	8530	68510	STUD            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 3 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	75844	150  				17267998	L64176			THE STUD THAT HOLDS DOWN THE EXHAUST ROCKER SNAPPED OFF, CAUSING ROCKER AND RELATED PARTS TO FLOAT AROUND IN VALVE COVER	.  LOOSE PARTS THEN LODGED BETWEEN INTAKE ROCKER CAUSING 30 DEGREE BEND IN PUSH ROD AND SHROUD.  THE STUD THAT BROKE, BR	OKE AT THREADS WITHIN THE CYLINDER HEAD.  PARTIAL POWER LOSS IN FLIGHT, PILOT MADE AN EMERGENCY LANDING AT 4S2.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002051500027	20020515	00027	EU  	2002	5	15	2002FA0000620    	1	20020412	G	7700	64031122101	DISPLAY         			AMD   	FALC20	20F5        	2730105	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	757CX					408				WHEN LEFT FUEL FEEDER TANK IS DRAINED COMPLETELY, RIGHT FUEL FEEDER TANK DROPS TO ZERO (QUANTITY INDICATOR).  WHEN YOU P	ULL LEFT FUEL FEEDER TANK CIRCUIT BREAKER THE LEFT FUEL QUANTITY GOES TO RED X AS IT SHOULD AND RIGHT FUEL QUANTITY INDI	CTOR DROPS TO ZERO.  IT WAS FOUND TO BE A SOFTWARE PROBLEM IN THE EEI  (ELECTRONIC ENGINE DISPLAY)				2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
2002051500031	20020515	00031		2002	5	15	2002FA0000621    	4	20020222	G	2211		COMPUTER        			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	TIO540*     	41532	EA  					AUTOFLIGHT	FAILED          	B			Z08S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	97TD					18280012				THE AC WAS IN LEVEL FLIGHT WITH AUTOPILOT TURNED OFF.  WHEN THE AUTOPILOT COMPUTER, WITHOUT INPUT FROM THE PILOT GAVE AN	 INDICATION THAT (PITCH WARNING) LIGHT CAME ON WITH A (UP) ARROW.  THE PILOT PULLED THE AUTOPILOT CIRCUIT BREAKER TO TUR	N OFF SYSTEM.  ANOTHER FLIGHT WITH THE AUTOPILOT SYSTEM (ON) THE ELECTRIC TRIM STARTED TO RUN AWAY IN THE NOSE UP ATTITU	DE AND THE PILOT WENT TO PRESS THE  AUTOPILOT DISCONNECT ON THE CONTROL WHEEL, WITH NO RESULTS.  THE PILOT PULLED THE AU	TOPILOT CIRCUIT BREAKER TO STOP THE OCCURRENCE AND MANUALLY TRIMMED AS REQUIRED.  MAINTENANCE DISABLED AUTOPILOT SYSTEM 	WHICH INCLUDES THE ELECTRIC TRIM.	1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2002051500066	20020515	00066	SO  	2002	5	15	2002FA0000623    	1	20020416	G	3230	PA6469100	TORQUE LINK     			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					LT MLG STRUT	DAMAGED         	D			QVVS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	261FC	6416 				2824697				DURING LANDING LT LOWER STRUT ASSEMBLY SEPERATED FROM UPPER CYLINDER.  LOWER TORQUE LINK FAILED IN AREA ABOVE MACHINED B	OSS AT THE LOWER STRUT ATTACHMENT END, ALLOWING THE LOWER STRUT / WHEEL ASSEMBLY TO BLOW OUT OF THE UPPER CYLINDER.  THI	S PN TORQUE LINK REQUIRES 500 HOUR RECURRING INSPECTION IAW AD.  PROBABLE CAUSE, FATIGUE.   REMOVE FROM SERVICE AND REPL	ACE WITH LATEST TORQUE LINK DESIGN.			1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002051500067	20020515	00067	SW  	2002	5	15	2002FA0000624    	1	20020426	G	3233		COUPLING        			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MLG ACTUATOR	FAILED          	B			PHKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	315SB	4997 				700005				WHEN PILOT SELECTED GEAR DOWN, INCOMPLETE EXTENSION OCCURRED.  ATTEMPTS TO EXTEND THE GEAR MANUALLY ALSO FAILED.  GEAR C	OLLAPSED ON LANDING. Z AN INSPECTION FOUND THAT THE COUPLING BETWEEN THE GEAR MOTOR AND ACTUATOR WAS SEPARATED.  THE MOT	OR WAS FOUND NOT TO OPERATE ALSO.  THE ACTUATOR ASSEMBLY IS 30+ YEARS OLD.				1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2002051500068	20020515	00068	SW  	2002	5	15	2002FA0000625    	1	20020426	G	3233	41960016	ACTUATOR        			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	FAILED          	B			PHKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	315SB	4997 				700005				WHEN PILOT SELECTED GEAR DOWN INCOMPLETE EXTENSION OCCURRED.  ATTEMPTS TO EXTEND THE GEAR MANUALLY ALSO FAILED.  AFTER T	HE AIRCRAFT WAS RETREIVED,  PLACED ON JACKS AND BELLY PANELS REMOVED, IT WAS DISCOVERED THE MAIN LANDING GEAR ACTUATOR (	DUKES) COUPLING BETWEEN THE MOTOR AND TRANSMISSION WAS SEPARATED, ALSO, THE MOTOR WAS FOUND NOT TO RUN ELECTRICALLY.  PR	OBABLE CAUSE:  MOTOR/ TRANSMISSION COUPLING SEPARATED, CAUSING MOTOR TO SEIED.  COUPLING IS 30+YEARS OLD.			1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2002051500069	20020515	00069	CE  	2002	5	15	2002FA0000626    	1	20020430	G	2420	AN66A	BOLT            			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					GENERATOR	WRONG PART      	B			CNQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	721T					5500993				A LOOSE GENERATOR GROUND CABLE BOLT WAS DISCOVERED WHILE TROUBLESHOOTING AN AMMETER SPLIT BETWEEN THE LEFT AND RIGHT ENG	INE GENERATORS.  AN AN610A BOLT WAS FOUND INSTALLED INSTEAD OF THE CORRECT AN6-6A BOLT.  THE BOLT WAS TOO LONG AND TORQU	E COULD BE REACHED.				1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2002051500070	20020515	00070	CE  	2002	5	15	2002FA0000627    	1	20020423	G	5520	6732030	HINGE           			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					ELEVATOR	CRACKED         	B			CNQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	789QS					6507089				CRACKS WERE FOUND IN BOTH INBOARD ELEVATOR HINGES DURING A SCHEDULED INSPECTION.  THE HINGES ARE ATTACHED TO THE HORIZON	TAL STABILIZER AND ARE LOCATED AT THE INBOARD END OF EACH ELEVATOR.  THE CRACKS EXTEND APPROXIMATELY .20 INCH IN LENGTH 	AND ARE LOCATED ON THE UPPER AFT END OF THE INBOARD HINGE FITTING.				2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2002051500134	20020515	00134	GL  	2002	5	15	2002FA0000628    	1	20020408	G	6500	E181150	BELT            			AMTR  	RWEXEC	ROTORWAYEXEC	       	GL  										TAIL ROTOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	21901	208  								CENTER TAIL ROTOR BELT FAILED RESULTING IN NO TAIL ROTOR CONTROL.  BELT LIKELY FAILED DUE TO IMPROPER BELT ROUTING THROU	GH TAILBOOM FROM ONE IDLER PULLEY TO NEXT IDLER PULLEY.					1	G	7	1 	3O			 	EXPA1G71					 
2002051500135	20020515	00135	CE  	2002	5	15	2002FA0000629    	1	20020429	G	2710	0860207180	CONTROL CABLE   			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520*    	17040	SO  					AILERON	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	310RH	1950 				310R1878				ALL FOUR CONTROL CABLES HAD STRANDS BROKEN.  THE LEFT FORWARD CARRY THRU CONTROL CABLE HAD APPROXIMATELY 70 PERCENT OF I	TS STRANDS BROKEN DUE TO CONTACT WITH PULLEY GUARD.  THE OTHER PROBLEM IS WHERE CONTROL CABLES COME OUT OF FUSELAGE RUBB	ING ON PHENOLIC BLOCK.				1	L	7	2 	3O	3	O	 	3A10    	E8CE				 
2002051500136	20020515	00136	CE  	2002	5	15	2002FA0000630    	1	20020501	G	3010	510010718	LINE            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					UNDER FLOOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	35DR	4300 				414A0628				LINE ASSEMBLY STA 229-289, FOUND TO HAVE HOLE IN IT DIRECTLY ABOVE THE AIR DISTRIBUTION DUCTS.  HOLE IN LINE CAUSED DEIC	E BOOTS TO PARTIALLY INFLATE UN-COMMANDED IN FLIGHT.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002051400030	20020514	00030	CE  	2002	5	14	2002FA0000631    	1	20020405	G	2435	23085004	STARTER GEN     			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	FAILED          	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	09	200CV		60   			S5500064				STATER GEN UNIT FAILED TO START ENGINE. NO OTHER OPERATION PROBLEM NOTED. SUBSEQUENT TEARDOWN REVEALED WORN AND / OR DAM	AGED PARTS. UNIT WAS REPORTED AND TAGGED OVERHAULED 60 HRS PRIOR TO FAILURE BY WECO OF LINCOLN, CA.					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2002051400031	20020514	00031	SO  	2002	5	14	2002FA0000633    	2	20020511	G	7322	CF30764	FLOAT           	FACET       	MA45        	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					CARBURETOR	WORN            	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23	4603N	3063 	1382 		CO43640	18267280	469241			AFTER A SERIES OF INTERMITTANT FUEL LEAKS FOLLOWING ENGINE SHUTDOWNS, CARBURETOR WAS REMOVED AND SUBMITTED TO REPAIR STA	TION (FK3R504L) FOR TROUBLESHOOTING AND/OR OVERHAUL.  SHOP FOUND THE FLOAT ASSEMBLY PIVOT TAB (WHERE FLOAT IS ANCHORED W	ITHIN THE CARBURETOR HOUSING) WAS WORN DOWN.  ON SHUTDOWN THE FLOAT'S MOVABLE "TAB" WOULD NOT LEVER THE NEEDLE VALVE TO 	THE FULLY-CLOSED POSITION ALLOWING FUEL TO BYPASS IT INTO THE VENTURI AND TRICKLE OUT OF THE AIRBOX.  RECORDS (FROM CBIR	054K) SUGGEST THIS FLOAT WAS NOT REPLACED AT ITS PREVIOUS OVERHAUL, 9 DEC 94.  WHILE CARBURETOR HAD ACCUMULATED 1382 HOU	RS SINCE OVERHAUL IT APPEARS ITS FLOAT DEVICE HAD ACCUMULATED 3063 HOURS.	1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002051400032	20020514	00032		2002	5	14	2002FA0000634    	4	20020513	G	3452		COAX            			PIPER 	PA28  	PA28181     	7102807	SO  										TRANSPONDER	WRONG PART      	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19		2592 				2843150				DISCOVERED INCORRECT COAX USED IN FACTORY INSTALLATION OF ATCRBS TRANSPODNER SYSTEM. COAX INSTALLED IN AIRCRAFT OF TYPE 	NOT APPROVED BY EQUIPMENT MANUFACTURER.  THIS LEAD TO TRANSPONDER SYSTEM FAILURE.					1	L	7	1 	3O			 	2A13    					 
2002051400033	20020514	00033	CE  	2002	5	14	2002FA0000635    	1	20020503	G	3213	65412045	STUD            			CESSNA	500   	550         	2076604	CE  										RT MLG STRUT	BROKEN          	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	87SF	3673 	3673 			5500096				DURING SCHEDULED REPLACEMENT OF THE MLG STRUT CYLINDERS, THE HYD ACTUATOR ATTACH STUD WAS BEING REMOVED FOR RE-USE. UPON	 APPLYING A TENSION LOAD ON THE STUD TO REMOVE IT, PER MM, THE STUD SEPARATED ALONG THE THREADS WELL BELOW THE MAX TORQU	E LIMIT, THE CRACK BEGAN APPROX 1 THREAD UP FROM THE BASE AND EXTENDED  UP THREE THREADS, STOPPING APPROX 1 THREAD BEFOR	E THE COTTER PIN HOLE.  EXAMINATION REVEALED THAT THE FRACTURE HAD EXISTED FOR SOME TIME AND THAT IT EXTENDED THROUGH AP	PROXIMATELY 80 PERCENT OF THE STUD. THE POINT AT WHICH THE FRACTURE BEGAN IS THE SAME POINT AT WHICH THE NUT CONTACTS TH	E ROD END.	1	L	7	2 	4F			 	A22CE   					 
2002051500137	20020515	00137	CE  	2002	5	15	2002FA0000636    	1	20020411	G	3320		BATTERY PACK    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN	MISREPAIRED     	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09	825JW					5500266				BATTERY HAS BEEN REPAIRED WITH NON-PMAD CELLS.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002051500138	20020515	00138	SW  	2002	5	15	2002FA0000637    	1	20020422	G	5711		SPAR            			BBAVIA	7     	7EC         	2110120	SW  	CONT  	C90   	C90*        	17009	SO  					RIGHT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4351C					370				IN COMPLYING WITH AD, FOUND CRACK AT BUTT OF MAIN SPAR JUST UNDER ATTACH FITTING TO FUSELAGE ON RIGHT WING TRAVELING SEV	ERAL INCHES LONGITUDINALLY.  SEVERAL RIB NAILS LOOSE ON BOTH WINGS.  AIRCRAFT HANGARED-CAUSE UNKNOWN, (HOURS ON WINGS 50	00 TO 6000), REPAIR OF WINGS REQUIRED.				1	H	7	1 	3O	3	O	 	A759    	E252				 
2002051500143	20020515	00143	EA  	2002	5	15	2002FA0000639    	1	20020429	G	2913	887138	BEARING         	VICKERS     		CNDAIR	CL600 	CL6002B19   	1900309	EA  										HYD PUMP	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27					MV595355					BEARING WAS FOUND IN PIECES.  INNER RACE OF BEARING STILL ATTACHED TO ROTOR LINER.  NO LUBRICANT VISIBLE.						2	L	7	2 	4F			RT	A21EA   					 
2002051500144	20020515	00144	CE  	2002	5	15	2002FA0000641    	1	20020423	G	7603	363800843	CONTROL CABLE   			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					THROTTLE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4151Q	6088 				E2679				END OF THROTTLE CABLE CAME APART A SURAGE.						1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2002051500001	20020515	00001	SW  	2002	5	15	2002FA0000642    	1	20020514	G	2731	550000151	CONTROL CABLE   			GULSTM	500   	500B        	0141106	SW  										ELEVATOR TRIM	BROKEN          	D				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			SO	11	24KM	8150 				500B129611				ELEVATOR TRIM CABLE BROKE WHILE ON APPROACH. CABLE BROKE WHERE IT WRAPPED AROUND AN AUTOPILOT TRIM ACTUATOR THAT HAD BEE	N DEACTIVATED. CORRECTIVE ACTION WAS TO REMOVE THE OLD TRIM ACTUATOR AND REPLACE ALL 4 ELEVATOR TRIM CABLES. AS A PRECAU	TION ALSO REPLACED THE RUDDER TRIM CABLES.				1	H	7	2 	3O			 	6A1     					 
2002051600001	20020516	00001	CE  	2002	5	16	2002FA0000645    	1	20020411	G	5521		SPAR            			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	355JS					LW257				END RIB CRACKED SEVERAL PLACES.  FORWARD SPAR, INBOARD END CRACKED.						1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2002051600002	20020516	00002	EA  	2002	5	16	2002FA0000646    	2	20020225	G	8500		BEARING         			MOONEY	M20   	M20M        	5870222	SW  	LYC   	0540  	TIO540AF1B  	41532	EA  					ENGINE	FAILED          	D			GJAS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	355RZ					270235	L982961			DURING REGULARLY SCHEDULED OIL CHANGE AT 399.5 HRS, UPON EXAM OF OIL FILTER, METAL CONTAMINATES WERE DISCOVERED IN THE E	LEMENT FOLDS.  CONTACTED MFG, ADVISED THERE WAS A SERVICE INSTRUCTION THAT PERTAINED TO THIS ENGINE THAT OUTLINES INSPEC	TION PROCEDURE FOR OIL FILTER/OIL SCREEN DEBRIS INSPECTION.  WE HAD WASHED THE FILTER CONTAMINATES INTO A CLEAN COFFEE F	ILTER.   AFTER PULLING THE PICK UP SCREEN FROM THE BOTTOM OF THE OIL SUMP.  WE DISCOVERED A LARGER AMOUNT OF DEBRIS IN T	HE SCREEN.  OIL SAMPLE INITINITALLY TAKEN FROM OIL SUMP.  CAME BACK STATING THAT MATERIAL FROM SAMPLES SENT WERE BEARING	MATERIAL FROM ROD, MAIN OR NOSE BEARINGS.  SENT ENGINE BACK TO MFG. FOR WARRANTY AND REPAIR.	1	L	7	1 	3O	3	O	RT	2A3     	E14EA				 
2002051600003	20020516	00003	CE  	2002	5	16	2002FA0000647    	1	20020426	G	2510	551900921	SEAT BACK       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	196JS					5500196				UPPER SEAT BASE ASSEMBLY CRACKED AT SEAT BACK ATTACH POINTS.  STRESS ON SEAT BACK AND METAL FATIGUE PROBABLE CAUSE.  SEA	T WAS REPAIRED.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002051600004	20020516	00004	SW  	2002	5	16	2002FA0000649    	1	20020430	G	5711	S147	SPAR            			BBAVIA	7     	7AC         	2110102	SW  										LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	83851	4379 				7AC2257				LEFT WING REAR SPAR COMPRESSION CRACK AT STRUT ATTACH POINT BETWEEN DOUBLER ON UPPER SURFACE.						1	H	7	1 	3O			 	A759    					 
2002051700001	20020517	00001	CE  	2002	5	17	2002FA0000652    	1	20020425	G	3297	32600101	WIRE            			CESSNA	500   	560CESSNA   	2076750	CE  										MLG	MISINSTALLED    	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	09	398RS					5605009				LANDING GEAR SELECTED.  UNLOCK LIGHT ON, RT MAIN GEAR, NOT LOCKED.  CREW DID THE CHECKLIST, BLEW GEAR, ABOVE CONDITION R	EMAINED.  CREW DECLARED EMERGENCY AND HAD TO LAND WITH GEAR UNSAFE.  MAINTENANCE TRACED PROBLEM TO A BAD GROUND WIRING. 	 THIS WIRE TERMINATED IN THE RIGHT FLAP WELL.  AS FLAPS ARE LOWERED THE AIR LOADS VIBRATE THE VERY SMALL 22 GAGE WIRE UN	TIL IT BREAKS AT THE ATTACHING TERMINAL.  THE TIE WRAP ATTACH POINT WAS INCORRECTLY INSTALLED AND THIS WIRE WAS NOT EVEN	 SECURED AT MANUFACTURER.  SECURED THE WIRE TIE WRAP AND ITS ATTACH POINT CORRECTLY AND PROSEALED ALL WIRES TO THE ADJOI	NING SHEETMETAL SO THAT IT CANNOT (FLAP IN THE BREEZE).	2	L	7	2 	4F			RT	A22CE   					 
2002051700002	20020517	00002	SO  	2002	5	17	2002FA0000653    	1	20020429	G	7160	86245834	AIR BOX         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENG CARBURETOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	355AB					4496093				DURING 100 HOUR INSPECTION, TECH FOUND RIGHT AND LEFT ENGINE CARBURETOR HEAT AIRBOXES CRACKED.  RIGHT AIRBOX WAS CRACKED	 AT HOT AIR INLET, LOCATED AT THE POINT WHERE TUBE IS WELDED TO AIRBOX AND EXTENDING HALFWAY AROUND THE TUBE.  LEFT AIRB	OX WAS CRACKED AT THE COLD AIR INLET AND EXTENDED ALMOST ALL THE WAY AROUND THE TUBE, RESULTING IN ALMOST COMPLETE SEPAR	ATION OF THE TUBE FROM AIRBOX.  CAUSE: MAY BE POOR DESIGN OF AIRBOX, WEAK WELDS AT BOTH HOT AND COLD AIR TUBES.			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002051700003	20020517	00003	EA  	2002	5	17	2002FA0000654    	2	20020501	G	8520	SL13S19646	GEAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					CRANKSHAFT	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	10	4640R					2821393	L2415627A			FOUND CRANKSHAFT GEAR TO HAVE ITS TIMING MARK OFF BY ONE TOOTH. FAA INSPECTOR NOTE:  MECHANIC SAID ENGINE WOULD NOT DEVE	LOP FULL POWER.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002052300006	20020523	00006	SO  	2002	5	23	2002FA0000655    	2	20020503	G	8550	B1119M	SEPARATOR       			BEECH 	35    	E35         	1151512	CE  	CONT  	E225  	E225*       	17015	SO  					AIR/OIL	LEAKING         	B			MI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	3311C	1291 				D3977	40150D			DURING ENGINE RUNUP OIL WAS OBSERVED LEAKING FROM SEPARATOR LOWER OUTBOARD CORNER.  INSPECTION REVEALED SEPRATOR CORRODI	NG/ RUSTING FROM INSIDE OUT.  OIL LEAKING THROUGH CORROSION PINTS IN BOTTOM ONTO EXHAUST.  REPLACED WITH NEW UNIT.  RECO	MMEND INSPECTION AT EACH ANNUAL INSPECTION.				1	L	7	1 	3O	3	O	 	A777    	E267				 
2002052300007	20020523	00007	CE  	2002	5	23	2002FA0000656    	1	20020508	G	7130		INSULATOR       			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					NACELLES	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	241MW	4789 				421C0030	610478			ON REPLACING LEFT WING LOCKER FUEL CELL, DISCOVERED  (PN 5656006-2),  FIREWALL FIRE SCREEN COATING BURNED THROUGH BEHIND	 TURBOCHARGER.  REMOVED RIGHT NACELLE TOP SKIN AND DISCOVERED OTHER (PN 5656006-2) FIREWALL FIRE SCREEN IN SIMILAR CONDI	TION.  INSTALLED NEW SCREENS, BOTH NACELLES.				1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2002052300008	20020523	00008	CE  	2002	5	23	2002FA0000657    	1	20020513	G	2751	503800135	INDICATOR       			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					TE FLAPS	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										THIS IS NEW FROM STOCK AND WAS JUST ORDER FROM MFG. WAS INSTALLED AND THE METER MOVEMENT WAS ONLY .5 OF THE TRAVEL.  PAR	T WAS REMOVED AND TESTED ON THE BENCH AND HAD A HIGH AMP DRAW.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002052300009	20020523	00009	SO  	2002	5	23	2002FA0000658    	1	20020429	G	7160	86245834	AIR BOX         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					CARB HEAT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	355AB	323  				4496093				DURING 100 HOUR INSPECTION, TECHNICIAN FOUND BOTH RIGHT AND LEFT ENGINE CARBUETOR HEAT AIRBOXES CRACKED.  THE RIGHT AIRB	OX WAS CRACKED AT THE HOT AIR INLET, LOCATED AT THE POINT WHERE TUBE IS WELDED TO AIRBOX  AND EXTENDING HALFWAY AROUND T	HE TUBE.  THE ALMOST ALL THE WAY AROUND THE TUBE, RESULTING IN ALMOST COMPLETE SEPARATION OF THE TUBE FROM THE AIRBOX.  	A POSSIBLE BOTH COLD AND HOT AIR TUBES.			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002052300001	20020523	00001	CE  	2002	5	23	2002FA0000659    	1	20020516	G	2701	05117821	YOKE            			CESSNA	172   	172M        	2072418	CE  										COCKPIT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4574V	6493 				17266358				UPON COMPLETION OF THE INITIAL INSPECTION FOR SEB01-3,THE CONTROL YOKE WAS FOUND TO BE INTERNALLY CORRODED. ULTRASONIC I	NSPECTION REVEALED WALL THICKNESS DETERIORATION TO LESS THAN 0.030 INCH.					1	H	7	1 	3O			NT	3A12    					 
2002052300002	20020523	00002	GL  	2002	5	23	2002FA0000660    	1	20020510	G	5510	81611	TERMINAL        			AVIAT 	A1    	A1A         	2210405	GL  										HORIZONTAL	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	478DM	420  				1450				LEFT LOWER FORWARD TAIL STRUT THREADED ROD DISCOVERED BROKEN ON PREFLIGHT. (NO ADVERSE FLIGHT CHARACTERISTICS NOTED ON P	REVIOUS FLIGHT.)  ROD BROKEN AT END OF 5/16 INCH X 24 THREADS NEXT TO 5/16 INCH HEX SHAFT.					1	H	7	1 	3O			NC	A22NM   					 
2002052300003	20020523	00003	CE  	2002	5	23	2002FA0000661    	1	20020521	G	5751	45135031139	SKIN            			BEECH 	95    	95B55       	1152729	CE  										LT AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	161DP	3128 				TC2151				AILERON SKIN CRACKS OBSERVED PROPAGATING LATERALLY IN UPPER AND LOWER AREAS FOWARD OF SPAR AND AFT OF BALLANCE WEIGHTS.						1	L	7	2 	3O			RT	3A16    					 
2002052300005	20020523	00005	GL  	2002	5	23	2002FA0000662    	2	20020521	G	7260	4252071	MAGNETIC SEAL   			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					ACCESSORY G/B	WORN            	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NM	09	551AM	460  				7500155	300329			CREW RECEIVED ENGINE CHIP-L CAS MESSAGE. AIRCRAFT LANDED AT DESTINATION. MAGNETIC INDICATOR PLUG INSPECTED AND SINGLE SL	IVER FOUND. 3RD INCIDENT OF THIS NATURE ON THIS ENGINE. ANALYSIS BY ROLL-ROYCE ON 2ND INCIDENT SLIVER SHOWED STAINLESS 4	10 ALLOY. FOUND WAVE SPRING AND MAGNETIC SEAL BADLY WORN.				2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2002052300104	20020523	00104	GL  	2002	5	23	2002FA0000663    	2	20020425	G	7230	23031938	TURBINE WHEEL   								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DESTROYED       	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17		163  								TURBINE WAS RECEIVED FOR REPAIR DUE TO N1 LOCK-UP.  UPON DISASSEMBLY FOUND THAT THE DIAPHRAGM HAD SEPARATED FROM THE CAS	TING AND WAS REDUCED TO SEVERAL SMALL PIECES.  ALSO FOUND THE FIRST AND SECOND STAGE TURBINE WHEELS HAD SUSTAINED SEVERE	 DAMAGED DUE TO CONTACT WITH THE DIAPHRAGM.  THE WHEELS WERE SCRAPPED.									3	U			E4CE				 
2002052300106	20020523	00106	SO  	2002	5	23	2002FA0000666    	1	20020501	G	5532	66975	SKIN            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					VERTICAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	56136	14077				287305538				VERTICAL STABILIZER - ON BOTTOM TRAILING EDGE OF VERTICAL STABILIZER.  THE SKIN APPEARED TORN, UPON REMOVAL OF RUDDER.  	THE STRUCTURE INSIDE THE VERTICAL STABILIZER APPEARED TO HAVE FATIGUE AND WAS CRACKED TO MIDPOINT OF VERTICAL WIDTH.  NO	 DAMAGE TO RUDDER.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002052300103	20020523	00103	CE  	2002	5	23	2002FA0000667    	1	20020523	G	2400	W31X2M1G50	MASTER SWITCH   			CESSNA	175   	175         	2072502	CE  										INSTRUMENT PANEL	FAILED          	E				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SW	01	7535M	2947 				55835				WHILE TAXING FOR  DEPARTURE AT TAOS AIRPORT. THE PILOT EXPERIENCED AN AVIONICS MASTER SWITCH FAILURE. UPON SEEING A SMAL	L AMOUNT OF SMOKE AT THE UPPER AREA OF THE INSTRUMENT PANEL THE PILOT IMMEDIATELY SHUT DOWN THE AIRCRAFT AND TAXIED BACK	 TO THE FBO				1	H	7	1 	3O			NT	3A17    					 
2002060600006	20020606	00006	CE  	2002	6	6	2002FA0000668    	1	20020222	G	5510	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					HORIZ STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	48787	14000				15280967				WHILE INSPECTING THE NUTPLATES IAW AD.  WE FOUND THAT THE FORWARD UPPER WELD JOINT HAD CRACKED ADJACENT TO THE NUTPLATES	 THEMSELVES.  THIS AIRCRAFT IS OPERATED IN A TRAINING ENVIRONMENT AND IS SUBJECTED TO A LOT OF ABRUPT MANEUVERS INCLUDIN	G SPINS.  DUE TO THE LOCATION OF THE CRACKS, MORE EMPHASIS SHOULD BE PLACED ON INSPECTING THE ENTIRE BRACKET AND NOT JUS	T THE NUTPLATES, ESPECIALLY AIRCRAFT THAT HAVE HAD THE NUT PLATES REMOVED TO DO AWAY WITH THE AD INSPECTION.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002060600010	20020606	00010	CE  	2002	6	6	2002FA0000669    	1	20020414	G	7921	635996	OIL COOLER      			CESSNA	310   	310R        	2074245	CE  										ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										THE LISTED OIL COOLER WAS OVERHAULED.  PROBLEM:  THE THREADS FOR THE OIL TEMP PROBE WAS 40 PERCENT DESTROYED OR GONE.  T	HIS AREA WAS NOT INSPECTED OR OVERLOOKED, WAS NOT POSSIBLE TO INSTALL OIL TEMP PROBE.  RETURNED OIL COOLER TO OVERHAUL C	OMPANY.				1	L	7	2 	3O			 	3A10    					 
2002060600011	20020606	00011	SO  	2002	6	6	2002FA0000670    	2	20020419	G	7414	6310	MAGNETO         			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					LEFT	SHORTED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	810NH	1347 				E2819				DURING ROUTINE INSPECTION WHITE POWDER WAS NOTICED AT LEFT MAGNETO VENT.  REMOVED MAGNETO FOR INTERNAL INSPECTION AND FO	UND COIL HAD SHORTED OUT, ARCING AND MELTING DISTRIBUTOR BLOCK AND GEAR ASSEMBLY.  INSTALLED NEW MAGNETO ASSEMBLY.					1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2002060600012	20020606	00012	CE  	2002	6	6	2002FA0000671    	1	20020225	G	5510	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					HORIZ STAB	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	757GQ	10000				15279732				WHILE INSPECTING THE NUTPLATES IAW AD, WE FOUND THAT THE FORWARD UPPER WELD JOINT HAD CRACKED ADJACENT TO THE NUTPLATES 	THEMSELVES.  THIS AIRCRAFT IS OPERATED IN A TRAINING ENVIRONMENT AND IS SUBJECTED TO A LOT OF ABRUPT MANEUVERS INCLUDING	 SPINS.  DUE TO THE LOCATION OF THE CRACKS, MORE EMPHASIS SHOULD BE PLACED ON INSPECTING THE ENTIRE BRACKET AND NOT JUST	 THE NUTPLATES, ESPECIALLY AIRCRAFT THAT HAVE HAD THE NUTPLATES REMOVED TO DO AWAY WITH THE AD INSPECTION.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002060600013	20020606	00013		2002	6	6	2002FA0000672    	4	20020409	G	2350	S28701	SWITCH          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					COCKPIT	FAILED          	B			LC1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	35331					17281037				REPLACED PILOTS PUSH TO TALK SWITCH.  0510.2 TACH.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002060600014	20020606	00014		2002	6	6	2002FA0000673    	4	20020409	G	2350	S28701	SWITCH          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					COCKPIT	INOPERATIVE     	B			LC1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	35331	510  				17281037				REPLACED COPILOTS PUSH TO TALK SWITCH.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002060600015	20020606	00015		2002	6	6	2002FA0000674    	4	20020415	G	2350	S28701	SWITCH          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					COCKPIT	INOPERATIVE     	B			LC1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	35331	517  				17281037				HAD TO REPLACE THE PILOTS PUSH TO TALK SWITCH.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002060600016	20020606	00016		2002	6	6	2002FA0000675    	4	20020402	G	2561	FV353500101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED, MFG RECOMMENDED CELL PRESSURE TEST.																			 
2002060600020	20020606	00020	EA  	2002	6	6	2002FA0000676    	2	20020502	G	8550	MS913401	GASKET          			CESSNA	206   	206CESSNA   	2073302	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					ENGINE	LEAKING         	G				O				OTHER                   				O			OTHER                     			UK	UNKNOWN        	1			EA	07	206YK	328  				T20608125	L1034661A			GASKET FAILED CAUSING LOSS OF ENGINE OIL LEADING TO CATASTROPHIC ENGINE FAILURE.  AIRCRAFT LANDED SAFELY IN FIELD.  THER	E IS NO REQUIREMENT TO GO BACK AND REPLACE THESE GASKETS.					1	H	7	1 	3O	3	O	 	A4CE    	E14EA				 
2002060600024	20020606	00024	SO  	2002	6	6	2002FA0000677    	1	20020501	G	1430		RIVET           			PIPER 	PA34  	PA34200T    	7103406	SO  										HORIZ STAB	LOOSE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	2849P	2780 				347970280				ON BOTH LEFT AND RIGHT STABILIZER TRIM SURFACES THE RIVETS HOLDING THE BRACKET FOR THE TRIM PUSH RODS WHERE LOOSE IN THE	 EXISTING HOLES.					1	L	7	2 	3O			 	A7SO    					 
2002052900065	20020529	00065	CE  	2002	5	29	2002FA0000678    	1	20020528	G	2910	6207023202	HYDRAULIC LINE  			CESSNA	650   	650         	2076802	CE  										HYD SYSTEM	CRACKED         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	09	3184Z					6500032				LINE WAS CRACKED BEHIND AN ADEL CLAMP.  MINOR PITTING AND CORROSION WAS EVIDENT ONCE CLAMP WAS REMOVED FROM LINE.  LINE 	HAD BEEN PREVIOUSLY REPLACED ON 01/02.  TWO OTHER HYDRAULIC LINES, P/N 6207023-154 AND 6207021-152 WERE REMOVED AND FOUN	D TO HAVE SIMILAR CORROSION AND PITTING.				2	L	7	2 	4F			 	A9NM    					 
2002061200120	20020612	00120	SO  	2002	6	12	2002FA0000679    	1	20020510	G	2450	W58X10095	CIRCUIT BREAKER 			PIPER 	PA28  	PA28161     	7102803	SO  										ELECTRICAL SYS	FAILED          	B			SL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	8179G	7620 				288016297				AIRCRAFT WAS NOT USED FOR APPROXIMATELY (7) MONTHS.  AIRCRAFT WAS TIED DOWN OUTSIDE, NEAR SALT WATER ENVIRONMENT.  NEW O	WNER HAD ANNUAL INSPECTION DONE.  DURING ANNUAL INSPECTION FOUND CORROSION ON BELLY HAT SECTION STIFFENER.  NO OTHER UNU	SUAL CORROSION NOTED.  AFTER ANNUAL INSPECTION ELECTRICAL EQUIPMENT BEGAN TO FAIL THAT WAS WORKING DURING ANNUAL INSPECT	ION.  RADIO , LIGHTS, T AND B, AUTO PILOT AND SMU WARNING.  FOUND CIRCUIT BREAKERS DEFECTIVE FOR EACH OF THESE CIRCUITS.			1	L	7	1 	3O			 	2A13    					 
2002061200121	20020612	00121	SO  	2002	6	12	2002FA0000681    	2	20020417	G	8530		EXHAUST VALVE   			PIPER 	PA28  	PA28151     	7102805	SO  	CONT  	O550  	IO550B      	 	SO  					ENGINE	DAMAGED         	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	03	32246	1045 				287515103	675942			NR 2 EXHAUST VALVE HEAD MISSING A SECTION (OVERHEATED AND TORCHED AWAY).  TRACED TO EXCESSIVE VALVE STEM/GUIDE CLEARANCE	.  ALL OTHER CYLINDERS WERE REMOVED AND REPORTED TO HAVE EXCESSIVE WEAR, REQUIRING VALVE AND GUIDE REPLACEMENT.  655 HOU	RS SHORT OF TBO.  PLANE WAS 2 MONTHS SINCE LAST ANNUAL AND AT THAT TIME STATIC COMPRESSIONS WERE WITHIN LIMITS.				1	L	7	1 	3O	3	O	 	2A13    	E3SO				 
2002061200132	20020612	00132	SO  	2002	6	12	2002FA0000682    	1	20020515	G	3010	474142	VALVE           			PIPER 	PA46  	PA46310P    	7104605	SO  										DEICE SYS	BROKEN          	B			BNGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	25120	3975 				468508097				DE-ICE BOOTS INOPERATIVE, FOUND AIRBORN MANIFOLD VALVE BROKEN IN TWO.						1	L	7	1 	3O			RT	A25SO   					 
2002061900231	20020619	00231	CE  	2002	6	19	2002FA0000683    	1	20020523	G	2434	632050	BUSHING         			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  					ALTERNATOR	WORN            	B			BNGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3712V	1205 				R1722261				ENGINE DRIVEN ALTENATOR DRIVE FOUND WORN.						1	H	7	1 	3O	3	O	 	3A17    	E1CE				 
2002061900232	20020619	00232	SO  	2002	6	19	2002FA0000684    	1	20020506	G	3230	AN2321A	BOLT            			PIPER 	PA28  	PA28R201    	7102816	SO  										CLEVIS	FAILED          	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5321U	820  				2844042				DURING CLIMB OUT, THE PILOT HEARD A LOUD BANG.  WHEN THE LANDING GEAR WAS RETRACTED, THE PILOT REPORTED THAT  THE NOSE G	EAR DOWN AND LOCKED LIGHT ILLUMINATED A FEW SECONDS LATER.  THE LANDING GEAR WAS EXTENDED BY THE PILOT AND A SAFE LANDIN	G WAS MADE.  A POST FLIGHT INSPECTION FOUND THAT THE CLEVIS BOLT THAT ATTACHES THE NOSE GEAR ACTUATOR TO THE NOSE GEAR D	OWNLOCK ASSEMBLY TO BE SHEARED OFF.  THE DOWNLOCK ASSEMBLY PARTIALLY DAMAGED WHEN THE BOLT DEPARTED.  THE BOLT AND DOWNL	OCK ASSEMBLY WERE REPLACED AND THE AIRPLANE WAS PUT BACK INTO SERVICE.  RECOMMEND REMOVING THE CLEVIS BOLT AND INSPECTIN	G EVERY 100 HOURS.	1	L	7	1 	3O			 	2A13    					 
2002061900233	20020619	00233	GL  	2002	6	19	2002FA0000685    	2	20020515	G	7250	23031938	NOZZLE          								ALLSN 	250C  	250C20B     	03013	GL  					TURBINE	DETACHED        	B			TU3R	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	CCCMV	3803 					CAE840678			A FOREIGN OPERATOR REPORTED A SUDDEN LOSS OF POWER IN-FLIGHT WITH NOISE FROM IDLE TO SHUTDOWN.  THE TURBINE ASSEMBLY WAS	 REMOVED AND RETURNED TO THE US REPAIR FACILITY THAT PERFORMED THE LAST OVERHAUL.  THE NR 1 SECTION MADE NOISE WHILE TUR	NING BY HAD AFTER TURBINE WAS REMOVED FROM THE ENGINE.  AT DISASSEMBLY, IT WAS NOTED THAT THE NR 2 NOZZLE DIAPHRAGM BRAZ	E JOINT WAS COMPLETELY GONE, ALLOWING THE DIAPHRAGM TO DETACH AND MOVE INTO NR 1 AND NR 2 TURBINE WHEELS.  SEPARATION OF	 THE DIAPHRAGM FROM THE NOZZLE INNER BAND DOES NOT ALLOW PROPER AIRFLOW THROUGH THE NOZZLE VANES.  THIS FAILURE OF THE B	RAZE JOINT CAUSED EXTENSIVE DAMAGE THOUGHT THE TURBINE ASSEMBLY, INCLUDING REPLACEMENT OF NR 1 AND NR 2 TURBINE WHEELS.						3	U			E4CE				 
2002061900234	20020619	00234	CE  	2002	6	19	2002FA0000686    	1	20020404	G	3220	124340216	TRUNNION        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					NLG	COLLAPSED       	B			JZRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	5132C	3437 				21063708	293952R			WHILE RETRIEVING AIRCRAFT FROM NOSE GEAR COLLAPSE, FOUND LOWER TRUNNION ASSEMBLY.  BROKEN AT AFT SIDE WHERE COLLAR WRAPS	 AROUND GEAR.  APPEARS THERE WERE CRACKS AT LEFT AND RIGHT TOP CORNERS JUST FORWARD OF THE BRACE SUPPORT MOUNTS.  THEY A	RE IN  A VERY DIFFICULT AREA TO SEE.				1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2002061900235	20020619	00235	CE  	2002	6	19	2002FA0000687    	1	20020507	G	7160	BA7210	FILTER          			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					INDUCTION SYS	CRACKED         	B			CGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	7RQ					CE1622				DURING INSPECTION OF BRACKET ENGINE INDUCTION AIR FILTER FRAME ASSEMBLY FOUND THE (STEEL) SCREEN CRACKED AND SECTIONS MI	SSING NEAR THE RIVET RETAINING AREAS.  SEE BRACKET AIR FILTER DOCUMENT.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002061900236	20020619	00236	SO  	2002	6	19	2002FA0000688    	1	20020503	G	5511	43001083	RIB             			PIPER 	PA22  	PA22        	7102202	SO  	LYC   	O290  	O290        	41506	EA  					HORIZONTAL STAB	CRACKED         	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	690A	4756 				2293				RT HORIZONTAL STABILIZER RIB CRACKED.  RIB LOCATED AT LEADING EDGE. (MV5R055N)						1	H	7	1 	3O	3	O	 	1A6     	E229				 
2002061900237	20020619	00237	SO  	2002	6	19	2002FA0000689    	1	20020503	G	5511	43001077	RIB             			PIPER 	PA22  	PA22        	7102202	SO  	LYC   	O290  	O290        	41506	EA  					HORIZONTAL STAB	CRACKED         	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	690A	4756 				2293				RIGHT HORIZONTAL STABILIZER RIB CRACKED.  RIB LOCATED AT LEADING EDGE.  (MV5R055N)						1	H	7	1 	3O	3	O	 	1A6     	E229				 
2002060300005	20020603	00005	NE  	2002	6	3	2002FA0000690    	2	20020522	G	7250		TURBINE         			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE73121C   	 	NE  					NR 1 ENGINE	DAMAGED         	E				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	R		OVER TEMP                 	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			EA	23	77SF					141	P73394			AFTER TAKEOFF AND DURING CLIMBOUT, THE PILOT EXPERIENCED A COMPUTER GENERATED AUTOMATIC ROLL BACK OF POWER ON THE NR 1 E	NGINE.  THE NR 2 ENGINE WAS BROUGHT BACK TO A MATCHING POWER SETTING.  IT WAS THEN NOTICED THAT THE NR 1 ENGINE ITT WAS 	MORE THAN 100 DEGREES HIGHER THAN THE NR 2 ENGINE.  THE NR 1 ENGINE WAS SHUT DOWN AS A PRECAUTIONARY MEASURE, AND AN UNE	VENTFUL LANDING WAS MADE.  AFTER SEVERAL GROUND MAINTENANCE RUNS FOR TROUBLESHOOTING, IT WAS DETERMINED THAT SEVERE HOT 	SECTION DISTRESS HAD OCCURRED.  THE ENGINE WAS REMOVED FOR REPAIR.  CAUSE OF PROBLEM UNKNOWN.		2	L	7	2 	4F	4	F	 	A33EU   	E6WE				 
2002061900238	20020619	00238	SO  	2002	6	19	2002FA0000691    	1	20020503	G	5511	43001081	RIB             			PIPER 	PA22  	PA22        	7102202	SO  	LYC   	O290  	O290*       	41506	EA  					HORIZONTAL STAB	CRACKED         	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	690A	4756 				2293				RIGHT HORIZONTAL STABILIZER RIB CRACKED.  RIB LOCATED AT LEADING EDGE.  (MV5R055N)						1	H	7	1 	3O	3	O	 	1A6     	E229				 
2002061900239	20020619	00239	SO  	2002	6	19	2002FA0000692    	1	20020503	G	5511	43001079	RIB             			PIPER 	PA22  	PA22        	7102202	SO  	LYC   	O290  	O290*       	41506	EA  					HORIZONTAL STAB	CRACKED         	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	690A	4756 				2293				RIGHT HORIZONTAL STABILIZER RIB CRACKED.  RIB LOCATED AT LEADING EDGE.						1	H	7	1 	3O	3	O	 	1A6     	E229				 
2002061900240	20020619	00240	SO  	2002	6	19	2002FA0000695    	2	20020513	G	8520	633620	CRANKSHAFT      			BEECH 	58    	58TCA       	1152747	CE  	CONT  	O520  	TSIO520L    	17040	SO  					ENGINE	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	942CP	800  				TK61	227658R			AIRCRAFT LANDED WITH RIGHT ENGINE FEATHERED.  REMOVED COWLING TO INVESTIGATE ENGINE STOPPAGE REMOVED TOP SPARK PLUGS,  F	OUND WHEN TURNING PROPELLER THAT IT WOULD ONLY MOVE ONE REVOLUTION THEN LOCKUP.  WHEN LOOKING IN CYLINDERS ONLY FRONT TW	O, NR 5 AND NR 6 PISTONS WERE MOVING.  NOTIFIED OWNER THAT CRACKSHAFT APPEARED TO BE BROKEN.  BY CRANKSHAFT CHEEK NR 7.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2002061900241	20020619	00241	CE  	2002	6	19	2002FA0000696    	1	20020322	G	5610	10138402521	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A11      	52043	NE  					COCKPIT	FAILED          	C				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			SW	15	350WH	1395 				FL210				WAS AT FL 280 WHEN LOUD POP WAS HEARD AND SAW THE PILOT FRONT WINDSHIELD WAS SHATTERED.  INITIATED AND EMERGENCY DESCENT	 AND LANDED AT AIRPORT FOR REPAIRS.					2	L	7	2 	4T	3	T	RT	A24CE   	E4EA				 
2002061900242	20020619	00242	CE  	2002	6	19	2002FA0000697    	1	20020513	G	2823	05131206	SELECTOR VALVE  			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300*       	17022	SO  					COCKPIT	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	2538U					17250138				SPRING WAS INSTALLED BACKWARD.  FUEL WOULD NOT SHUT OFF LEFT TANK.  TO PREVENT RECURRENCE VALVE SHOULD BE INSPECTED AFTE	R OVERHAUL.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002061900243	20020619	00243	EA  	2002	6	19	2002FA0000700    	2	20020515	G	8520		CAMSHAFT        			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	WORN            	B			SL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	38996	495  				327740104	L1558148A			DURING NORMAL INSPECTION, FOUND FERROUS METAL SLIVERS IN OIL FILTER,  FUTHER INSPECTION BY REMOVING NR 1 AND NR 3 CYLIND	ER SHOWED, METAL IMBEDED IN PISTON SKIRTS, AND CAM LOBE SHAIRED BY NR 3 CYLINDER INTAKE AND NR 4 CYL EXHAUST SEVERELY WO	RN AND PITTED AND CAM FOLLOWERS PITTED.  THIS IS THE 2ND OCCURRENCE OF A PREMATURE CAM LOBE FAILURE FOUND IN A 12 MONTH 	PERIOD.  REMOVAL NR 1 CYLINDER FOR REPAIRS FOR HIGH OIL CONSUMPTION, FOUND NR 3 CYLINDER INTAKE CAM LOBE SEVERLY WORN.			1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2002062000002	20020620	00002	CE  	2002	6	20	2002FA0000701    	1	20020516	G	5751	0322709032270	BRACKET         			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	R7557       	35003	EA  					AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1532D					7754				THESE BRACKETS ARE MADE OF MAGNESIUM AND ARE CORRODING AND CRACKING TO AN ALARMING DEGREE.  THE ORIGINAL ALUMINUM PAINT 	ALONG WITH TODAYS MODERN URETHANES ARE CONCEALING THE MAGNITUDE OF THIS PROBLEM.  APPROX 80 PERCENT OF THE BRACKETS WE H	AVE INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY.  THEN THERE IS THE PROBLEM OF CORROSION BETWEEN THE BEARING AND BOSS WH	ICH EXPANDS AND CRACKS THE BOSS.  THE SEPERATION OF THE AILERON FROM THE REAR WING SPAR WHILE STILL ATTACHED TO THE STEE	L ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE.  WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACK	ETS.  BEAD BLAST BODY WHILE PROTECTING THE BEARING.  CHEMICALLY STRIPPING DOES NOT REMOVE THE CORROSION BY PRODUCTS.	1	H	7	1 	3R	3	R	 	A790    	5E11				 
2002061100042	20020611	00042	SW  	2002	6	11	2002FA0000704    	1	20020508	G	5320	206031202015S	SUPPORT         			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	MISMANUFACTURED 	D			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										SUPPORT, NEW PART.  LOCATING NEW PART ON AIRCRAFT.  PILOT HOLES MISDRILLED FROM FACTORY.						1	G	7	1 	3U			 	H2SW    					 
2002061100046	20020611	00046	GL  	2002	6	11	2002FA0000705    	2	20020513	G	7210	E6898785	GEAR            			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C28B     	03013	GL  					PTO GEAR TEETH	DAMAGED         	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										(PTO GEAR) UPON VISUAL INSPECTION OF PART AFTER BEING CHECKED OUT OF STOCK.  DAMAGE TO 4 EA SMALL GEAR TEETH AND 1 EACH 	TOOTH HAS ARC LIKE RECESSED AREA.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002061100047	20020611	00047	GL  	2002	6	11	2002FA0000706    	2	20020514	G	7210	23071895	GEAR            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	ROUGH           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03										(TM GEAR)  UPON VISUAL INSPECTION OF PART.  FOUND EXTREMELY ROUGH GEAR TEETH EDGES AT RADIUS ON FORWARD TEETH.  SENT FOR	 WARRANTY.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002061100048	20020611	00048	GL  	2002	6	11	2002FA0000707    	2	20020227	G	7210	23071895	GEAR            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	MISMANUFACTURED 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										(TM GEARS)  UPON VISUAL INSPECTION OF NEW PART FROM STOCK.  IMPROPER AND UNFINISHED MACHINING ON GEAR TEETH AT RADIUS.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002061100049	20020611	00049	GL  	2002	6	11	2002FA0000708    	2	20020416	G	7210	23071896	GEAR            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	MISMANUFACTURED 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										UPON VISUAL INSPECTION OF NEW PARTS FROM STOCK, IMPROPER AND UNFINISHED MACHINING AND MESHING OF GEAR TEETH AT RADIUS.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002061100050	20020611	00050	GL  	2002	6	11	2002FA0000709    	2	20020410	G	7210	23071896	GEAR            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					GEAR TEETH	ROUGH           	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										UPON RECEIVING AND INSPECTION, ROUGH EDGES OF RADIUS OF GEAR TEETH AFT SIDE.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002062000003	20020620	00003	EU  	2002	6	20	2002FA0000711    	1	20020531	G	7820	115TA601004	BAFFLE          			GROB  	120   	G120A       	       	EU  										NR 3 CYLINDER	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	862AF	218  				85002				ENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER.  PART REMOVED AND NEW BAFFLE INSTALLED.  PART SENT IN FOR WARRANTY.						1	L	7	1 	3O			RT	A49CE   					 
2002062000004	20020620	00004	EU  	2002	6	20	2002FA0000712    	1	20020604	G	7820	115TA601003	BAFFLE          			GROB  	120   	G120A       	       	EU  										NR 1 CLYINDER	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	193  				85001				ENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER.  PART REMOVED AND NEW BAFFLE INSTALLED.						1	L	7	1 	3O			RT	A49CE   					 
2002062000005	20020620	00005	EU  	2002	6	20	2002FA0000713    	1	20020504	G	2434	115TA6003	SUPPORT BRACKET 			GROB  	120   	G120A       	       	EU  										ALTERNATOR	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	864AF	194  				85004				ALTERNATOR SUPPORT BRACKET CRACKED.  PART REMOVED AND A NEW SUPPORT BRACKET INSTALLED.						1	L	7	1 	3O			RT	A49CE   					 
2002062000007	20020620	00007	EU  	2002	6	20	2002FA0000714    	1	20020604	G	7820	115TA601004	BAFFLE          			GROB  	120   	G120A       	       	EU  										ENGINE	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	193  				85001				ENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER.  PART REMOVED AND NEW BAFFLE INSTALLED.  PART SENT IN FOR WARRANTY.						1	L	7	1 	3O			RT	A49CE   					 
2002062000008	20020620	00008	SO  	2002	6	20	2002FA0000715    	2	20020606	G	7322	6299042	FUEL CONTROL    			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8240T					CE1542				FLUCTUATION IN FUEL FLOW AND UNABLE TO ADJUST IDLE MIXTURE.  THEY FOUND THAT THE MIXTURE CONTROL WAS STIFF WHEN MOVED, (	POSSIBLE GALLING).  FUEL CONTROL WAS REMOVED AND A NEW ONE INSTALLED, ENGINE WAS TRIMMED, TEST FLIGHT CHECKED NORMAL.  F	UEL CONTROL WAS SENT IN FOR WARRANTY.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002062000009	20020620	00009	SO  	2002	6	20	2002FA0000716    	2	20020604	G	7314	7429322	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE DRIVEN	FAILED          	B			VJ3R	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	8240T	312  				CE1542				IN FLIGHT, THE ENGINE WAS ROUGH AND FUEL FLOW WAS BELOW NORMAL AND FLUCTUATING AT THAT POWER SETTING.  A SAFE LANDING WA	S MADE.  A GROUND CHECK OF THE ENGINE OPERATION WAS PERFORMED.  IT WAS FOUND THAT THE ENGINE DRIVEN FUEL PUMP WAS SUCKIN	G AIR THRU THE CASE DRAIN VENT.  PUMP WAS REMOVED AND AN NEW PUMP INSTALLED.  PUMP SENT IN FOR WARRANTY.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002062000010	20020620	00010	EA  	2002	6	20	2002FA0000717    	2	20020605	G	7414	01081792	MAGNETO         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	FAILED          	B			VJ3R	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			WP	07	9299B	69   				2843116				ROUGH ENGINE ON GROUND RUN, A MAGNETO CHECK WAS PERFORMED AND THE LEFT MAGNETO HAD EXCESSIVE MAGNETO DROP.  MAGNETO WAS 	REMOVED AND A  REPAIRED MAGNETO INSTALLED.  MAGNETO OPERATION CHECK OF THE ENGINE WAS PERFORMED AND CHECKED NORMAL.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002062100008	20020621	00008	EU  	2002	6	21	2002FA0000718    	1	20020605	G	7820	120A6401	MUFFLER         			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 	 	EA  					ENGINE EXHAUST	CRACKED         	C			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	861AF	193  				85001				TAIL PIPE SUPPORT BRACKET CRACKED AT WELD.  REMOVED MUFFLER AND INSTALLED NEW MUFFLER ASSEMBLY.  PART SENT IN FOR WARRAN	TY.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2002062000035	20020620	00035	WP  	2002	6	20	2002FA0000720    	1	20020602	G	5313		LONGERON        			DOUG  	DC8   	DC873F      	302199F	WP  										FUSELAGE	CORRODED        	B			T64R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	961R	84102				46133				(LONGERON/BATHTUB FITTING) FOUND DURING (D) CHECK INSPECTION, LEFT LONGERON, LEFT LONGERON, 24 STA. 960.						2	L	7	4 	4F			RT	4A25    					 
2002062000036	20020620	00036	WP  	2002	6	20	2002FA0000721    	1	20020508	G	5313		LONGERON        			DOUG  	DC8   	DC873F      	302199F	WP  										FUSELAGE	CORRODED        	B			T64R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	961R					46133				(LONGERON 24)  FOUND DURING (D) CHECK INSPECTION, LEFT WHEEL WELL STA. 902 FITTING AND LONGERON 24 CORROSION EMINATING F	ROM BETWEEN FITTING AND LONGERON LOWER SURFACE.					2	L	7	4 	4F			RT	4A25    					 
2002062000037	20020620	00037	WP  	2002	6	20	2002FA0000722    	1	20020508	G	5320		WEB             			DOUG  	DC8   	DC873F      	302199F	WP  										MLG WW	CORRODED        	B			T64R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	961R	84102				46133				(WEB SKIN)  FOUND DURING (D) CHECK INSPECTION, RIGHT W/W STA. 980  CNAT BULKHEAD WEB SKIN AND ANGLES HAS SURFACE CORROSI	ON FROM LONGERON 24 TO LONGERON 27R.					2	L	7	4 	4F			RT	4A25    					 
2002062000038	20020620	00038	WP  	2002	6	20	2002FA0000723    	1	20020608	G	5320		PANEL           			DOUG  	DC8   	DC873F      	302199F	WP  										RT MLG WW	CORRODED        	B			T64R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	961R	84102				46133				(BULKHEAD PANELS) FOUND DURING (D) CHECK INSPECTION.  RIGHT W/W STA. 980 CNAT BULKHEAD PANELS HAVE CORROSION SPOTS FROM 	LONG 24R TO LONGERON 25R.					2	L	7	4 	4F			RT	4A25    					 
2002062000043	20020620	00043	SO  	2002	6	20	2002FA0000728    	2	20020524	G	8530	654972A1	CYLINDER        			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011B     	17026	SO  					NR 6 POSITION	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	305A	714  				23182				(CYLINDER) FOUND HEAD OF CYLINDER NR6 SEPARATING FROM THE BARREL AT THE THREADED PORTION OF HEAD.  VERIFIED ENGINE TIMIN	G WAS CORRECT.  NO EVIDENCE OF DETONATION FOUND.  AL CYLINDER NEW AT OVERHAUL.  AT 570 HOURS NR4 CYLINDER FAIL THE SAME 	WAY.  ALL CYLINDERS HAD SAME DATE CODE 5-99.  APPEARS TO BE A MFG DEFECT.				1	H	7	1 	3O	3	O	 	5A5     	E269				 
2002062100091	20020621	00091	CE  	2002	6	21	2002FA0000729    	1	20020509	G	5753	16916000511	RIB             			BEECH 	23    	C24R        	1151254	CE  										TE FLAP	CORRODED        	B			JZRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	910JM	2951 				MC683				DURING DISASSEMBLY FROM A BELLY LANDING, FOUND SEVERE CORROSION BETWEEN INBOARD FLAP HINGE (PN 169-160005-20).  PARTS WE	RE ON THE VERGE OF FAILURE.  THEIS AREA IS TOTALLY INACCESSABLE FOR INSPECTION WITHOUT DRILLING THE FLAP APART.					1	L	7	1 	3O			 	A1CE    					 
2002062500121	20020625	00121	CE  	2002	6	25	2002FA0000731    	1	20020612	G	2434	991059111	ALTERNATOR      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	D			CMRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	809SP	1172 				172S8112	2802351A			CHARGING SYSTEM CEASED TO FUNCTION.  DIAGNOSIS WAS ALTERNATOR FAILURE, PROBABLY BREAKDOWN OF DIODES.  NO EXTERNAL SIGNS 	OF FAILURE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002062500122	20020625	00122	CE  	2002	6	25	2002FA0000732    	1	20020520	G	2434	991059111RX	ALTERNATOR      			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	MALFUNCTIONED   	D			ALFG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	166ME	721  				172S8446				ALTERNATOR MALFUNCTIONED.  NO OUTPUT.  DISASSEMBLED, FOUND ONE BRUSH WORN AND OTHER MISSING.  I SUSPECT BRUSH WAS WORN T	O THE POINT THAT THE SPRING FOUND ITS WAY TO THE COMMUTATOR, WRAPPING ITSELF AROUND IT.  BRUSH NOT LOCATED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002062500123	20020625	00123	CE  	2002	6	25	2002FA0000733    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195A        	2073110	CE  	JACOBS	R915  	L6          	35005	EA  					AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	9869A					7571				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING B	EARING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.  IF BRACKETS ARE GOOD,		1	H	7	1 	3R	3	R	 	A790    	TC195				 
2002062500124	20020625	00124	CE  	2002	6	25	2002FA0000734    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195A        	2073110	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	3462V					7187				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEAR	ING.  CHEMICALLLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			 	A790    					 
2002062500125	20020625	00125	CE  	2002	6	25	2002FA0000735    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	190   	190         	2072902	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9872A					7574				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING B	EARING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			NC	A790    					 
2002062500127	20020625	00127	CE  	2002	6	25	2002FA0000736    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195B        	2073112	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	1LA					7908				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING B	EARING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			 	A790    					 
2002062500128	20020625	00128	CE  	2002	6	25	2002FA0000737    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195B        	2073112	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	195HJ					7880				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING B	EARING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			 	A790    					 
2002062500129	20020625	00129	CE  	2002	6	25	2002FA0000738    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195         	2073102	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	211RD					7294				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING B	EARING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			NC	A790    					 
2002062500130	20020625	00130	CE  	2002	6	25	2002FA0000739    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195B        	2073112	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	302GT					7910				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIR CRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEAR	ING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			 	A790    					 
2002062400126	20020624	00126	GL  	2002	6	24	2002FA0000740    	1	20020523	G	3245		TUBE            			CIRRUS	SR    	SR22        	2130001	GL  										NOSE TIRE	LEAKING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	279DV	31   				0196				FOUND THE 5.00-5 NOSE TIRE TO HAVE A VERY SLOW LEAK. REMOVED TUBE AND FOUND IT TO BE LEAKING OUT OF SEVERAL ESTREMELY SM	ALL PIN HOLES WHERE THE VALVE STEM RUBBER IS BONDED TO THE TUBE. A BRAND NEW REPLACEMENT TUBE WAS FOUND TO HAVE THE SAME	 PROBLEM RIGHT OUT OF THE BAG. A THIRD REPLACEMENT TUBE TESTED SATISFACTORY.				1	L	7	1 	3O			NT	A00009CH					 
2002062500137	20020625	00137	SO  	2002	6	25	2002FA0000741    	2	20020531	G	7314	8773	PUMP            			BEECH 	35    	D35         	1151510	CE  	CONT  	E185  	E18511      	17014	SO  					ENGINE FUEL	BROKEN          	G				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			SW	09	2966B					D3607				FOLLOWING AN INFLIGHT ENGINE STOPPAGE, THE AIRCRAFT WAS FORCED TO MAKE AN UNSCHEDULED LANDING CAUSING SUBSTANTIAL DAMAGE	 TO THE AIRCRAFT. THE AIRCRAFT ENGINE WAS SENT TO A FACILITY APPROVED BY THE NTSB TO DETERMINE CAUSE OF THE ENGINE FAILU	RE. DURING THIS TIME IT WAS DISCOVERED THAT THE ENGINE DRIVEN FUEL PUMP WAS BROKEN. THE AIRCRAFT HAD PLENTY OF FUEL AT T	HE TIME OF THE ACCIDENT. THE FUEL PUMP WAS SENT TO THE NTSB LABORATORY FOR EXAMINATION BY THE METALLURGISTS.			1	L	7	1 	3O	3	O	 	A777    	E246				 
2002062500138	20020625	00138	CE  	2002	6	25	2002FA0000742    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195B        	2073112	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	9800V					16163				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEARD BLA	STING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF	 AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLL	ABLE.  HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEA	RING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			 	A790    					 
2002062500139	20020625	00139	CE  	2002	6	25	2002FA0000743    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	LC126C      	2073108	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	1064D					7676				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 90 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEAR	ING   CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			 	A790    					 
2002062500140	20020625	00140	CE  	2002	6	25	2002FA0000744    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195         	2073102	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	3457V					7154				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEAR	ING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			NC	A790    					 
2002062500142	20020625	00142	CE  	2002	6	25	2002FA0000745    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	190   	190         	2072902	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	190EC					7653				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEAR	ING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			NC	A790    					 
2002062500143	20020625	00143	CE  	2002	6	25	2002FA0000746    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195         	2073102	CE  										AILERON HINGE	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	1533D					7755				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEAR	ING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			NC	A790    					 
2002062500145	20020625	00145	CE  	2002	6	25	2002FA0000747    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	195   	195B        	2073112	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	195WT					16128				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEAR	ING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			 	A790    					 
2002062500146	20020625	00146	CE  	2002	6	25	2002FA0000748    	1	20020516	G	5751	0322709	BRACKET         			CESSNA	190   	190         	2072902	CE  										AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	4411C					7996				BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING.  APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLAS	TING ARE UN-AIRWORTHY.  PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS.  SEPARATION OF 	AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLA	BLE.  HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEAR	ING.  CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS.		1	H	7	1 	3R			NC	A790    					 
2002062500148	20020625	00148	CE  	2002	6	25	2002FA0000749    	1	20020326	G	7603	311AS3146780	CONTROL CABLE   			MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					THROTTLE	FRAYED          	E			HMNA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	840MA	9970 				612				DURING ROUTINE MAINTENANCE FOUND A FRAYED ENGINE CONTROL CABLE. THE FRAYED PORTION WAS LOCATED IN THE AFT FUSELAGE WHERE	 THE CABE GOES OVER A 90DEGREE TURN PULLEY. THIS IS THE FIRST OF THREE CABLE PROBLEMS THIS OPERATOR HAS FOUND IN THE LAS	T 90 DAYS				1	H	7	2 	3T	3	T	RT	A10SW   	E2WE				 
2002062500095	20020625	00095	SO  	2002	6	25	2002FA0000751    	2	20020603	G	7322	16A30	NOZZLE          			CESSNA	182   	182L        	2072726	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	CARBUETOR	LOOSE           	D				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			NM	01	42397	435  				18259003	811774R	922654		AIRCRAFT MADE AN EMERGENCY LANDING DUE TO LOSS OF POWER. FOUND CARBURETOR MAIN JET VERY LOOSE (REQUIRED TWO COMPLETE FIN	GER TIGHT TURNS TO TIGHTEN). THE TAB WASHER THAT LOCKS THE MAIN JET HAD NOT BEEN LOCKED, ALL THE TABS WERE FLAT IN A "AS	 NEW" CONDITION.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002070100022	20020701	00022	EU  	2002	7	1	2002FA0000752    	1	20020615	G	7333	P16575GB4A	TRANSDUCER      			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 	 	EA  					FUEL SYSTEM	FAILED          	G			VJ3R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	865AF					85005	L2856448A			AFTER START UP OF THE ENGINE THE FUEL FLOW INDICATION WENT TO ZERO.  AIRCRAFT WAS TAKEN TO MAINTENANCE AND FOUND THAT IF	 YOU TAPPED ON THE  UNIT IT WILL WORK.  FUEL FLOW TRANSDUCER WAS REMOVED AND AN NEW FUEL FLOW TRANSDUCER WAS INSTALLED. 	 GROUND RUN OF THE ENGINE AND AN OPERATIONAL CHECK OF THE SYSTEM CHECKED NORMAL.				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2002062500096	20020625	00096	SW  	2002	6	25	2002FA0000753    	1	20020508	G	3230	F3114MPB	ROD END         			LUSCMB	1     	PHANTOM1    	5350102	SW  	CONT  	O550  	IO550G      	17042	SO  	MCAULY	2A34C	2A34C*      	GL  	MLG	BROKEN          	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	01	1008	321  	77   			108	679476	000374		ROD-END BEARING FAILED ON RIGHT RETRACT ROD.						1	H	7	1 	3R	3	O	 	ATC552  	E3SO	5	C	P3EA	 
2002062500097	20020625	00097	SW  	2002	6	25	2002FA0000755    	1	20020508	G	3230	F3114MPB	ROD END         			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  	MCAULY	2A34C	D2A34C*     	GL  	MLG	BROKEN          	C				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	01	10081	321  	77   			290245	679476	000374		ROD-END BEARING FAILED ON RIGHT RETRACT ROD.						1	L	7	1 	3O	3	O	RT	2A3     	E3SO	5	C	P3EA	 
2002062500099	20020625	00099	CE  	2002	6	25	2002FA0000756    	1	20020605	G	3340	CM358910	SWITCH          			CESSNA	172   	172S        	2072439	CE  										LANDING LIGHT	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03	789EP	1660 				172S8135				LANDING LIGHT SWITCH FAILED IN THE ON POSITION.  THE SWITCH WAS TURNED OFF AFTER LANDING AND WHILE TAXI TO PARKING NOTED	 THE LIGHT WAS STILL ON AND THE SWITCH WAS IN THE OFF POSITION.  THE LANDING LIGHT WOULD ONLY TURN OFF WITH THE BATTERY 	SWITCH.  THIS IS A CIRCUIT BREAKER SWITCH, IF A SHORT HAD OCCURED THE WIRES WOULD HAVE BURNED UP.				1	H	7	1 	3O			NT	3A12    					 
2002062500101	20020625	00101	CE  	2002	6	25	2002FA0000757    	1	20020605	G	3340	CM358910	SWITCH          			CESSNA	172   	172S        	2072439	CE  										LANDING LIGHT	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03	789EP					172S8135				TAXI LIGHT SWITCH FAILED WITH THE LIGHT IN THE OFF POSITION.  THIS IS A CIRCUIT BREAKER SWITCH AND THIS OPERATOR HAS HAD	 THREE PREVIOUS FAILURES THE OTHER FAILURES WERE WITH THE SWITCH IN THE ON POSITION.					1	H	7	1 	3O			NT	3A12    					 
2002062500102	20020625	00102	CE  	2002	6	25	2002FA0000758    	1	20020605	G	3340	CM358910	SWITCH          			CESSNA	172   	172S        	2072439	CE  										LANDING LIGHT	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03	789EP	1660 				172S8135				TAXI LIGHT SWITCH FAILED WITH THE LIGHT IN THE OFF POSITION.  THIS IS A CIRCUIT BREAKER SWITCH. THIS OPERATOR HAS HAD TH	REE PREVIOUS FAILURES, THE FAILURES WERE WITH THE SWITCH IN THE ON POSITION.					1	H	7	1 	3O			NT	3A12    					 
2002062500106	20020625	00106	SW  	2002	6	25	2002FA0000759    	1	20020605	G	3220	540015001	STRUT           			MOONEY	M20   	M20J        	5870219	SW  										MLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	56433	1800 				241381				DURING ROUTINE REPLACEMENT OF NOSE STRUT LORD SHOCK DISCS, SEVERE CORROSION WAS FOUND INSIDE THE STRUT ASSEMBLY.  CORROS	ION PENETRATED 30 PERCENT OF WALL THICKNESS.  PART IS ALMOST 20 YEARS OLD.  RECOMMEND LOOKING INSIDE TUBE DURING ANNUALS	 WITH MIRROR.				1	L	7	1 	3O			 	2A3     					 
2002062500108	20020625	00108		2002	6	25	2002FA0000760    	4	20020531	G	2562	EBC102A	ELT             			UNIVAR	415   	415E        	0420308	NM  	CONT  	C85   	C85*        	17008	SO  					CABIN	ACTIVATED       	G				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			SW	11	94769					4880				THE ELT SWITCH WAS IN THE ON POSITION BUT THE ELT DID NOT ACTIVATE DURING THE ACCIDENT SEQUENCE. THE REASON WAS NOT IMME	DIATELY KNOWN.					1	L	7	1 	3O	3	O	 	A787    	E233				 
2002062500110	20020625	00110		2002	6	25	2002FA0000761    	4	20020613	G	2562	AK450	ELT             																	CABIN	FAULTY          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	30		50   	11   							ELT INSTALLED NEW JUNE 2001, WITH NEW BATTERIES.  IN MAY 2002, IT WAS FOUND THAT THE UNIT DID NOT TRANSMIT WHEN THE G SW	ITCH WAS ACTIVATED.  THE BATTERIES ARE STILL GOOD AND THE UNIT APPEARS TO BE GOOD.  IT HAS BEEN RETURNED TO AMERI-KING F	OR REPAIR.  FURTHUR INQUIRY BY THE TECHNICIAN FOUND THREE OTHER UNITS INSTALLED IN AIRCRAFT THAT DID NOT WORK.																	 
2002062500113	20020625	00113	EA  	2002	6	25	2002FA0000762    	1	20020614	G	5711		SPAR            			ARONCA	15    	15AC        	0191202	EA  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	86189					11AC620				DURING INSPECTION PER AD2000-25-02 R1 CRACKS FOUND IN LT FRONT SPAR APPROXIMATELY THE OUTBOARD 3 FEET AND ON THE RT FRON	T SPAR FROM THE STRUT ATTACH POINT OUTBOARD.  RIB NAILS MISSING ON THE RIB JUST OUTBOARD OF THE STRUT ATTACH POINT AND S	PAR DAMAGE ACROSS THE TOP OF THE SPAR UNDER THE RIB.				1	H	7	1 	3O			 	A802    					 
2002070100023	20020701	00023	EU  	2002	7	1	2002FA0000763    	1	20020615	G	7333	P16575GB4A	TRANSDUCER      			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 	 	EA  					FUEL SYSTEM	FAILED          	G			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF					85005	2856448A			FUEL PRESSURE INDICATION WAS 75 PSI WITH THE ENGINE SHUT DOWN AND THE FUEL BOOST PUMP SHUT OFF.  REMOVED TRANSDUCER AND 	INSTALLED NEW FUEL PRESSURE TRANSDUCER.  GROUND OPERATION OF FUEL SYSTEM CHECKED NORMAL.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2002070100024	20020701	00024	CE  	2002	7	1	2002FA0000765    	1	20020617	G	3230		RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					LANDING GEAR	FAILED          	G			VJ3R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	07	5609S	518  				CE1454	825756R			LANDING GEAR FAILED TO EXTEND IN FLIGHT, GEAR WAS HAND CRANKED DOWN AND A SAFE LANDING WAS MADE.  AIRCRAFT WAS PLACED ON	 JACKS AND THE LANDING GEAR CYCLED IAW MM.  THE RELAY CONTROL STICK IN THE UP POSITION WHEN THE GEAR WAS CYCLED.  RELAY 	WAS REMOVED AND A NEW RELAY INSTALLED.  LANDING GEAR OPERATIONAL CHECK OF THE SYSTEM WAS MADE.  LANDING GEAR CHECKED NOR	MAL.			1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002070100025	20020701	00025	EU  	2002	7	1	2002FA0000766    	1	20020612	G	7333	201030W	TRANSDUCER      			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 	 	EA  					FUEL SYSTEM	LEAKING         	G			VJ3R	O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			WP	07	865AF	99   				85005	2826448A			FUEL FLOW INTERMITTENT WENT TO ZERO IN FLIGHT.  ENGINE FUEL FLOW SYSTEM WAS INSPECTED AND FOUND THAT FUEL FLOW TRANSDUCE	R WAS LEAKING FUEL.  REMOVED TRANSDUCER AND INSTALLED NEW TRANSDUCER.  OPERATIONAL CHECK OF THE ENGINE ON THE GROUND CHE	CKED NORMAL.				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2002070100077	20020701	00077	EU  	2002	7	1	2002FA0000767    	1	20020611	G	3110	B10X15M4X10	SHOCK MOUNT     			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 	 	EA  					COCKPIT	BROKEN          	G			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	99   				85005	2856448A			INSTRUMENT SHOCK MOUNT BROKEN, IT SUPPORTS THE UPPER RIGHT HAND SIDE.  REMOVED BROKEN SHOCK MOUNT AND INSTALLED NEW SHOC	K MOUNT.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2002071100164	20020711	00164	EU  	2002	7	11	2002FA0000768    	1	20020611	G	2434	115TA600009	BRACKET         			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 	 	EA  					ALTERNATOR	CRACKED         	G			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	194  				85004	2826348A			ALTERNATOR BRACKET CRACKED, THIS BRACKET IS USED TO ADJUST THE BELT TENSION.  REMOVED BRACKET AND INSTALLED NEW BRACKET.	  ADJUSTED BELT TENSION IAW MM.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2002071100166	20020711	00166	CE  	2002	7	11	2002FA0000769    	1	20020611	G	3230	583800901	MOTOR           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					LANDING GEAR	NOISY           	G			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8252T					CE1545	820446R			GEAR MOTOR MAKES GRINDING NOISE WHEN THE GEAR IS RETRACTED.  MOTOR WAS REMOVED AND A NEW MOTOR INSTALLED OPERATION OF TH	E GEAR SYSTEM IAW MM, CHECKED NORMAL.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002071100168	20020711	00168	CE  	2002	7	11	2002FA0000770    	1	20020611	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					LANDING GEAR	STICKS          	G			VJ3R	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			WP	07	1569A	162  				CE1328	820447R			LANDING GEAR WOULD NOT RETRACT AFTER TAKE OFF.  AIRCRAFT WAS PLACED ON JACKS AND THE LANDING GEAR CYCLED IAW MM.  INSPEC	TION OF THE SYSTEM FOUND THAT THE DYNAMIC RELAY WOULD STICK IN THE DOWN POSITION.  A NEW DYNAMIC RELAY WAS INSTALLED AND	 THE SYSTEM OPERATIONAL CHECKED NORMAL.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002071100171	20020711	00171	SO  	2002	7	11	2002FA0000771    	2	20020611	G	7324	6314272A20	FLOW DIVIDER    			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					ENGINE	FLUCTUATES      	G			VJ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	8240T	318  				CE1542	825758R			FUEL FLOW FLUCTUATES IN-FLIGHT AND THE ENGINE WAS ROUGH RUNNING AT ALTITUDE, AT LOW ALTITUDE THE ENGINE WAS SMOOTH IN OP	ERATION.  OPERATION CHECK OF ENGINE ON THE GROUND FOUND THE FUEL FLOW DIVIDER WOULD FLUCTUATE.  REMOVED FLOW DIVIDER AND	 INSTALLED A NEW OVERHAULED ASSEMBLY.  GROUND OPERATION OF ENGINE CHECKED NORMAL.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002071500167	20020715	00167	CE  	2002	7	15	2002FA0000772    	1	20020610	G	3710	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					VACUUM SYS	FAILED          	G			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1568P	213  				CE1298	825776RR			UNABLE TO MAKE INSTRUMENT AIR PRESSURE AT LOW RPM, INSPECTED SYSTEM AND FOUND THAT THE PUMP WAS MAKING SMALL CHUNKS OF C	ARBON FOUNDED IN THE REGULATOR AND INLET FILTER.  PURGED SYSTEM AND CLEANED LINES IN SYSTEM.  NEW INLET AND INLINE FILTE	R INSTALLED.  NEW PUMP INSTALLED, SYSTEM GROUND CHECKED, CHECKED NORMAL.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002071500168	20020715	00168	SO  	2002	7	15	2002FA0000773    	1	20020612	G	7921	85487012	BRACKET         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	FAILED          	G			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4175V	107  				2843126	RL2833836A			THIS BRACKET ATTACHES TO THE LEFT SIDE OF ENGINE COOLING BAFFLE AND ALSO SUPPORTS THE OIL COOLER ON THE LEFT HAND REAR C	ORNER.  BRACKET REMOVED AND A NEW BRACKET INSTALLED.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002071100175	20020711	00175	SW  	2002	7	11	2002FA0000774    	1	20020312	G	3246		SPLICE          			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360*       	41514	EA  					RT MLG SKI	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	695AC					39498				RIGHT LANDING GEAR, SKI CABLE CAME LOOSE.  AERO SKI R2800 SKIS INSTALLED.  CABLE IS SMALLER THAN MOST SKI INSTALLATIONS.	  THE NICOPRESS SLEEVE ON THE THIMBLE EYE SPLICE ON THE CABLE END SLIPPED OFF THE CABLE.  CABLE CAME LOOSE FROM AIRFRAME	.				1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002071500169	20020715	00169	SW  	2002	7	15	2002FA0000775    	1	20020312	G	2910		FITTING         			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360*       	41514	EA  					HYD SYSTEM	BROKEN          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AL	05	695AC					39498				PLASTIC T FITTING IN HYDRAULIC LINE BETWEEN RESERVOIR AND BRAKE CYLINDERS BREAKS OFF.  THIS ALLOWS THE BRAKE FLUID TO ES	CAPE.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002071700097	20020717	00097	CE  	2002	7	17	2002FA0000776    	1	20020313	G	3010		DUCT            			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6*        	52043	EA  					DEICE SYSTEM	COLLAPSED       	G				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			WP	11	948CC	8773 				LW236				AT STATION 277 IS THE HEATER REGISTER LOCATED FORWARD OF THE LAVATORY.  TWO INCHES FROM THE HEAT DUCTING IN THIS AREA IS	 THE (1010 EV A .6250 IMPERIAL) TUBING THAT SUPPLIES PNEUMATIC PRESSURE TO THE EMPENNAGE DEICE BOOTS.  THIS EMPENNAGE DE	ICE BOOT TUBING WAS COLLAPSED FROM APPROXIMATELY 11 INCHES AFT OF STATION 277 TO APPROXIMATELY NINE INCHES FORWARD OF ST	ATION 277.  THIS DUCTING SHOWED SIGNS OF HEAT DISTRESS THROUGHOUT THE RUN UNDER THE RIGHT CABIN FLOORBOARDS, THOUGH NOT 	AS SEVERE AS WHERE THE DUCTING NECKS DOWN TO A SMALLER DIAMETER.		1	L	7	2 	3T	3	T	 	3A20    	E2NE				 
2002070800058	20020708	00058	WP  	2002	7	8	2002FA0000779    	1	20020426	G	2822		SEAL            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL PUMP	LEAKING         	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	5074R					1151D				AFTER OIL SEAL REPLACEMENT, AND REINSTALLATION OF FUEL PUMP, THE PUMP SHAFT SEAL WAS DISCOVERED LEAKING.  DURING BOOST P	UMP OPERATION FOR BLEEDING , FUEL SYSTEM ABOUT 50/60 + PER MINUTE DROP LATE.  REPLACED PUMP					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002071100176	20020711	00176	EA  	2002	7	11	2002FA0000780    	2	20020514	G	7314	LW15473	PUMP            								LYC   	O540  	IO540*      	41532	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			NE	03		318  					L1852248A			PILOT REPORTS FUEL PRESSURE WAS LESS AND LESS WITH EACH FLIGHT.  PILOT STATED:  A PROGRESSIVE FAILURE MODE.  INSTALLED N	EW PUMP AND FOUND FUEL PRESSURE NORMAL.										3	O			1E4				 
2002071500170	20020715	00170	NE  	2002	7	15	2002FA0000781    	2	20020601	G	8530	45937	ROCKER SHAFT    			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R1340*      	52016	NE  					ENGINE	DEPARTED        	D			UJBG	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CE	09	48485	185  				44B	15771			WHILE FLYING, NR 3 ROCKER SHAFT ON EXHAUST VALVE EXITED THE AIRCRAFT CAUSING THE ENGINE TO LOSE POWER.  AIRCRAFT MADE A 	FORCED LANDING INTO A PLOWED FIELD CAUSING THE AIRCRAFT TO FLIP OVER.  THE ENGINE HAD 185 HOURS SINCE OVERHAUL, PART COU	LD NOT BE FOUND, BUT SUSPECT IT FAILED IN THE THREAD AREA NEXT TO THE SMALL NUT.				1	Q	7	1 	3R	3	R	 	1A16    	5E2				 
2002071100177	20020711	00177	SO  	2002	7	11	2002FA0000783    	2	20020122	G	7421	RHB32E	SPARK PLUG      			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT ENGINE	FOULED          	G				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NE	01	37150	400  				414A0251				PILOT REPORTED ROUGH RUNNING ENGINE (RIGHT SIDE) AT ALTITUDE.  LANDED AND FOUND SPARK PLUGS WORN AND FOULED, INSTALLED C	LEAN AND GAPED SET.  RUN UP AND REMAINDER OF FLIGHT NORMAL.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002071100178	20020711	00178	CE  	2002	7	11	2002FA0000784    	1	20020612	G	2510	051422713	SEAT            			CESSNA	172   	172R        	2072401	CE  										COPILOT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	98682	779  				17280604				1.5 INCH CRACKS ON COPILOTS SEAT CUSHION BASE.  REPLACED WITH NEW PART WHICH IS TWICE AS THICK.						1	H	7	1 	3O			NT	3A12    					 
2002071100179	20020711	00179	CE  	2002	7	11	2002FA0000785    	1	20020608	G	3230	089400011	GEAR            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					LANDING GEAR	WORN            	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			WP	13	5403M					402B0003	7910838			DURING LANDING GEAR RETRACTION PILOT REPORTED LAND GRINDING NOISE.  CAUSED BY WORN OUT GEAR BOX INTERNAL SYSTEM.  INSPEC	TED WORN OUT GEARS TOOTH.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002071100180	20020711	00180	SO  	2002	7	11	2002FA0000787    	1	20020604	G	7120	8193702	MOUNT           			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	05	529TX	1835 				4622045				FAILURE DURING LANDING.  ENGINE MOUNT REVEALED THAT THE RIGHT SIDE OF THE NOSE GEAR ACTUATOR, AFT ATTACH POINT, HAD SEPA	RATED FROM THE TUBE CLUSTER ON THE MOUNT ASSEMBLY.					1	L	7	1 	3O	3	O	RT	A25SO   	1E4				 
2002071500172	20020715	00172	CE  	2002	7	15	2002FA0000790    	1	20020606	G	5510	12326241	BRACKET         			CESSNA	210   	T210N       	2073456	CE  	CONT  	O550  	IO550*      	 	SO  					HORIZ STAB	BROKEN          	B			MI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	6468N					21063042	289167R			AIRCRAFT UNDERGOING ANNUAL INSPECTION. HORIZONTAL STABILIZER FOUND LOOSE.  INSPECTED AND FOUND REAR MOUNTING REINFORCEME	NT BRACKET BOTH SIDES BROKEN AND THE FORWARD ATTACHMENT FITTINGS LOOSE.  INSTALLED REAR BRACKETS AND PN SK210-126.					1	H	7	1 	3O	3	O	 	3A21    	E3SO				 
2002071700101	20020717	00101	SO  	2002	7	17	2002FA0000794    	1	20020601	G	2810		TANK            			LUSCOM	8     	8A          	8190104	SO  	CONT  	A65   	A65*        	17003	SO  					LT WING	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	71170					2597				WING TANKS INSTALLED IN THIS AIRCRAFT DURING 200-2001 WING RECOVER.  TANKS REMOVED FOR REPAIR AFTER COMPLAINT ABOUT LEAK	AGE. RIGHT TANK HAD LEAKED AT WELD SEAM AND WAS PREVIOUSLY REPAIRED BY OWNER.  LEFT TANK HAD A LEAK AT THE ROOT OF TANK 	IN THE WELD BEAD WHERE FLANGES WERE JOINED BY WELDING THE BASE METALS TOGETHER AT A PARALLEL LAP JOINT (NO FILLER).  THI	S JOINT APPEARS TO BE SMOOTH AND WELL FORMED.  NOTED DAMAGE IN THE FORM OF SOME TOOL MARKS, PART DEFORMITIES, BENDING AN	D BULGES WHICH WOULD INCREASE STRESS TO THE WELD JOINTS IN SERVICE.		1	H	7	1 	3O	3	O	 	A694    	E205				 
2002071100181	20020711	00181	CE  	2002	7	11	2002FA0000795    	1	20020606	G	7111	S13602AL	CIRCUIT BREAKER 			CESSNA	337   	337D        	2075717	CE  										COWL FLAP SYS	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	86076	75   				3371067				CIRCUIT BREAKER FAILED INTERNALLY WITHOUT TRIPPING.  CAUSED OPEN CIRCUIT TO COWL FLAP MOTORS.  FAILURE OCCURRED DURING G	ROUND MAINTENANCE.  NEED TO IMPROVE QUALITY CONTROL IN PRODUCTION.					1	H	7	2 	3O			 	A6CE    					 
2002071900095	20020719	00095	SO  	2002	7	19	2002FA0000796    	2	20020328	G	7314	6381563	PUMP            			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  					FUEL SYSTEM	FAILED          	B			RV3R	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	15	8130Z					2050130	77235OE			ENGINE LOST POWER, AIRCRAFT LANDED OFF AIRPORT.  FOUND FUEL CONTAMINATION AND FUEL PUMP PRESSURE RELIEF VALVE STUCK.  AD	841001, WAS SIGNED OFF BUT FUEL HEADER TNKS WERE CONTAMINATED AND NO DRAIN VALVES HAD BEEN INSTALLED.  CUSTOMER WAS NOTI	FIED THAT PUMP HAD TRASH IN AND AROUND RELIEF VALVE AREA.  SAMPLES WERE TAKEN AND SENT TO CUSTOMER FOR IDENTIFICATION.  	ENTIRE FUEL SYSTEM MUST BE CLEANED TO REMOVE ALL OF THIS MATERIAL OR IT WILL GET INTO THE PUMP AGAIN, VOIDING ANY WARRAN	TY ON FUEL PUMP, AND COULD POSSIBLY CAUSE ENGINE FAILURE.		1	H	7	1 	3O	3	O	 	3A21    	3E1				 
2002071500173	20020715	00173	SO  	2002	7	15	2002FA0000798    	1	20020619	G	2460	150905	RELAY           			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360*    	17025	SO  					ELECTRICAL SYS	BURNED          	B			RSUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	8106H					28R8031012				HAVE FOUND 2-3 RELAYS WITHIN PAST MONTH WITH BURNED CONNECTION TO MFG.  THE MAIN BUSS CONNECTIONS OVER TIME HAVE TURNED 	BLACK AND HAVE ULTIMATELY FAILED.					1	L	7	1 	3O	3	O	 	2A13    	E9CE				 
2002071100182	20020711	00182	CE  	2002	7	11	2002FA0000800    	1	20020516	G	5751	03225709	HINGE BRACKET   			CESSNA	190   	190         	2072902	CE  										AILERON	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	9854A					7547				THESE BRACKETS ARE MADE OF MAGNESIUM AND ARE CORRODING AND CRACKING TO AN ALARMING DEGREE.						1	H	7	1 	3R			NC	A790    					 
2002071100183	20020711	00183	CE  	2002	7	11	2002FA0000801    	1	20020516	G	5751	0322709	HINGE BRACKET   			CESSNA	195   	195B        	2073112	CE  										AILERON	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	2165C					16150				THESE BRACKETS ARE MADE OF MAGNESIUM AND ARE CORRODING AND CRACKING TO AN ALARMING DEGREE.						1	H	7	1 	3R			 	A790    					 
2002071100184	20020711	00184		2002	7	11	2002FA0000803    	4	20020503	G	2561	PA5	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED.  THE MANUFACTURER RECOMMENDED PRESSURE TEST. DOM: JUNE 1983																			 
2002071100185	20020711	00185		2002	7	11	2002FA0000804    	4	20020503	G	2561	KS35P0701117	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED.  THE MANUFACTURER  RECOMMENDED PRESSURE TEST.  DOM:  JUNE 1983.																			 
2002071500174	20020715	00174	EA  	2002	7	15	2002FA0000807    	2	20020618	G	8540	LW15659	DRIVE GEAR      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENGINE	SEIZED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	8154J	219  				448095020	23572T			MAGNETO DRIVE GEAR WAS SEIZED TO CRANKCASE BUSHING WHICH WAS SPINNING IN ITS CRANKCASE BORE.  THIS ENGINE HAD ONLY 219 H	OURS SINCE FACTORY REMANUFACTURE.  THE OPPOSITE ENGINE WHICH ALSO HAD 219 HOURS SINCE FACTORY REMANUFACTURE EXHIBITED TH	E EXACT SAME PROBLEM.  BOTH ENGINES WERE REMOVED AND SENT OUT FOR REPAIR.				1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002071900104	20020719	00104	EA  	2002	7	19	2002FA0000808    	2	20020701	G	8520		CRANKSHAFT      			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	5859Q					795				NR 3 CYLINDER AND ROD LOOSE FROM CRANKSHAFT AND CASE HALF SENT TO HALF SENT TO REPAIR FACILITY.  THEY SAID WRONG OIL PUM	P GEARS.  FAILED PUMP OIL STARVATION DESTROYED CRANK SHAFT AND ENGINEER.					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2002071500175	20020715	00175	EA  	2002	7	15	2002FA0000810    	2	20020618	G	8530	70310	SEAL            			AMTR  	S1C   	S1C         	       	GL  	LYC   	O360  	IO360B4A    	41514	EA  					ENGINE	FAILED          	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	05	6DD					1DD				PUSH ROD SHROUD SEAL FAILED, CAUSING OIL LEAK.						1	Q	7	1 	3O	3	O	NC	EXPA1Q71	1E10				 
2002071900107	20020719	00107	EU  	2002	7	19	2002FA0000812    	1	20020605	G	3520		DOOR            			AMD   	FALC90	FALCON900EX 	2730009	EU  										OXYGEN SYSTEM	STUCK           	C				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	11	404A	1512 				56				WHILE PERFORMING MAINTENANCE TASK 35.200, ITEM 6, SELECTION OF OXYGEN CONTROLLER TO OVERIDE, SIX PASSENGER OXYGEN MASK D	OORS FAILED TO OPEN FULLY AND DEPLOY THE MASKS. FIVE OF THE DOORS OPENED APPROXIMATELY .250 INCHES AND THE SIXTH DOOR FA	ILED TO OPEN. INSPECTION OF THE OXYGEN MASK DOORS INDICATED THAT THEY WERE STICKING TO THE LEATHER COVERING ON THE DOORS	 OR ON INTERIOR FOAM. THE OXYGEN MASKS WERE INSPECTED AND RE-SECURED. MAINTENANCE TASK 35.200, ITEM 6 WAS REPEATED AND A	LL PASSENGER OXYGEN MASKS DEPLOYED PROPERLY.  DURING THE INITIAL INSPECTION, IT WAS ALSO NOTED THAT FORWARD CABIN SEAT R	2 OXYGEN MASK'S FLEXIBLE OXYGEN SUPPLY HOSE WAS NOT CONNECTED TO THE OXYGEN SUPPLY FIRTREE.	2	L	7	3 	4F			RT	A46EU   					 
2002071800188	20020718	00188	EA  	2002	7	18	2002FA0000818    	2	20020625	G	7314		WASHER          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL PUMP	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	503ER	1071 				172S8003	L2267651A			DURING SCHEDULED TIME CHANGE OF THE ENGINE-DRIVEN FUEL PUMP, THE SMALL RETAINING WASHER FOR THE PUMP SHAFT SPRING WAS FO	UND BROKEN.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002071800189	20020718	00189	CE  	2002	7	18	2002FA0000819    	1	20020627	G	3246	1228100781	WHEEL           			BEECH 	2000  	2000        	1152000	CE  										MLG	DESTROYED       	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			SO	35	786BP	346  	71   			NC28				RIGHT INBOARD WHEEL AND TIRE ASSEMBLY DEPARTED THE AIRCRAFT AFTER TAKEOFF.  WHEEL BEARING HAD  DISINTEGRATED.  INSPECTIO	N REVEALED NR 2 WHEEL BEARINGS SPALLED AND NR 4 WHEEL BEARINGS OVERHEATED.  71 HOURS SINCE INSPECTION AND LUBE.  RECOMME	ND MORE FREQUENT LUBE INTERVAL OR REDESIGN WITH LARGER BEARING.				1	L	7	2 	4T			RT	A38ACE  					 
2002071900118	20020719	00118		2002	7	19	2002FA0000820    	4	20020628	G	3422	S25031	ELBOW           			CESSNA	172   	172S        	2072439	CE  										GYRO	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	17ER	838  				172S8921				FOUND PLASTIC ELBOW AT DIRECTIONAL GYRO CRACKED CAUSING INSTRUMENT TO PRECESS.						1	H	7	1 	3O			NT	3A12    					 
2002071900034	20020719	00034	EA  	2002	7	19	2002FA0000821    	2	20020629	G	8530	19001	EXHAUST VALVE   								LYC   	O320  	O320E2G     	41508	EA  					NR 3 CYLINDER	BROKEN          	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	05		2351 	466  				L4805127A			REPLACED NR 3 CYLINDER & PISTON DUE TO EXHAUST VALVE SEPARATION & DAMAGE TO CYLINDER CAUSED BY NOT REPLACING NEEDED PART	S AT M.O.H. (466.6-HRS S.M.O.H.) TOTAL TIME ON P/N 19001 EXHAUST VALVES 2351.6-HRS. THERE IS NO RECORD OF THE EXHAUST & 	INTAKE VALVES, EXHAUST GUIDES OR PISTONS REPLACED AT M.O.H.  WE ACCOMPISHED T.O.H. ON ALL CYL'S BY REPLACING ALL VALVES,	 EXHAUST GUIDES, PISTONS, RINGS, GASKETS & SEALS. ON TEAR-DOWN WE FOUND INTAKE & EXHAUST ROCKERS REVERSED, INVERTED VALV	E SPRINGS, ROCKER SHAFT THRUST BUTTONS DETERIORATED & WRONG SIZE PUSH RODS. ALSO NO ORANGE PAINT TO DESEGINATE CHROME CY	LINDERS'S.						3	O			E274				 
2002071900035	20020719	00035	CE  	2002	7	19	2002FA0000822    	1	20020702	G	7602	S29991	SWIVEL          			CESSNA	337   	T337G       	2075726	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					MIXTURE CABLE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	265	150  				P3370232				THIS ITEM IS INSTALLED ON A CESSNA T337G THAT HAS HAD TCM TSIO-520 ENGINES INSTALLED AS AN STC MODIFICATION. THE PART IS	 A BALL-TYPE SWIVEL THAT CONNECTS THE MIXTURE CABLE TO THE MIXTURE CONTROL ARM. THE BALL HAS PULLED OUT OF ITS SWAGED HO	USING. THIS IS THE THIRD SUCH FAILURE IN 177 HOURS.				1	H	7	2 	3O	3	O	 	A6CE    	E8CE				 
2002071900036	20020719	00036	CE  	2002	7	19	2002FA0000823    	1	20020705	G	3213	05412024	BUSHING         			CESSNA	172   	172S        	2072439	CE  										LT MLG	DEBONDED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	243SP	1928 				172S8212				DURING A PHASE INSPECTION FOUND THE RUBBER TYPE BUSHING HAD BECOME LOOSE AND SLID DOWN THE LEFT GEAR LEG, RESULTING IN M	ETAL TO METAL CONTACT OF THE GEAR LEG AND BUSHING SLEEVE. JACKED A/C, REMOVED GEAR LEG AND OLD BUSHING. INSPECTED GEAR L	EG, FOUND DAMAGE LIMITED TO PAINTED SURFACES, REPAINTED GEAR LEG AS NEEDED, INSTALLED NEW BUSHING ASSEMBLY, REINSTALLED 	GEAR LEG. BLED BRAKES AND RETURNED TO SERVICE.			1	H	7	1 	3O			NT	3A12    					 
2002071900037	20020719	00037	CE  	2002	7	19	2002FA0000824    	1	20020708	G	3110	S337711	SWITCH          			CESSNA	172   	172S        	2072439	CE  										INTRUMENT PANEL	FAILED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	30	948SP	1652 				172S8144				DURING MAINTENANCE PRE-RUN FOR PHASE INSPECTION, WHEN MASTER AVIONICS SWITCH WAS TURNED OFF, ONLY HALF OR THE AVIONICS C	OMPONENTS TURNED OFF.  ONE SIDE OF THE SWITCH FAILED IN THE ON POSITION.  REPLACED SWITCH, OPERATIONAL CHECKED SAT.					1	H	7	1 	3O			NT	3A12    					 
2002071900038	20020719	00038	SO  	2002	7	19	2002FA0000825    	2	20020523	G	8530	652541	NUT             			CESSNA	182   	182J        	2072722	CE  	CONT  	O470  	O470S       	17026	SO  					CYLINDER	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3090F	73   				18257190	226264R			DURING CYLINDER INSTALLATION  P/N 652541 NUT CRACKED DURING TORQUEING OPERATION.    FAILURE AT ABOUT 60 FT/LBS						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002071900119	20020719	00119	SO  	2002	7	19	2002FA0000830    	2	20020717	G	8530		PISTON PIN      			CESSNA	172   	R172E       	2072413	CE  	CONT  	O360  	IO360DB     	17025	SO  					NR 6 CYLINDER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	30	146AC	1051 				R1720147	808811R			ENGINE OIL FILTER INSPECTED DURING 100 HOUR INSPECTION, FOUND EXCESSIVE AMOUNT OF ALUMINUM FLAKES IN FILTER.  CAUSE OF M	ETAL IN OIL FILTER TRACED TO NR 6 CYLINDER PISTON PIN PLUG.  WHEN CYLINDER WAS REMOVED THE FWD PLUG HAD EXCESSIVE WEAR. 	 THIS WAS A FACTORY REMANUFACTURED ENGINE AND THIS CYLINDER WAS NOT REMOVED SINCE REMANUFACTURE.   THE PISTON PIN PLUGS 	WERE REPLACED AND THE CYLINDER OVERHAULED & REINSTALLED.  NO MORE METAL HAS BEEN DETECTED IN THE OIL FILTER.			1	H	7	1 	3O	3	O	 	3A17    	E1CE				 
2002071900076	20020719	00076	SW  	2002	7	19	2002FA0000831    	1	20020718	G	5711	5263	SPAR CAP        			BBAVIA	7     	7ECA        	21101NN	SW  										RT WING	CRACKED         	D				K				NONE                    				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			WP	29	6312N	2593 	4    			308				DURING COMPLIANCE WITH AD 00-25-02R1, THE RIGHT WING REAR SPAR WAS FOUND TO HAVE A COMPRESSION CRACK AT THE AILERON CENT	ER HINGE ATTACH BRACKET, UPPER HOLE. THE CRACK IS VISIBLE ON THE FORWARD AND AFT FACE OF THE SPAR EXTENDING UP FROM THE 	BOLT HOLE AND ACROSS THE SPAR CAP. THE INSPECTION WAS ACCOMPLISHED USING A FLEXIBLE BORESCOPE AS PER SERVICE BULLETIN 40	6 INSTRUCTIONS.			1	H	7	1 	3O			 	A759    					 
2002071900167	20020719	00167	SO  	2002	7	19	2002FA0000832    	2	20020702	G	7414		MAGNETO         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	FAILED          	B			FFKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	11HW	3    				TH271				ON A GROUND RUN UP, PILOT REPORTED A BAD MAG DROP.   AFTER PULLING MAGNETO OFF OF THE ENGINE,  IT APPEARS THE MAGNETO FA	ILED.  THE PLASTIC DRIVE GEARS WERE STRIPPED AS WELL AS THE MAGNETO RETAINER DRIVE COUPLING AND DRIVE COUPLING RUBBER BU	SHING WERE DAMAGED.  NO OTHER DAMAGE WAS FOUND ON THE ENGINE.				1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002071900169	20020719	00169	SO  	2002	7	19	2002FA0000833    	2	20020530	G	8530	SA539988	INTAKE VALVE    			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	FAILED          	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	61858	563  				18052807				THIS ENGINE WAS OVERHAULED 6/10/99 BY REPAIR STATION, IT NOW HAS 563 HOURS AND ALL THE INTAKE VALVES WERE BAD, ALL EXHAU	ST GUIDES WERE BAD, AND ALL LIFTERS ARE BAD.  CYLINDERS WERE NEW FROM PARTS MFG AND SUPPLY.  THIS AIRCRAFT HAS NOT SET F	OR OVER 1 MONTH AT A TIME, USED HEAVY IN THE SUMMER.  THIS IS THE 3RD TIME THIS AIRFRAME HAS HAD LIFTER TROUBLES IN 3 EN	GINES, ALL GOING ABOUT 600 HOURS.			1	H	7	1 	3O	3	O	 	5A6     	E273				 
2002071900170	20020719	00170	SO  	2002	7	19	2002FA0000834    	2	20020530	G	8530	SA643767	GUIDE           			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	FAILED          	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	61858	563  				18052807				THIS ENGINE WAS OVERHAULED 6/10/99 BY REPAIR STATION.  IT NOW HAS 563.3 HOURS AND ALL THE INTAKE VALVES WERE BAD, ALL EX	HAUST GUIDES WERE BAD, AND ALL LIFTERS ARE BAD.  CYLINDERS WERE NEW FROM PARTS MFG AND SUPPLIER. THIS AIRCRAFT HAS NOT S	ET FOR OVER 1 MONTH AT A TIME USED HEAVY IN THE SUMMER.  THIS IS THE 3RD TIME THIS AIRFRAME HAS HAD LIFTER TROUBLES IN 3	 ENGINES ALL GOING ABOUT 600 HOURS.			1	H	7	1 	3O	3	O	 	5A6     	E273				 
2002071900171	20020719	00171	SO  	2002	7	19	2002FA0000835    	2	20020530	G	8520	SA646277	LIFTER          			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	FAILED          	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	61858	563  				18052807				THIS ENGINE WAS OVERHAULED 6/10/99 BY REPAIR STATION.  IT NOW HAS 563.3 HOURS AND ALL THE INTAKE VALVES WERE BAD, ALL EX	HAUST GUIDES WERE BAD, AND ALL LIFTERS ARE BAD.   CYLINDERS WERE NEW FROM PARTS MFG AND SUPPLY. THIS AIRCRAFT HAS NOT SE	T FOR OVER 1 MONTH AT A TIME USED HEAVY IN THE SUMMER.  THIS IS THE 3RD TIME THIS AIRFRAME HAS HAD LIFTER TROUBLES IN 3 	ENGINES ALL GOING ABOUT 600 HOURS.			1	H	7	1 	3O	3	O	 	5A6     	E273				 
2002071900172	20020719	00172	SO  	2002	7	19	2002FA0000836    	2	20020530	G	8520	SA628488	LIFTER          			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	FAILED          	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	61858	563  				18052807				THIS ENGINE WAS OVERHAULED 6/10/99 BY REPAIR STATION.  IT NOW HAS 563.3 HOURS AND ALL THE INTAKE VALVES WERE BAD, ALL EX	HAUST GUIDES WERE BAD, AND ALL LIFTERS ARE BAD.  CYLINDERS WERE NEW FROM PARTS MFG AND SUPPLY.  THIS AIRCRAFT HAS NOT SE	T FOR OVER 1 MONTH AT A TIME USED HEAVY IN THE SUMMER.  THIS IS THE 3RD TIME THIS AIRFRAME HAS HAD LIFTER TROUBLES IN 3 	ENGINES ALL GOING ABOUT 600 HOURS.			1	H	7	1 	3O	3	O	 	5A6     	E273				 
2002072200001	20020722	00001	CE  	2002	7	22	2002FA0000837    	1	20020625	G	2720	0400107150	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  										COPILOT PEDALS	FAILED          	B			LN3R	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	48803	518  				15280973				THE PILOT COMPLAINED OF COPILOTS LEFT RUDDER PEDAL BEING LOOSE AND NOT VERY RESPONSIVE.  INSPECTED PEDALS AND RUDDER CAB	LE SYSTEM.  FOUND RIGHT RUDDER CABLE AT AFT FUSELAGE BULKHEAD HOLDING BY TWO STRANDS, FORWARD OF WHERE CABLE COMES OUT O	F FUSELAGE TO ATTACH TO RUDDER ON LEFT SIDE.  THE MFG IPC CALLS THE COPILOTS LEFT RUDDER CABLE THE RIGHT RUDDER CABLE.  	THE CABLE HAD WORN THROUGH THE PHENOIC ON THE AFT BULKHEAD WHERE CABLE COMES THROUGH AND WEARING ON THE BULKHEAD.  INSTA	LLE NEW PIECE OF PHENOLIC TO KEEP THE CABLE FROM WEARING ON THE BULKHEAD AT FS 173.41.  THIS PART WOULD HAVE FAILED WITH	IN A FEW HOURS.  IT APPEARS THE DAMAGE WAS CAUSED BY THE WAY THE CABLE WAS ROUTED AT LAST REPLACEMENT 518.0 HOURS AGO.	1	H	7	1 	3O			NT	3A19    					 
2002072300076	20020723	00076	SO  	2002	7	23	2002FA0000838    	1	20020628	G	8120	60051004	HOUSING         			PIPER 	PA34  	PA34200T    	7103406	SO  										TURBOCHARGER	CRACKED         	B			YXUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	749LW		1381 			347770416				TURBINE HOUSING HAS A 1 INCH CRACK BEYOND LIMITS DESCRIBED IN AD.						1	L	7	2 	3O			 	A7SO    					 
2002072300078	20020723	00078	GL  	2002	7	23	2002FA0000839    	1	20020604	G	3222	111020	SPRING          			AMTR  	CA7   	CA7         	05610EB	GL  										TAIL WHEEL	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	753KD	119  								TAIL SPRING BROKE FORWARD OF TAIL WHEEL ATTACH AREA.  PREVIOUS DAMAGE NOTED AT SPRING CRACKED/BROKEN AREA.						1	H	7	1 	3T			NT	EXPA1H71					 
2002072300080	20020723	00080	CE  	2002	7	23	2002FA0000840    	1	20020614	G	5220	08911077	WINDOW          			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520*    	17040	SO  					EMERGENCY EXIT	DEPARTED        	B				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CE	07	87RJ					310R0676				EMERGENCY WINDOW EXIT DEPARTED AIRCRAFT IN FLIGHT, IN RAIN SHOWER.  ALL CABLE PINS BENT.  VERY DIFFICULT TO SEE WITH INT	ERIOR INSTALLED.					1	L	7	2 	3O	3	O	 	3A10    	E8CE				 
2002072300081	20020723	00081	SO  	2002	7	23	2002FA0000841    	1	20020510	G	5753	6232800	ATTACH FITTING  			PIPER 	PA34  	PA34200     	7103405	SO  										RT TE FLAP	FAILED          	G			W5YS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	15024	10000				347250349				THE OUTBOARD ATTACH POINTS (2) OF THE RT FLAP FAILED IN FLIGHT.  INSPECTION OF THE FLAP INTERIOR FOUND THE FAILURE WAS C	AUSED BY HEAVY CORROSION AT THE STEEL TO ALUMINUM INTERFACE OF THE FLAP NOSE RIBS AND BRACKET.					1	L	7	2 	3O			 	A7SO    					 
2002072300082	20020723	00082		2002	7	23	2002FA0000842    	4	20020604	G	6113	12504192	SPINNER         			CESSNA	210   	210L        	2073448	CE  	CONT  	O550  	IO550*      	 	SO  					PROPELLER	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			EA	11	59176					21060142				SPINNER DEPARTED AIRCRAFT WHILE IN FLIGHT.  PARTS OF SPINNER AND HARDWARE STILL ATTACHED TO BULKHEAD.						1	H	7	1 	3O	3	O	 	3A21    	E3SO				 
2002072300085	20020723	00085	EA  	2002	7	23	2002FA0000843    	2	20020701	G	8500		ENGINE          			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  					NOSE	FIRE            	D				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			WP	07	33439					287515299	L40784			FIRE OCCURED IN ACCESSORY AREA OF ENGINE DURING START RESULTING IN MINOR DAMAGE.  UPON POST FIRE INSPECTION, ONLY DEFECT	 FOUND WAS BROKEN AND SEVERLY BURNED RUBBER PRIMER HOSE ADJACENT TO EGT PROBE.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002072300098	20020723	00098	GL  	2002	7	23	2002FA0000844    	2	20020701	G	7210	23064640	GEARBOX         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	MISMANUFACTURED 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										UPON INSPECTION BEFORE GEARBOX ASSEMBLY.  SCAVENGE TUBE CUT OUT NOT WIDE ENOUGH, CAUSING TUBE TO RUB.  2 EACH STUDS NOT 	FULLY SEATED AT N1 PICKUP AREA.  OIL PUMP INSERTS NOT CLEANED OUT.  ASSURE PROPER MANUFACTURING AND INSPECTED BY QA BEFO	RE LEAVING FACTORY.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002072300100	20020723	00100	SO  	2002	7	23	2002FA0000845    	1	20020628	G	8120	60051004	HOUSING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360E   	17025	SO  					TURBOCHARGER	CRACKED         	B			YXUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	749LW		1381 			347770416	306120			TURBINE HOUSING  TYPE C STAGE 1 CRACK BEYOND LIMITS DESCRIBED IN AD.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002072300182	20020723	00182	EA  	2002	7	23	2002FA0000847    	2	20020715	G	8500		ENGINE          			UNIVAR	108   	1083        	9230408	NM  	FRNKLN	6A4165	6A4165B3    	27025	EA  					NACELLE	SHUTDOWN        	G				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			EA	13	6678M						32712			ENGINE SHUT DOWN ON CLIMB OUT AT APPROX. 80 FEET, ALTITUDE.  VISUAL EXAMINATION REVEALED NO OBVIOUS REASON FOR THE FAILU	RE.  FUEL VENTING AND QUANTITY WERE COMPROMISED BY THE CRASH IMPACT  AFTER RECOVERY EFFORTS WERE COMPLETE FUEL WAS PUT I	N THE RIGHT WING TANK AND THE ENGINE WAS EASILY STARTED AND RAN WITH NO MALFUNCTIONS.				1	H	7	1 	3O	3	O	 	A767    	E238				 
2002072400002	20020724	00002	CE  	2002	7	24	2002FA0000848    	1	20020711	G	5310	051313211	BRACKET         			CESSNA	172   	172I        	2072426	CE  										FUSELAGE	CRACKED         	D			DBWS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	35605	5983 				17256859				DURING INSPECTION TO DETERMINE WHY INDUCTION AIR FILTER WAS RUBBING AGAINST OPENING IN LOWER ENGINE COWL.  IT WAS FOUND 	THAT THE LT UPPER FIREWALL WAS FILLED FORWARD APPROX  .2500 INCH WHERE ENGINE MOUNT ATTACHED TO FIREWALL.  AFTER REMOVEI	NG INTERIOR PANEL FORWARD OF LT ENTRANCE DOOR IT WAS DETERMINED THAT BRACKET, WHICH HAS A HOLE FOR THE UPPER LT ENGINE M	OUNT BOLT.  BRACKET WAS CRACKED COMPLETELY IN TO TWO PARTS.  PART WITH BOLT HOLE HAD SHEARED THE TWO RIVET THAT ATTACH B	RACKET TO STRINGER ASSY.  ENGINE MOUNT UPPER LEFT WHEN ALLOWED ENGINE WEIGHT TO PULL FIREWALL FORWARD.  SUSPECT HARD LAN	DING AT SOME TIME IN PAST.	1	H	7	1 	3O			NT	3A12    					 
2002072400003	20020724	00003	SO  	2002	7	24	2002FA0000849    	1	20020718	G	5313		STRINGER        			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	6174P					241275				DURNING ANNUAL INSPECTION FOUND RIVETS SHEARED AND MISSING FROM HOLES ON RIGHT REAR WING SPAR ATTACH FITTING ASSY. THIS 	ASSEMBLY IS ATTACHED TO CENTER SECTION.  CARRY THRU UNDER BAGGAGE COMPARTMENT FLOOR.  ALSO ON THIS AC THE STRINGER WAS C	RACKED AND BUCKLED.  THIS STRINGER IS ATTACHED TO THE RIGHT FRONT WING ATTACH POINT, PREVIOUSLY THE BULKHEAD ASSY (PN 20	614-11) HAD BEEN REPLACED.  THIS IS ANOTHER RIGHT FRONT WING ATTACH POINT BRACKET.			1	L	7	1 	3O	3	O	 	1A15    	E295				 
2002072400004	20020724	00004	SO  	2002	7	24	2002FA0000851    	1	20020705	G	2400		WIRE            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O320  	O320A2B     	41508	EA  					MAIN POWER	SHORTED         	G				A				UNSCHED LANDING         				A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		AP	APPROACH       	1			SO	05	43134					347450150	L874427			ON APPROACH TO LANDING, PILOT REPORTED ELECTRICAL FIRE UNDER INSTRUMENT PANEL.  COCKPIT FILLED WITH SMOKE AND FLAMES WER	E NOTED UNDER PANEL BEHIND GLOVE BOX.  PILOT WAS ABLE TO LAND THE AIRCRAFT BUT THE FIRE DESTROYED THE AIRCRAFT.  THE POW	ER WIRE FROM THE RELAY ON THE FIREWALL WAS BURNED FROM THE RELAY TO THE POINT WHERE IT GOES THROUGH THE FIREWALL.				1	L	7	2 	3O	3	O	 	A7SO    	E274				 
2002072400005	20020724	00005	CE  	2002	7	24	2002FA0000852    	1	20020705	G	7160		DOOR            			CESSNA	177   	177RG       	2073709	CE  										ALTERNATE AIR	SEPARATED       	G				O				OTHER                   				D	Y	J	INFLIGHT SEPARATION       	ENGINE STOPPAGE           	WARNING INDICATION        	NR	NOT REPORTED   	1			EA	17	8200G	3126 				177RG0100				ALTERNATE AIR DOOR CAME LOOSE FROM PLENUM CHAMBER.  DOOR WENT INTO FUEL SERVO INLET, CAUSING ENGINE TO QUIT.						1	H	7	1 	3O			 	A20CE   					 
2002072400006	20020724	00006	EU  	2002	7	24	2002FA0000853    	1	20020723	G	7820		MUFFLER         			GROB  	G115  	G115C       	1660303	EU  	LYC   	O320  	O320D1A     	41508	EA  	SNSNCH	74D	74DM        	EA  	EXHAUST STACK	SEPARATED       	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			WP	03	115FN					82061C1	L1838939A	A55759		RT MUFFLER/EXHAUST LITERALLY FELL APART IN FLIGHT. BEYOND REPAIR. THE INLET FLANGE/PIPE ASSEMBLY COMPLETELY BROKE LOOSE 	FROM THE MUFFLER BODY. THE EXHAUST HANGAR, A RUBBER STRAP, WAS THE ONLY PART SECURING THE MUFFLER BODY TO THE AIRFRAME. 	THIS PART WAS PREVIOUSLY REPLACED APPROXIMATELY 500 HOUR PREVIOUSLY. THIS IS A CHRONIC PROBLEM WITH THESE MAKES AND MODE	LS AIRCRAFT. REPLACEMENT PARTS ARE NOT READILY AVAILABLE. AIRCRAFT WAS AOG FOR THREE WEEKS.			1	L	7	1 	3O	3	O	NT	A57EU   	E274	5	N	P88614	 
2002072900005	20020729	00005	SW  	2002	7	29	2002FA0000854    	1	20020708	G	3251	35021505	VALVE           			SWRNGN	SA226 	SA226T      	8780122	SW  										STEERING UNIT	FAILED          	C			W6NR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	25	117CC					T325				OVERHAULED VALVE FAILED SHOP GROUND TEST.  VALVE (SN 493A), FAILED ON FIRST LANDING, CAUSING AN UNCONTROLABLE SHIMMY IN 	STEERING OF AIRCRAFT, VIOLANT SHAKING.					2	L	7	2 	4T			RT	A5SW    					 
2002072900006	20020729	00006	CE  	2002	7	29	2002FA0000855    	1	20020614	G	2760	6511711023	LINE            			CESSNA	500   	550         	2076604	CE  										SPEED BRAKE	CHAFED          	G			CNQ6	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	316CS	308  				5501010				FRESH AIR DUCT IN TAILCONE FOUND CHAFING AGAINST SPEED BRAKE CONTROL LINES.						1	L	7	2 	4F			 	A22CE   					 
2002072900007	20020729	00007	EA  	2002	7	29	2002FA0000857    	2	20020515	G	7414	M3827	GEAR            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					MAGNETO	CRACKED         	B			NX42	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	412ER	1286 				172S8643				MAGNETO ROTOR GEAR FOUND CRACKED ON INSPECTION.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002072900008	20020729	00008	CE  	2002	7	29	2002FA0000859    	1	20020713	G	3220	99101397	ACTUATOR        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					NLG	CONTAMINATED    	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	15	2664T					414A0623				UPON LANDING ROLLOUT NOSE GEAR COLLAPED.  INVESTIGATION INDICATED ACTUATOR CONTAMINATED BY WATER.  CHEVRON SEALS WORN, A	ND DOWN LOCK SWITCH DETERIORATED.  SUSPECT ACTUATOR FROZE IN FLIGHT FROM COLD TEMPERATURES.  ACTUATOR OVERHAULED.  NO FU	RTHER PROBLEM.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002072900010	20020729	00010	SO  	2002	7	29	2002FA0000861    	1	20020626	G	3210	AN6H14A401462	BOLT            			PIPER 	PA38  	PA38112     	7103812	SO  										RT MLG	FAILED          	B			KRTR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	09	2356A	619  				3878A0652				RT MLG DEPARTED AIRCRAFT DURING LANDING.  FORWARD CLAMP BOLT FAILED CAUSING LANDING GEAR TO ROTATE FROM ITS PROPER LOCAT	ION.  BOLT WAS FOUND WITH A SHEAR TYPE FAILURE.					1	L	7	1 	3O			 	A18SO   					 
2002072900011	20020729	00011	EU  	2002	7	29	2002FA0000862    	1	20020625	G	6320	32030004	OIL FILTER      			SNIAS 	350   	AS350B2     	8680813	EU  										M/R GEARBOX	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	455AE					3509				MAIN GEAR BOX OIL FILTER USED ON CERTAIN A/C HAVE A TAB TACK WELDED TO THE FILTER CASING SO SAFETY WIRE CAN BE ATTACHED.	  ON 5/30/02, 3 OF THESE FILTER HAD THE SAFETY WIRE TABS FALL OFF BEFORE THE FILTERS WERE INSTALLED.   MFG WAS NOTIFIED 	OF THIS PROBLEM.				1	G	7	1 	3U			 	H9EU    					 
2002072900012	20020729	00012	CE  	2002	7	29	2002FA0000863    	1	20020522	G	3220	95824019	BRACE           			BEECH 	58    	58          	1152740	CE  										NLG	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	05	6577S	5131 				TH712				NOSE RETRACT BRACE FAILED ALLOWING NOSE GEAR TO RETRACT UPON LANDING.						1	L	7	2 	3O			 	3A16    					 
2002072900013	20020729	00013	SW  	2002	7	29	2002FA0000864    	1	20020702	G	5310		STRUCTURE       			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	6363Q					670446				HEADLINER EACH LOCATION THE HEADLINER MATERIAL CAME INTO CONTACT WITH ALUMINUM ATTACH POINTS THE AREA CORRODED THE INTER	IOR WAS REPLACED IN THE SUBJECT AIRCRAFT ON MAY 1, 1998  THE CORROSION WAS DISCOVERED DURING MAINTENANCE MAY 17, 2002.					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2002072900014	20020729	00014	SO  	2002	7	29	2002FA0000865    	2	20020714	G	7414		SPRING          			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BB     	17032	SO  					IMPULSE COUPLIN	BROKEN          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	25	1859A	1958 				E1929	248569R			PILOT REPORTED SMOOTH 200 RPM DROP ON LT MAGNETO DURING RUN UP.  TROUBLESHOOTING FOUND LT MAGNETO TIMING 7 DEGREES RETAR	DED.  MAGNETO WAS REMOVED AND IMPULSE COUPLING FOUND TO HAVE A BROKEN SPRING.  COUPLING WAS REPLACED WITH A NEW UNIT.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002072900015	20020729	00015	SO  	2002	7	29	2002FA0000866    	1	20020702	G	3210	AN717A401511	BOLT            			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235*       	41505	EA  					MLG	DAMAGED         	B			KRTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2589B	6684 				3879A0135				MLG ATTACH BOLTS WERE REMOVED FOR INSPECTION DUE TO AN INCIDENT THAT OCCURED ON 6/17/02 WITH A SAME MODEL AIRCRAFT.  FOU	ND THE INBOARD GEAR ATTACH BOLTS FOR BOTH MAIN LANDING GEAR BENT IN THE SHANK AREA.  ONE BOLT HAD ITS SHANK DISPLACED AP	PROX. .012 OF AN INCH.  SECOND BOLT SHANK WAS DISPLACED APPPROX.  .008.				1	L	7	1 	3O	3	O	 	A18SO   	E223				 
2002072900016	20020729	00016	EA  	2002	7	29	2002FA0000868    	2	20020701	G	7320	70145401	SERVO           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL INJECTION	INOPERATIVE     	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	13	996RA					17280404	L2745951A			AFTER RECEIVING THE ENGINE BACK FROM MFG, YELLOW TAGGED, STICKERED IN THE LOG BOOK AIRWORTHY, REINSTALLED ENGINE.  GROUN	D RUN FOR LEAKS BUT WOULD NOT IDLE SMOOTH UNTIL IDLE/MIXTURE WAS SET AT 625 RPM.   OK`D TEST FLIGHT AND IT QUIT ON LANDI	NG.  THIS AIRCRAFT DID THIS ONCE BEFORE WITH SAME PILOT, MADE SOME ADJUSTMENTS AND SENT IT UP WITH ANOTHER PILOT TELLING	 HIM TO WATCH FOR RECURRING RICHENED OPERATION.  HE WAS ABLE TO COMPLETE TEST HOP SUCCESSFULLY WITH USE OF MIXTURE CONTR	OL.  AFTER CALLING MFG, REMOVED SERVO PER SI.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002072900017	20020729	00017	SO  	2002	7	29	2002FA0000869    	1	20020627	G	8120	46C19839F	BLADE           			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					TURBOCHARGER	FAILED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	07	96PP	870  				4636120	L985461A			PILOT REPORTED LOSS OF POWER AT FLIGHT OF 18,000 FT.  REGAINED POWER AT 9,000 FEET AND LANDED.  INSPECTED, FOUND EXHAUST	 SIDE OF TURBO BLADE BROKEN OFF AND TURBO WAS SEIZED.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2002072900018	20020729	00018	CE  	2002	7	29	2002FA0000870    	1	20020604	G	7160	C2945100501	AIR FILTER      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					INDUCTION SYS	MISINSTALLED    	B			H4SR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	35	5105U					172RG0239				INSPECTED AIRCRAFT FOLLOWING PURCHASE FOR FLIGHT SCHOOL.  DISCOVERED INDUCTION AIR FILTER INSTALLED BACKWARDS.  HOUSING 	IS EVEN LABELED FOR AIRFLOW WITH AN ARROW.  HOUSING WAS IN BACKWARDS ALSO.  WITH ARROW POINTING FORWARD AWAY FROM THE CA	RB TOWARDS THE INSIDE.				1	H	7	1 	3O	3	O	 	3A17    	E286				 
2002072900019	20020729	00019	SW  	2002	7	29	2002FA0000871    	1	20020614	G	6510	MS21042L4	NUT             			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					T/R DRIVESHAFT	UNSECURE        	B			VE3R	O				OTHER                   				E	W		VIBRATION/BUFFET          	INADEQUATE Q C            		NR	NOT REPORTED   	1			WP	23	83WP	4431 				51359				PILOT COMPLAINED OF MEDIUM FREQUENCY VIBRATION.  VIBRATION WAS ISOLATED TO THE TAIL ROTOR DRIVE SHAFT 5TH SEGMENT.  THE 	MS21042L4 NUT THAT SECURES THE HANGER BEARING ON THE SHAFT HAD LOST TORQUE.  THIS ALLOWED THE BEARING INNER RACE TO SPIN	 ON THE SHAFT, RUINING THE SHAFT.  THE NUT HAD 5 INCH LBS. OF TORQUE.  THERE HAD BEEN NO PREVIOUS MAINTENANCE IN THIS AR	EA EXCEPT INSPECTIONS.  THE SHAFT, ADAPTER, AND THE HANGER BEARING HAD TO BE REPLACED.			1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002072900020	20020729	00020	SO  	2002	7	29	2002FA0000872    	1	20020701	G	3210		BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O541  	TIO541*     	41536	EA  					PARK GEAR	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	4237D	9270 				317305055				(PARK GEAR EXTENSION RETRACT) ACTUATOR BROKE .2500 BOLT THAT HOLDS FORK THAT RELEASES GEAR UNLOCK GEAR WOULD NOT RETRACT	.					1	L	7	2 	3O	3	O	 	A20SO   	E10EA				 
2002072900003	20020729	00003	SO  	2002	7	29	2002FA0000873    	1	20020726	G	5711		SPAR            			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  					WING	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	31	8536N					2811335				DURING ANNUAL INSPECTION SB1006 PERFORMED. FOUND CRACKS AND CORROSION IN AFT REAR SPAR FLANGE-APPROX 3 INCHES OUTBOARD O	F LANDING GEAR ATTACH. CAUSE DUE TO STANDING WATER IN WING. FIX BY ADDING DRAIN HOLE IN THIS AREA.					1	L	7	1 	3O	3	O	 	2A13    	E295				 
2002073000008	20020730	00008	GL  	2002	7	30	2002FA0000874    	3	20020701	G	6114	745255	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CRACKED         	B			S6PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	333BS		133  			310R0865		745255		PROPELLER SENT TO OUR REPAIR STATION FOR RED DYE LEAK CHECK.  PROPELLER WAS DISASSEMBLED AND INSPECTED NR 1 AND NR 3 BLA	DE FERRULE WERE DRILLED TOO DEEP.  NR 2 BLADE SOCKET WAS FILLED WITH RTV.  NR 2 BLADE BEARING AND BALLS AND FERRULE WERE	 CONDEMNED FOR RUST FROM RTV.  PROPELLER HUB WAS CRACKED.  UN-AIRWORTHY PARTS RETURNED TO CUSTOMER.				1	L	7	2 	3O			 	3A10    		5	C	P22EA	 
2002073000009	20020730	00009	GL  	2002	7	30	2002FA0000875    	3	20020509	G	6114	777290	HUB             			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	PROPELLER	CORRODED        	B			S6PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	756JX		187  			U20604138		777290		PROPELLER CAME IN REPAIR STATION BECAUSE IT WOULD NOT CHANGE PITCH.  THE PROPELLER WAS DISASSEMBLED.  PROPELLER WAS FULL	 OF RUST, ALL STEEL PARTS WERE CONDEMNED.  PROPELLER BLADES AND HUB WERE CONDEMNED FOR EXTENSIVE CORROSION.  THE PROPELL	ER WAS FOUND TO BE UNAIRWORTHY AND RETURNED TO CUSTOMER.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002073000010	20020730	00010	GL  	2002	7	30	2002FA0000876    	3	20020702	G	6114	D5347	HUB             			CESSNA	206   	P206C       	2073312	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	PROPELLER	CRACKED         	B			S6PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	8630Z		1520 			P2060430		737174		PROPELLER CAME IN OUR REPAIR STATION FOR RED DYE LEAK.  PROPELLER WAS DISASSEMBLED AND INSPECTED.  PROPELLER HUB WAS FOU	ND TO BE CRACKED IN THE NR 2 BLADE SOCKET.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA9	 
2002073000011	20020730	00011	WP  	2002	7	30	2002FA0000877    	2	20020715	G	7230	30740962	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					COMPRESSOR	OUT OF TOLERANCE	B			UO2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19										NEW COMPRESSOR WHEEL RECEIVED FROM HONEYWELL WITH DAMAGE GREATER THAN .001 INCHES BY FIR TREE AREA.											4	F			E6WE				 
2002073000012	20020730	00012	WP  	2002	7	30	2002FA0000878    	2	20020715	G	7250	30723973	TURBINE WHEEL   								GARRTT	TFE731	TFE731*     	01518	WP  					3RD LPC DISK	GOUGED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW TURBINE DISK RECEIVED FROM HONEYWELL WITH SCRATCHES/GOUGES ON FORWARD WEB BY CURVIC TEETH.											4	F			E6WE				 
2002073000121	20020730	00121	NE  	2002	7	30	2002FA0000881    	2	20020427	G	7320	32448094	FUEL CONTROL    			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					THRUST BEARING	FAILED          	B			IG0R	O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	03										PILOT REPORTED LOSS OF ENGINE CONTROL.  INVESTIGATION REVEALED A THRUST BEARING (PN 2523973) FAILURE INSIDE THE FUEL CON	TROL.					1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
2002081200130	20020812	00130	EA  	2002	8	12	2002FA0000882    	2	20020422	G	8530		PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	6376M	493  				15284698	L1508115			THIS ENGINE SENT BACK TO THE FACTORY FOR METAL CONTAMINATION AND REWORKED THERE.  ALL NEW CYLINDERS INSTALLED.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081200131	20020812	00131	CE  	2002	8	12	2002FA0000883    	1	20020702	G	3246	1540320	SEAL            			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					NLG BEARING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	3243B	1049 				E3243				RT NOSE WHEEL BEARING, CORRODED.  BEARING SEAL NOT INSTALLED ON BEARING SECURELY.  THE SEAL RESTS AGAINST THE BEARING.  	WATER EASILY GETS INTO BEARING.  BEARING CORRODES AND SPINS ON AXLE.  HAD TO REPLACE AXLE.  REPAIR STATION SAID THE MANU	FACTURED THE SEAL TO MFG. INSTRUCTIONS AND IF THERE IS A PROBLEM IT IS A MFG PROBLEM.				1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2002081200132	20020812	00132	CE  	2002	8	12	2002FA0000884    	1	20020723	G	5312	04120081	BULKHEAD        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200*       	17020	SO  					TAILCONE	CRACKED         	D			ET9T	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	88808	2730 				15076150				CRACKS THROUGH BULKHEAD.  TIE DOWN PROBLEMS/ LANDINGS TAIL LOW. REPETITIVE TAIL LOW LANDINGS.						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002081200133	20020812	00133	SO  	2002	8	12	2002FA0000887    	2	20020701	G	8530	TSIO520VB	CYLINDER        			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1233T					402C0805				CRACK BETWEEN SPARK PLUG HOLE AND INJECTOR HOLE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002081300001	20020813	00001	SO  	2002	8	13	2002FA0000889    	2	20020528	G	7414		IMPULSE COUPLING	SLICK       	6310        	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					MAGNETO	FAILED          	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	27	1080M	1749 			97012222	18266034	249972R			LEFT MAGNETO IMPULSE COUPLING FAILED IN FLIGHT.  COUPLING PAWS BROKEN FROM BODY AND CAUSED MAGNETO CASE TO BREAK AT MOUN	T PAD.  MAGNETO MADE METAL INTO ENGINE BEFORE FAILING.  WHEN AIRCRAFT PICKED UP AT HANGAR, NO OIL REGISTERED ON DIP STIC	K.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002081300002	20020813	00002	SO  	2002	8	13	2002FA0000890    	1	20020715	G	2140	A23D04475	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					HEATER FUEL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	350PC	42   				318152006				FOUND AIRCRAFT HEATER FUEL PRESSURE REGULATOR LEAKING WHILE SERVICING AIRCRAFT HEATER.  THIS UNIT INSTALLED NEW, MAY 200	2, WITH 42 HOURS OF HEATER OPERATION.  THIS UNIT ALSO HAD AD AND SB, COMPLIED WITH AT UNIT INSTALL (NEW TYPE FUEL PRESSU	RE REGULATOR).				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002081300003	20020813	00003	CE  	2002	8	13	2002FA0000891    	1	20020723	G	3250	AN3H	BOLT            			CESSNA	206   	TU206F      	2073353	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG STEERING	SHEARED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AL	01	8763Q					U20603516				ON LANDING, AIRCRAFT EXITED RUNWAY BECAUSE NOSE GEAR STEERING WAS LOST.  NO DAMAGE OR INJURIES.  MECHANIC FOUND STEERING	 COLLAR ATTACHING FORWARD BOLT SHEARED.  STRUT APPEARED TO BE OVER INFLATED CAUSING BOLT TO SHEAR WHEN TOWED IN THIS CON	DITION.  SERVICED STRUT AND REPLACED BOLT.  CHECKED OK.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2002081300004	20020813	00004		2002	8	13	2002FA0000894    	4	20020620	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										PROP SPINNER	CRACKED         	B			FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	792SP	35   				172S8717				DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED THAT THE SPINNER BULKHEAD WAS CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2002081300005	20020813	00005	NE  	2002	8	13	2002FA0000895    	2	20020724	G	7323	1528232	SPRING          	WOODWARD    							LYC   	LTS101	LTS101600A3 	41560	NE  					O/S GOVERNOR	BROKEN          	B			OL3R	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	27					2122350					ENGINE WILL NOT ACCELERATE ABOVE 90 PERCENT NP.  FOUND SPEEDER SPRING BROKEN IN HALF.											3	U			E5NE				 
2002081300006	20020813	00006	CE  	2002	8	13	2002FA0000897    	1	20020712	G	5751	512400097	ANGLE           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					AILERON	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4652N					402C0011				COULD NOT MOVE AILERONS.  90 PERCENT ANGLE, USED TO PREVENT OIL CANNING, BONDED INSIDE AILERON, BROKE LOOSE AND WORKED I	TS WAY DOWN TRAILING EDGE OF AILERON AND INTO FLAP TRAILING EDGE, PREVENTING AILERONS FROM MOVING.  90 PERCENT ANGLE IS 	8 INCHES LONG AND .3750 WIDE, .016 THICK.  AILERON WAS REPLACED.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002081300007	20020813	00007	EA  	2002	8	13	2002FA0000898    	2	20020722	G	7532	MS924530	COTTER PIN      								PWA   	PT6   	PT6A27      	52043	EA  					BLEED VALVE	BROKEN          	B			UE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01										DURING TEARDOWN OF COMPONENT TO CLEAN FOR AN OVERHAUL INSPECTION, BROKEN PIECES OF COTTER PIN WERE FOUND.  THE PISTON GU	IDE PIN WAS LOOSE INSIDE.  THE GUIDE PIN IS HELD IN THE COVER BY A PRESSFIT AND THE COTTER PIN, NORMALLY.  THE COVER, GU	IDE PIN AND COTTER PIN WILL BE SCRAPPED.  A SERVICEABLE COVER WILL BE USED TO REPLACE THE SCRAPPED PARTS.									4	T			E4EA				 
2002081300008	20020813	00008	CE  	2002	8	13	2002FA0000899    	1	20020723	G	5741	MS1782612	NUT             			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					WING ATTACH	CRACKED         	B			QF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	208TW	1022 				208B0671				FOUND RIGHT LOWER WING STRUT ATTACH HARDWARE LIGHTLY CORRODED.  FURTHER INSPECTION FOUND THAT NUT WAS COMPLETELY CRACKED	 THROUGH.  NEW NUT AND BOLT INSTALLED.  PART MAY HAVE BEEN OVERTORQUED UPON INSTALLATION.					1	H	7	1 	3T	3	T	 	A37CE   	E2NE				 
2002081300009	20020813	00009	CE  	2002	8	13	2002FA0000900    	1	20020708	G	5610	10138402517	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	FAILED          	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			NE	01	525SK					BB1148				IN CRUISE RIGHT WINDSHIELD SHATTERED FOLLOWED BY EMERGENCY DESCENT.  UPON AFTER LANDING INSPECTION LEFT W/S OBSERVED TO 	HAVE A 2 X 4.7500 INCH PEEL CHIP FAILURE, UPPER LEFT CORNER.  CAUSE OF PEEL CHIP FAILURE OF INNER GLASS LAMINATION WAS A	N INTERNAL STRESS BUILT INTO THE WINDSHIELD AT MANUFACTURE PER TRIDENT ENGINEERING ASSOC.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002081300010	20020813	00010	CE  	2002	8	13	2002FA0000901    	1	20020708	G	5610	10138402522	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	FAILED          	G				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NE	01	525SK					BB1148				IN CRUISE AT WINDSHIELD SHATTERED, WINDSHIELD REMOVED AND SUBMITTED FOR EXAMINATION ( PEEL CHIP OR SPALLING FAILURES OF 	THE INNER LAMINATION OF BOTH WINDSHIELDS WAS AN INTERNAL STRESS BUILT INTO THE WINDSHIELDS AT MANUFACTURE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002081300011	20020813	00011	WP  	2002	8	13	2002FA0000906    	1	20020227	G	5246		LOCK            			LKHEED	18    	1856        	5261642	WP  										ACCESS PANEL	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	669					2044				FORWARD EXT. ACCESS PANEL LOCK ASSEMBLY CHAFES DOOR LATCH WHEN PANEL IS IN THE OPEN POSITION.  REMOVED MATERIAL FROM ARM	 OF LOCK ASSY TO PROVIDE CLEARANCE, OPS CHECK COMPLETED NO CHAFING NOTED PER B/P 1159B50000.  COMPLIED WITH ENGINEERS DI	SPOSITION PER SR  PH TEST COMPLIED WITH 7.0				2	L	7	2 	4R			RT	A723    					 
2002081300012	20020813	00012	WP  	2002	8	13	2002FA0000907    	1	20020227	G	5620	1159CE5000155	WINDOW          			LKHEED	18    	1856        	5261642	WP  	WRIGHT	R1820 	GR1820G2    	67020	EA  					CABIN	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	669					2044				NR 3 RIGHT CABIN WINDOW INNER PANE IS CRACKED.  REMOVED AND REPLACED CABIN WINDOW.  LEAK CHECK GOOD.						2	L	7	2 	4R	4	R	RT	A723    	TC157				 
2002081300013	20020813	00013	WP  	2002	8	13	2002FA0000908    	1	20020227	G	5230		CABLE           			LKHEED	18    	1856        	5261642	WP  	WRIGHT	R1820 	GR1820G2    	67020	EA  					CARGO DOOR	MISROUTED       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	669					2044				BAGGAGE DOOR MAKES A VIBRATION NOISE WHEN DOOR IS OPENED APPROX .5000 TO .7500 OPEN POSITION.  DOOR APPEARS TO BE CHAFIN	G JUST BEFORE CLOSING.    FOUND AFT CABLE NOT ROUTED PROPERLY GOING TO BAGGAGE DOOR, ROUTED CABLE OPS CHECK COMPLIED WIT	H, CHECKED OK.				2	L	7	2 	4R	4	R	RT	A723    	TC157				 
2002090600198	20020906	00198	GL  	2002	9	6	2002FA0000910    	1	20020313	G	1430	1159WM5153511	SCREW           			AMTR  	WOODHS	PSE1        	       	GL  										LT WING	INCORRECT       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	670									LEFT WING (D) TRACK ABOVE INBOARD EDGE 4 SCREWS TOO SHORT IN COVE PANEL.  SHORT SCREWS AND INSTALLED CORRECT SCREWS PER 	B/P.					1	M	0	0 	  				EXPA1M00					 
2002081300014	20020813	00014	SO  	2002	8	13	2002FA0000911    	1	20020717	G	7810	LW1277885	WASTEGATE VALVE 			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					LT ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	40454	91   				277305167	L482761A			LT ENGINE  EXHAUST BACK PRESSURE SEPARATED (PN LW 11657) WASTE GATE MALE FROM (PN LW 11656) FEMALE.  (PN LW 1165) U BOLT	 WAS NOT LOOSE.					1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2002081300015	20020813	00015	EA  	2002	8	13	2002FA0000912    	2	20020719	G	8530		RETAINER        			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					NR 5 CYLINDER	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	300WF	641  				18280015	L2594348A			NR 3 CYLINDER PUSH ROD BENT, REMOVED THE NR 5 CYLINDER VALVE COVER FOR FURTHER INSPECTION AND FOUND PUSH ROD RETAINING C	LIP MISSING AND ASSOCIATED HARDWARE.  NO DAMAGE OR PARTS FOUND					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2002081300016	20020813	00016	CE  	2002	8	13	2002FA0000915    	1	20020613	G	2150	73838426	ACM             			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ACM BAY	DAMAGED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	4	4517 				5600113				PILOT REPORTED INSUFFICIENT COOLING TO THE CABIN.  UPON VISUAL INSPECTION OF THE AIR CYCLE MACHINE (ACM) IT WAS NOTICED 	THAT ONE OF THE THREE FAN BLADES WAS BROKEN OFF THE HUB.  AFTER REMOVAL OF THE ACM IT WAS FURTHER DISCOVERED THAT THE SH	AFT HAD SHEARED INTERNALLY AND THE COMPRESSOR BLADES WERE DAMAGED.				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2002081300017	20020813	00017	EA  	2002	8	13	2002FA0000916    	2	20020723	G	7322	HA6105235	CARBURETOR      			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	6183T		772  			R18201930	L2111440A			PILOT BROUGHT IN AIRCRAFT WITH ROUGH RUNNING ENGINE.  ENGINE WOULD SURGE BELOW 900 RPM AND MIXTURE CONTROL WOULD NOT SHU	T DOWN ENGINE.  FOUND FUEL DRIPPING FROM CARBURETOR THROAT.  THE CARBURETOR WAS REPLACED AND OPERATION RETURNED TO NORMA	L.				1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2002081300018	20020813	00018	CE  	2002	8	13	2002FA0000919    	1	20020614	G	3260		DOWNLOCK SWITCH 			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NLG	FAILED          	B				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			WP	03	400HS	594  				RK314				NOSE LANDING GEAR DOWNLOCK LIGHT DID NOT COME ON AFTER DEPLOYMENT OF LANDING GEAR.  GEAR CYCLED SEVERAL TIMES AND STILL 	NO DOWN AND LOCK LIGHT ILLUMINATION.  TOWER FLY BY PERFORMED AND CONFIRMED DEPLOYMENT.  AIRCRAFT LANDED SAFELY.  NEW SWI	TCH INSTALLED.				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2002081300019	20020813	00019	CE  	2002	8	13	2002FA0000920    	1	20020719	G	2110	585550111	BRACKET         			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					A/C COMPRESSOR	CRACKED         	B			AWKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	658DG	94   				TH2017	685248			DURING 100 HOUR INSPECTION FO THE LT ENGINE, THE UPPER ARM OF THE AIR CONDITION COMPRESSOR BRACKET WAS FOUND TO BE CRACK	ED.  IT APPEARS AS IF IT WAS NOT SHIMMED CORRECTLY.  DURING INITIAL INSTALATION WHICH PRELOADED THE ARM AND CRACKED.  C/	A: PROPERLY SHIM BRACKET TO PREVENT PRELOAD.				1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2002081300020	20020813	00020	SO  	2002	8	13	2002FA0000921    	1	20020723	G	5511	6697500	SPAR            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	16319	13800				287305224				HORIZONTAL STAB REAR SPAR CRACKED HALF WAY ACROSS. 5 INCHES ABOVE FUSELAGE.  NO SIGN OF BEING HIT OR EXTERIOR DAMAGE.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002081300030	20020813	00030	CE  	2002	8	13	2002FA0000925    	1	20020703	G	3060	3E20901	BRUSH BLOCK     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					PROPELLER	INOPERATIVE     	B			PIYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	87SA	5    				BB1089	PCE93030			AFTER PROPELLER OVERHAUL AND PROPELLER DE-ICE BRUSH REPLACEMENT,  PILOT REPORTED DEICE SYSTEM CIRCUIT/BREAKER SWITCH TRI	PPED IN FLIGHT.  COULD NOT DUPLICATE PROBLEM ON GROUND WITH ENGINES RUNNING.  INSPECTED SYSTEM AND FOUND IF SIDE PRESSUR	E WS APPLIED TO RIGHT BRUSH BLOCK STACK, THE WASHERS ON THE WIRING ATTACH SCREWS WOULD SHORT TOGETHER TRIPPING THE SWITC	H.  A NYLON SPACER IS USED TO RAISE ONE OF THE TERMINALS TO PREVENT THIS FROM HAPPENING, BUT THE DIFFERENCE IN HEIGHT WA	S NOT SUFFICIENT IN THIS CASE.  A SLIGHTLY TALLER NYLON SPACER WAS USED TO INCREASE CLEARANCE.  THE AIRCRAFT WAS FLOWN A	ND PROPELLER DEICE SYSTEM OPERATION WAS NORMAL.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002081300043	20020813	00043	EA  	2002	8	13	2002FA0000927    	2	20020422	G	8530		PISTON PIN      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	6376M	400  				15284698	L1508115			CYLINDER 1 AND 3 DAMAGED DUE TO PISTON PIN WEAR.   ALUMINUM IF FILTER TOTAL TIME ON CYLINDERS WAS 400 HR.  TSMOH FOR ENG	INE 1095.3, OCCURED 9/26/01 INSTALLED CHROME CYLINDERS.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300045	20020813	00045	EA  	2002	8	13	2002FA0000928    	1	20020510	G	2910	6047523879	LINE            			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF34*       	 	NE  					NR 2 HYD SYS	CHAFED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	788SC					5391				LOST ALL NR 2 HYDRAULIC FLUID AT CRUISE FL 37 AFTER 3 HOURS IN FLIGHT.  LEAK TRACED TO NR 2 EDB CASE DRAIN RETURNED LINE	 TUBE ASSEMBLY.  REPLACED LINE, BLED AND LEAK CHECKED, NO LEAKS NOTED.  AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002081300046	20020813	00046	EA  	2002	8	13	2002FA0000929    	2	20020422	G	8530		PISTON PIN      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5416M	381  				15284584	L1675415			REMOVED NR 1 CLYINDER DUE TO POSTON PIN CAP WEAR INSTALLED CHROME CYLINDER ASSEMBLY OCCURED 02/15/2002.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300048	20020813	00048	EA  	2002	8	13	2002FA0000930    	2	20020422	G	8530		PISTON PIN      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5416M					15284584	L1675415			REMOVED NR 1 CYLINDER.  INSTALLED ANEW PISTON PIN CAPS/ WEAR WAS NOT NORMAL.  THIS ENGINE FACTORY OVERHAUL 9/24.  OCCURE	D 11/3/98					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300050	20020813	00050	EA  	2002	8	13	2002FA0000931    	2	20020422	G	8530		PISTON PIN      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5416M	1470 				15284584	L1675415			FACTORY OVERHAUL 24-9.  INSTALLED ALL NEW FACTORY NEW CYLINDERS DUE TO METAL CONTAMINATION FROM PISTON PIN CAPS.  OCCURR	ED 05/07/2001					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300051	20020813	00051	EA  	2002	8	13	2002FA0000932    	2	20020422	G	8530		CAP             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5403H	1800 				15284096	L1672515			FACTORY OVERHAUL 02/28/96.  OCCURRED 12/26/00.  REMOVED NR 1 CYLINDER METAL IN FILTER,  CAPS WORN.  INSTALLED NEW FACTOR	Y CYLINDER.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300052	20020813	00052	EA  	2002	8	13	2002FA0000933    	2	20020422	G	8530		CAP             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					PISTON PIN	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5403H	1700 				15284096	L1672515			FACTORY OVERHAUL ENGINE 02/28/96.  RIGHT NR 2, 3 CYLINDERS HAD SOME WEAR IN PINS, NOT BAD.  HAND INSTALLED NEW CAPS AND 	RINGS.  OCCURED 10/05/00					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300054	20020813	00054	EA  	2002	8	13	2002FA0000934    	2	20020401	G	8530		CAP             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					PISTON PIN	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5403H	680  				15284096	L1672515			FACTORY OVERHAUL 02/28/96.  RIGHT NR 2 CYLINDER DUE TO PISTON PIN WEAR.  INSTALLED CHROME CYLINDER. 04/01/02						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300056	20020813	00056	EA  	2002	8	13	2002FA0000935    	2	20020422	G	8530		CAP             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					PISTON PIN	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5403H	500  				15284096	L1672515			REMOVED NR 1 CYLINDER DUE TO PISTON PIN CAP WEAR, INSTALLED CHROME CYLINDER.  FACTORY OVERHAUL 02/28/90						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300058	20020813	00058	EA  	2002	8	13	2002FA0000936    	2	20020422	G	8530		PISTON PIN      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	94662	2000 				15285757				FACTORY OVERHAUL 12/96.  REMOVED ENGINE FOR ALUMINUM CONTAMINATION.  NR 1 PISTON PIN WEAR, NR 3 PISTON PIN WEAR.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300059	20020813	00059	EA  	2002	8	13	2002FA0000937    	2	20020422	G	8530		PISTON PIN      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	94662	1550 				15285757	1174615			FACTORY OVERHAUL 12/96.  REMOVED AND REPLACED NR 4 CYLINDER DUE TO PISTON PIN WEAR/ CYLINDER RIDGE.  DATE OF OCCURANCE 0	1/00.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300061	20020813	00061	EA  	2002	8	13	2002FA0000938    	2	20020412	G	8530		CAP             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					PISTON PIN	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	94662	1000 				15285757	1174615			FOUND ALUMINUM IN FILTER REMOVED AND REPLACED NR 2 CYLINDER DUE TO PISTON PIN WEAR FROM RIDGE IN CYLINDER.  DATE OF OCCU	RANCE 11/98					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300062	20020813	00062	EA  	2002	8	13	2002FA0000939    	2	20020412	G	8530		CAP             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					PISTON PIN	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	94662	700  				15285757	1174615			THIS ENGINE FACTORY OVERHAUL 12/96.  ALUMINUM IN FILTER, NR 1 CYLINDER WEARS A RIDGE FROM RING IN FORWARD SIDE THEN THE 	RIDGE WEARS PISTON PIN.  DATE OF OCCURANCE 03/98					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300063	20020813	00063	EA  	2002	8	13	2002FA0000940    	2	20020422	G	8530		PISTON PIN      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					NR 1 CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	94662	299  				15285757	L2486615			FACTORY ENGINE OVERHAUL O1/01.  ALUMINUM IN FILTER DUE TO NR 1 PISTON PIN WEAR.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002081300064	20020813	00064	SO  	2002	8	13	2002FA0000943    	1	20020322	G	2497	CM358950	SWITCH          			BALWKS	FIREFY	FIREFLY7    	1050100	SO  										AVIONICS MASTER	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	02	4066A					10016				(AVIONICS BUS SWITCH)  INDICATIONS SHOW A SWITCH MANUFACTURING OR LOAD PROBLEM AND SHOULD BE INVESTIGATED.						1	B	0	0 	  			 	A14SO   					 
2002081300065	20020813	00065	CE  	2002	8	13	2002FA0000951    	1	20020311	G	2497	CM358950	SWITCH          			CESSNA	402   	402C        	207590R	CE  										AVIONICS BUS	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	02	812AN					402C0229				(AVIONICS BUS SWITCH) INDICATIONS SHOW A SWITCH MANUFACTURING OR LOAD PROBLEM AND SHOULD BE INVESTIGATED.						1	L	7	2 	3O			 	A7CE    					 
2002081300066	20020813	00066	EA  	2002	8	13	2002FA0000952    	2	20020619	G	8530		CYLINDER        								LYC   	O540  	TIO540J2BD  	41532	EA  					NR 3	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08							L669361A			(NR 3 CYLINDER) NR 3 CYLINDER CAME LOOSE FROM CASEHALF.  ROD STILL CONNECTED TO CRANKSHAFT.											3	O			E14EA				 
2002081300067	20020813	00067	SO  	2002	8	13	2002FA0000953    	2	20020724	G	8530	631996	RETAINER        			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					ROCKER SHAFT	CRACKED         	C			BUWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9712C	178  				347870211	306405			DURING AN ANNUAL INSPECTION, ONE ROCKER BOX COVER ON THE LEFT ENGINE WAS REMOVED IN THE PROCESS OF REPLACING PUSHROD TUB	E SEALS.  DISCOVERED ONE ROCKER SHAFT RETAINER CRACKED INTO TWO PIECES.  DECIDED TO INSPECT REMAINDER OF CYLINDERS AND F	OUND 19 OF 24 ROCKER SHAFT RETAINERS EITHER COMPLETELY CRACKED IN HALF OR ALMOST CRACKED IN HALF.  ELECTED TO REPLACE AS	S RETAINERS AT THIS TIME.  THIS IS AN AREA THAT IS NOT NORMALLY ACCESSED DURING A NORMAL ANNUAL.  SUSPECT THAT THE CAUSE	 MAY HAVE BEEN OVER-TORQUE ON THE NUTS HOLDING THE RETAINERS.		1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002081300068	20020813	00068		2002	8	13	2002FA0000954    	4	20020625	G	3160	7011674119	SYMBOL GENERATOR			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					NR 1	FAILED          	C				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			GL	07	29B	667  				258518				AFTER TAKEOFF, CAPTAINS EADI AND EHSI WENT BLANK.  TROUBLESHOOTING REVEALED NR 1 SYMBOL GENERATOR HAD FAILED.  UNIT (SN9	8071444) WAS INSTALLED.UNIT FAILED ON INSTALL.  UNIT (SN 99081612) WAS INSTALLED.  THIS UNIT FAILED AFTER 30 MIN OF OPER	ATION.  UNIT (SN 91110731 WAS INSTALLED.  THIS UNIT FAILED AFTER 1.5 HOURS OF OPERATION.  ORIGINAL UNIT (SN 00111758) WA	S INSTALLED AFTER REPAIR BY THE MANUFACTURER.  THIS UNIT CONTINUES IN SERVICE.  IT IS TO BE NOTED THAT ALL FAILURES HAD 	DIFFERENT SYMPTOMS.  ALL UNITS WERE REPAIRED BY THE MANUFACTURER.  THEIR SERVICE REPORTS INDICATED THAT NO DEFECTS WERE 	NOTED DURING BENCH TESTS AND WERE RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002081300069	20020813	00069	GL  	2002	8	13	2002FA0000955    	1	20020724	G	5750	35128001	STOP            			AVIAT 	A1    	A1A         	2210405	GL  	LYC   	O360  	O360C1G     	41514	EA  					TE FLAPS	CRACKED         	B			EZ6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	96186	4048 				1186	L3056236A			DURING FLAP HANDLE REPLACEMENT,   THE FLAP SETTING STOP ASSY WAS REMOVED AND A CRACK WAS FOUND IN THE FULL FLAP NOTCH AN	D FAILURE OF THE ASSY WAS FORTHCOMING.  THIS SAME STOP ASSY HAD BEEN REMOVED 128.7 HOURS EARLIER FOR FLAP SYSTEM INSPECT	ION AND NO CRACK WAS PRESENT AT THAT TIME.  THIS WOULD BE THE SECOND FLAP STOP ASSY FAILURE DUE TO CRACKING FOUND BY THI	S SHOP.			1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2002081300070	20020813	00070		2002	8	13	2002FA0000956    	4	20020627	G	2562		BATTERY         			BEECH 	76    	76          	1153005	CE  										ELT	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	6701R					ME281				UNDER ANNUAL INSPECTION DURING BATTERY OPS CHECK, NO READING.  FURTHER INSPECTION OF BATTERY PACK REVEALED WATER INSIDE 	BATTERY AND ELT COMPARTMENTS.  THERE WAS NO EVIDENCE OF WATER IN ELT ATTACHING TRAY.					1	L	7	2 	3O			 	A29CE   					 
2002081300071	20020813	00071	CE  	2002	8	13	2002FA0000958    	1	20020318	G	2140	CA14071	IGNITER         			CESSNA	402   	402B        	207590P	CE  										HEATER	OVERHEATED      	D				H				DEACTIVATE SYST/CIRCUITS				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			NM	01	402CA					402B0842				NITE IMC HAD SUDDEN ELECTRIAL SMELL AND SMOKE IN COCKPIT.  PILOT SHUT DOWN TOTAL ELECTRICAL SYSTEM SMELL AND SMOKE CLEAR	ED.  WHILE TROUBLESHOOTING FOUND INGNITION UNIT ON HEATER HAD OVERHEATED AND STARTED TO MELT DOWN CHANGED UNIT SYSTEM OP	S CHECKED GOOD.				1	L	7	2 	3O			 	A7CE    					 
2002081200122	20020812	00122	EA  	2002	8	12	2002FA0000959    	1	20020728	G	2823		SELECTOR VALVE  			PERTH 	BIRD  	BIRDCK      	6840132	EA  										COCKPIT	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			EA	21	99754					4006	4545			DURING TAKE OFF, THE ENGINE SUDDENLY STOPPED RUNNING AT ALTITUDE OF 200 TO 300 FEET.  ATTEMPTED TURN AROUND AND LAND WIT	HOUT SUCCESS.  PILOT STATED THAT FUEL SELECTOR WAS IN THE ON POSITION.  DURING A POST ACCIDENT ENGINE TEST RUN, IT APPEA	RED THAT THE FUEL SELECTOR VALVE WHEN SELECTED TO THE "ON" POSITION,  DOES NOT ALLOW FULL FLOW THROUGH THE VALVE.  WHEN 	THE FUEL SELECTOR VALVE WAS SELECTED 3/8 INCH PAST THE "ON" POSITION, THE VALVE APPARENTLY FLOWS ENOUGH FUEL TO MAINTAIN	 FULL ENGINE RPM.  THE FUEL SELECTOR VALVE IS NOT A DETENT TYPE VALVE.  IT IS NOT MARKED AS TO THE MANUFACTURER OR WITH 	A PART NUMBER.  THIS AIRCRAFT IS AN ANTIQUE BIPLANE WHICH WAS BUILT IN 1931.	1	Q	7	1 	3R			 	ATC388  					 
2002081200123	20020812	00123	CE  	2002	8	12	2002FA0000962    	1	20020731	G	3040	57033	MOTOR           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BLOWER	FAILED          	G				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			EA	03	80AW	2991 				5500186				ON DECENT, THE COPILOT DETECTED AN ODOR THAT APPEARED TO BE ELECTRICAL IN ORIGIN.  THE CHECKLIST WAS EXECUTED AND THE OD	OR WAS ELIMINATED.  MAINTENANCE FOUND AND REPLACED THE INOP BLOWER FAN AND RETURNED THE AIRCRAFT BACK TO SERVICE.  TBO F	OR THIS PART IS  3500 HRS. AND THE PART REMOVED HAD 2991 HRS.  THE CIRCUIT BREAKER FOR THIS CIRCUIT DID NOT TRIP IN OTHE	R REPORTS HAD SIMILIAR RESULTS.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002081200124	20020812	00124	SO  	2002	8	12	2002FA0000964    	1	20020809	G	2900	AN833	FITTING         			GULSTM	G1159 	G1159B      	3953535	SO  										HYD SYSTEM	SCORED          	B				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	01	344GW	7953 	7953 			344				COMBINED HYDRAULIC SYSTEM INDICATED LOW QUANITY PRESSURE 330PSI TEE FITTING SCORED ON HYD LINE.						2	L	7	2 	4F			RT	A12EA   					 
2002081600001	20020816	00001	CE  	2002	8	16	2002FA0000965    	1	20020729	G	2130	E45C47	SWITCH          			LEAR  	35    	36A         	5170603	CE  										CABIN PRESSURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11										ANEROID SWITCH FAIL SPECIFIC PRESSURE LIMITS.						2	L	7	2 	4F			 	A10CE   					 
2002081600002	20020816	00002	CE  	2002	8	16	2002FA0000966    	1	20020729	G	2130	E45C47	SWITCH          			LEAR  	35    	36A         	5170603	CE  										CABIN PRESSURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11										ANEROID SWITCH FAILED SPECIFIC PRESSURE LIMITS.						2	L	7	2 	4F			 	A10CE   					 
2002081600003	20020816	00003	CE  	2002	8	16	2002FA0000967    	1	20020729	G	2130	E45C47	SWITCH          			LEAR  	35    	36A         	5170603	CE  										CABIN PRESSURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11										ANEROID SWITCH FAILED SPECIFIC PRESSURE LIMITS.						2	L	7	2 	4F			 	A10CE   					 
2002081600004	20020816	00004	CE  	2002	8	16	2002FA0000968    	1	20020729	G	2130	E45C47	SWITCH          			LEAR  	35    	36A         	5170603	CE  										CABIN PRESSURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11										ANEROID SWITCH FAILED SPECIFIC PRESSURE LIMITS.						2	L	7	2 	4F			 	A10CE   					 
2002081600005	20020816	00005	CE  	2002	8	16	2002FA0000969    	1	20020729	G	2130	E45C47	SWITCH          			LEAR  	35    	36A         	5170603	CE  										CABIN PRESSURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11										ANEROID SWITCH FAILED SPECIFIC PRESSURE LIMITS.						2	L	7	2 	4F			 	A10CE   					 
2002081600006	20020816	00006	SO  	2002	8	16	2002FA0000970    	2	20020729	G	8570	6533608R	PUMP            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COOLING WATER	FAILED          	D			TVMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	500AA					414A0313	8000652			THIS AIRCRAFT HAS RAM WATER COOLED ENGINE.  LEFT ENGINE WATER PUMP FAILED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002082600008	20020826	00008	SO  	2002	8	26	2002FA0000972    	1	20020816	G	2497		ELECTRICAL BOX  			PIPER 	PA46  	PA46500TP   	7104622	SO  										COCKPIT	LOOSE           	B				O				OTHER                   				I	G		FLT. ATTITUDE INST.       	MULTIPLE FAILURE          		CR	CRUISE         	1			SO	15	264B	251  				4697028				ENGINE DISPLAY UNITS, PILOT'S PRIMARY FLIGHT DISPLAY, COPILOT'S PRIMARY FLIGHT DISPLAY AND COPILOT'S NAV DISPLAY DIMMED 	OUT OF VIEW DURING CRUISE AT FL240.  PILOT REPORTED THAT DIMMING WAS AFFECTED BY OPERATION OF CABIN HEAT.  FOUND TAPER B	LOCK (TB4) TO HAVE LOOSE PINS.  THIS IS A DISTRIBUTION BLOCK FOR AIRCRAFT LCD DIMMING.				1	L	7	1 	3O			RT	A25SO   					 
2002082600009	20020826	00009	SO  	2002	8	26	2002FA0000973    	2	20020606	G	8520		CRANKCASE       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	6124Z	4047 	685  			U20606150	574729			CRACK 1.3750 INCH OUT OF THE UPPER REAR CYLINDER BASE STUD, AT THE ONE OCLOCK POSITION.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2002082600010	20020826	00010	CE  	2002	8	26	2002FA0000974    	1	20020801	G	3213	9530489	AXLE            			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480*      	41527	EA  					RT MLG	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	50718					1268				RIGHT GEAR AXLE BROKE (MAIN) ON LANDING, CAUSING SUBSTANTIAL DAMAGE TO FUSELAGE GEAR ATTACH AREA.						1	H	7	1 	3O	3	O	 	1A8     	E275				 
2002082600011	20020826	00011	WP  	2002	8	26	2002FA0000975    	2	20020806	G	8550	21713T009	HOSE            			AYRES 	S2    	S2RG10      	0970217	SO  	GARRTT	TPE331	TPE331*     	01514	WP  					OIL TANK VENT	DETERIORATED    	B			XR5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	40261	1945 				G10158				(HOSE)  DURING ROUTINE MAINTENANCE, THE .5000 INCH OVERBOARD VENT HOSE FROM THE ENGINE OIL TANK WAS FOUND TO BE RESTRICT	ED.  THE .5000 HOSE, WAS REDUCED TO .1250 OR LESS DIAMETER WHERE IT PASSED FROM THE OIL TANK, ALONG THE GAS GENERATOR.  	THE COMBINATION OF HEAT AND OIL MIST IS CAUSING THE DETERIORATION OF THE INSIDE OF THE HOSE.  THIS IS NOT THE FIRST OCCU	RRECE OF THIS PROBLEM.  RECOMMEND THAT THE MANUFACTURER INSTALL A .5000 INCH ALUMINUM TUBE IN PLACE OF THE HOSE FROM THE	 OIL TANK PAST THE ENGINE (APPROXIMATELY 3.5 FT), WHERE THE HOSE COULD THEN BE USED.		1	L	7	1 	3T	3	T	NC	A4SW    	E2WE				 
2002082600012	20020826	00012		2002	8	26	2002FA0000976    	4	20020604	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					PROP SPINNER	CRACKED         	B			FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	792SP	386  				172S8717				DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED THAT THE SPINNER BULKHEAD WAS CRACKED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002082600013	20020826	00013		2002	8	26	2002FA0000977    	4	20020516	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PROP SPINNER	CRACKED         	B			FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	51387	31   				172S9013				DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED THAT SPINNER BULKHEAD WAS CRACKED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002082600014	20020826	00014	SO  	2002	8	26	2002FA0000978    	2	20020731	G	8520		CRANKCASE       								CONT  	O520  	IO520D      	17032	SO  					ENGINE	CRACKED         	B			O3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03							552755			DURING OVERHAUL.  THE LIQUID PENETRANT INSPECTION REVEALS CRACKS IN MAIN BEARING BOSSES, CENTER ON LEFT SIDE.  DOWN IN O	IL CHANNEL RADIUS.  THIS CRANKCASE IS PHASE III 7TH STUD STYLE.										3	O			E5CE				 
2002082600015	20020826	00015		2002	8	26	2002FA0000979    	4	20020717	G	3421	C6610550103	INDICATOR       			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COCKPIT	LEAKING         	B			MINR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	05	79CE					414A0263				AIRCRAFT LOST GYRO INSTRUMENTS AFTER TAKEOFF INTO IFR CONDITIONS.  TROUBLESHOT PROBLEM AND FOUND CO-PILOTS ART HORIZON C	ASE LEAKING.  CABIN PRESSURE DURING CLIMBOUT PRESSURIZED VACUUM SYSTEM CAUSING VACUUM FAILURE.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002082600016	20020826	00016	SO  	2002	8	26	2002FA0000980    	1	20020802	G	7160		FLANGE          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					AIR BOX	FAILED          	B			QE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	978WC	400  			4496041	4496041				THE COMPONENT AS DESCRIBED WAS BROUGHT FOR INSPECTION AND WARRANTY REPAIR DUE TO FAILURE OF MOUNTING FLANGE TO THE TUBE.	  THE MOUNTING FLANGE SEPARATED FROM THE TUBE IN THE HEAT AFFECTED ZONE OF THE ATTACHING WELD.  ADDITIONAL CONDITIONS TH	AT CONTRIBUTED TO THE FAILURE IS THE TUBE IS BEADED AT THIS ATTACH POINT.  THE TUBE BASE MATERIAL APPEARS TO BE STRETCHE	D AND STRUCTURALLY CHALLENGED DUE TO BEADING OF THE TUBE.  THE AIR BOX WAS INSPECTED IAW SB AND NO PROBLEM WAS OBSERVED.	  AN ADDITIONAL CRACK WAS REPAIRED ON THE MOUNTING EAR OF THE FLANGE.		1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002082600017	20020826	00017	EA  	2002	8	26	2002FA0000981    	2	20020813	G	8520	SL13521	ROD END BEARING 			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  					ENGINE	SEPARATED       	B			ZM3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	66340	549  				ME241	L2645736A			METAL CONTAMINATION FOUND IN SUCTION SCREEN AND FILTER.  DISASSEMBLY OF ENGINE NOTED BABBIT SEPERATION FROM NR 1 ROD CAP	 BEARING SHELL.  THE REMAINDER OF THE OTHER ROD BEARINGS SHOWED SIGNS OF STARTING TO SEPARATE.					1	L	7	2 	3O	3	O	 	A29CE   	E286				 
2002082600022	20020826	00022	EA  	2002	8	26	2002FA0000982    	2	20020813	G	8520	SL16711	BEARING         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SEPARATED       	B			ZM3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	502ER	974  				172S8002	L2781636A			CONTAMINATION FOUND IN SUCTION SCREEN.  DISASSEMBLY OF ENGINE FOUND ONE OF THE CENTER MAIN BEARINGS BABBIT MATERIAL STAR	TED TO SEPARATE FROM SHELL.  DATE CODE ON BEARING IS (07-2000).					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002082600023	20020826	00023	SO  	2002	8	26	2002FA0000983    	1	20020816	G	2910	5777402	LINE            			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6*        	52043	EA  					HYD SYSTEM	CHAFED          	B			MVJR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			GL	25	75FL	4516 				428301002				DURING LANDING THE PILOT SELECTED GEAR DOWN, WITH NO RESPONSE FROM SYSTEM.  THE PILOT SUCCESSFULLY PUT GEAR DOWN WITH EM	ERGENCY BLOW DOWN SYSTEM AND A SAFE LANDING WAS MADE.  MAINTENANCE FOUND LEFT INBOARD PORTION OF WING COVERED IN HYDRAUL	IC FLUID.  UPON REMOVAL OF WING LEADING EDGE AND NACELLE PANELS THE LEAK WAS TRACED TO MAIN PRESSURE LINE FROM ENGINE DR	IVEN PUMP.  THE LINE WAS CHAFED THROUGH AT POINT WEAR IT ENTERS THE WING FROM NACELLE.  THE CHAFE CAME FROM SCREW THAT W	AS TO LONG IN LEADING EDGE TO NACELLE PANEL (PN 7261602) THIS  PANEL SELDEM NEEDS REMOVED AND ON SOME LIKE AC IT IS RIVE	TED ON.  THIS AREA SHOULD HAVE A CLOSE LOOK AT IT AT INSPECTION AND SCREW LENGTHS CHECKED.	1	L	7	2 	4T	3	T	 	A23SO   	E2NE				 
2002082600033	20020826	00033	SO  	2002	8	26	2002FA0000984    	1	20020801	G	2910	6390170	LINE            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	DETERIORATED    	B			O0BR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	09	15925	7209 				347350109				THE AIRCRAFTS NOSE GEAR FAILED TO EXTEND DURING ROUTINE TRAINING FLIGHT.  A/C MADE LANDING WITHOUT NOSE GEAR EXTENDING. 	 PILOT WAS ABLE TO FEATHER RIGHT ENGINE BUT LEFT SUFFERED A MINOR PROP STRIKE.  INSPECTION OF A/C ON THE RUNWAY REVELED 	THAT GEAR WAS FREE TO MOVE, HOWEVER IT WAS HELD IN UP POSITION WITH HYDRAULIC PRESSURE.  ONLY AFTER PRESSURE WAS RELIEVE	D FROM THE NOSE GEAR ACTUATOR DID GEAR EXTEND AND LOOK.  A/C  WAS PLACED ON JACKS AND CONTAMINATION (RUBBER PARTICLES AN	D OTHER DEBRIS) WAS REMOVED FROM THE OUTLET OF THE NOSE GEAR DOWN FLEX HOSE.  HOSE WAS REMOVED AND INSPECTION REVEALED I	NTERNAL LINING WAS DETERIORATING AND COLLAPSING.   SYSTEM WAS FLUSHED, SERVICED AND OPS CHECK PERFORMED SATISFACTORILY.	1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2002082600043	20020826	00043	CE  	2002	8	26	2002FA0000985    	1	20020712	G	2510	05142132	LOCK            			CESSNA	172   	172R        	2072401	CE  										SEAT BACK	WEAK            	B			Z08R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	9710F					17280017				THE LOCK CYLINDER RECLINE MECHANSIM BECOMES WEAK OVER TIME.  SEAT BACK WOULD RECLINE ABRUPTLY WHEN PRESSURE WAS APPLIED 	TO THE SEAT BACK, SUCH AS TAKEOFF.  THIS COULD CAUSE THE PILOT TO LOOSE CONTROL OF THE AIRCRAFT.					1	H	7	1 	3O			NT	3A12    					 
2002082600047	20020826	00047	SO  	2002	8	26	2002FA0000986    	1	20020805	G	3230	8360607	TRUNNION        			PIPER 	PA46  	PA46350P    	7104602	SO  										NLG	CRACKED         	B			HW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9167R	1913 				4622032				DURING ANNUAL INSPECTION FOUND CRACK IN NOSE LANDING GEAR TRUNION WHERE ACTUATOR ATTATCHES MAY BE CAUSED FROM TOWING AIR	CRAFT OR HAND LANDING.  RECOMMEND CLOSE INSPECTION OF THIS AREA.					1	L	7	1 	3O			RT	A25SO   					 
2002082600064	20020826	00064	SO  	2002	8	26	2002FA0000989    	2	20020814	G	7414	6220	MAGNETO         			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	CORRODED        	B			GBBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	59132					21060112	517861			DURING MAINTENANCE, IT WAS NOTED THAT THE MAGNETOS WERE HAVING TROUBLE HOLDING THEIR TIMING POSITIONS.  RT MAGNETO WAS D	ISASSEMBLED AND FOUND THAT THE DRIVE AND DRIVEN GEARS HAD ROTTED TO THE POINT OF LOSING TEETH.  NOTED THAT THE CARBON BU	TTON THAT RIDES ON THE COIL TAB HAD WORN THROUGH AND THE BUSHINGS THAT SUPPORT THE DISTRIBUTOR GEAR HAD BEEN SEVERELY WO	RN.  ALL OF THE INTERNAL HARDWARE WAS SEVERELY CORRODED.  BOTH POINT CAMS WERE BADLY WORN AND THE POINTS WERE WORN TO TH	E POINT OF BEING INOPERATIVE.  DEFECTS WERE FOUND IN RT AND LT MAGNETOS.  THE DRAIN FOR MAGNETO PRESSURIZATION FILTER HA	D BEEN SILICONED CLOSED.	1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2002082600065	20020826	00065	SO  	2002	8	26	2002FA0000990    	2	20020814	G	7414	6220	MAGNETO         			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	CORRODED        	B			GBBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	59132					21060112	517861			DURING MAINTENANCE, ITS WAS NOTED THAT THE MAGNETOS WERE HAVING TROUBLE HOLDING THEIR TIMING POSITIONS.  RT MAGNETO WAS 	DISASSEMBLED AND FOUND THAT THE DRIVE AND DRIVEN GEARS HAD ROTTED TO THE POINT OF LOSING TEETH.  NOTED THAT THE CARBON B	UTTON THAT RIDES ON THE COIL TAB HAD WORN THROUGH AND THE BUSHINGS THAT SUPPORT THE DISTRIBUTOR GEAR HAD BEEN SEVERELY W	ORN.  ALL OF THE INTERNAL HARDWARE WAS SEVERELY CORRODED.  BOTH POINT CAMS WERE BADLY WORN AND THE POINTS WERE WORN TO T	HE POINT OF BEING INOPERATIVE.  DEFECTS WERE FOUND IN RIGHT AND LEFT MAGNETOS.  THE DRAIN FOR MAGNETO PRESSURIZATION FIL	TER HAD BEEN SILICONED CLOSED.	1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2002082600066	20020826	00066	WP  	2002	8	26	2002FA0000991    	2	20020715	G	7532	HTE49029A	SEAL            			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE7315R    	01518	WP  					BLEED VALVE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	217AL					258177				AFTER TAKEOFF, DURING CLIMBOUT, PILOT REPORTED AFT EQUIPMENT BYA OVERHEAT LIGHT ON MASTER CAUTION WARNING PANEL ILLUMINA	TED.  RETURNED TO PLACE OF ORIGIN.  AFTER TROUBLESHOOTING, FOUND DETERIORATED BLEED VALVE SEAL AT RIGHT ENGINE BLEED AIR	  SHUTOFF VALVE IN AFT EQUIPMENT BAY.  REPLACED DEFECTIVE SEAL WITH NEW SEAL.  RAN BOTH ENGINES AT POWER AND PERFORMED O	PERATIONAL AND LEAK CHECK.  NO DISCREPANCIES NOTED.  SUSPECT CAUSE OF DEFECT IS SHRINKAGE OF SEAL OVER PERIOD OF TIME.  	RECOMMEND PERIODIC BLEED AIR LEAK CHECKS AND TORQUE CHECKS OF BLEEDAIR MARMON CLAMPS.		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002082600068	20020826	00068	EA  	2002	8	26	2002FA0000992    	2	20020808	G	8520		PIN             			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					LIFTER/BORE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	102SB	80   				P375	L61959			THE LIFTER BORES WERE ALL SLEEVED (ALL 12) NOTE: THE SLEEVES CAME LOOSE IN ALL THE HOLES (EXCEPT TWO) ROTATING AND BLOCK	ING OFF OIL PASSAGES.  THERE WERE NO STANDARD SAFETY PINS, OR DEVICES TO HOLE THE LIFTER SLEEVE IN PLACE.  THERE ARE MAN	Y OTHER ENGINES IN SERVICE WITH THIS SAME REPAIR PRACTICE IN PLACE.				1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2002082600001	20020826	00001	NM  	2002	8	26	2002FA0000993    	1	20020706	G	5730	P2V7	DOUBLER         			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R335042     	 	EA  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	139HP	8782 				145906				LOWER WING SKIN ACCESS PANEL CUTOUT DOUBLER CRACKED IN SEVERAL PLACES CWS 90 LEFT SIDE TO CWS 90 RIGHT SIDE.  RIGHT WING	 LOWER SKIN CRACKED AT AN ACCESS PANEL CWS 94.  (SW)					2	M	7	2 	2R	4	R	RT	A1RM    	 				 
2002082600002	20020826	00002	NM  	2002	8	26	2002FA0000994    	1	20020709	G	5730		DOUBLER         			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R335042     	 	EA  					RT WING	CRACKED         	B			BZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	140HP	9633 				140443				LOWER WING SKIN ACCESS PANEL DOUBLER CRACKED IN SEVERAL PLACES CWS 90 LEFT SIDE TO CWS 90 RIGHT SIDE.  RIGHT WING LOWER 	SKIN CRACKED AT AN ACCESS PANEL AT CWS 94.  (SW)					2	M	7	2 	2R	4	R	RT	A1RM    	 				 
2002082600003	20020826	00003	SO  	2002	8	26	2002FA0000995    	1	20020627	G	5711		SPAR            			LKHEED	282   	C130A       	5262502	SO  										LT & RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	133HP	16959				570482				FRONT WING SPAR WEB WAS CRACKED IN THE SAME LOCATION ON BOTH WINGS JUST ABOVE THE LOWER SPAR CHORD AT THE LANDING GEAR B	EAM					2	H	7	4 	4T			 	A31NM   					 
2002082600004	20020826	00004	NM  	2002	8	26	2002FA0000996    	1	20020708	G	5730		DOUBLER         			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R335042     	 	EA  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	139HP					145906				LOWER WING SKIN ACCESS PANEL DOUBLER CRACKED IN SEVERAL PLACES CWS 90 LEFT SIDE TO CWS 90 RIGHT SIDE.  RIGHT WING LOWER 	SKIN CRACKED AT AN ACCESS PANEL AT CWS 94.  (SW)					2	M	7	2 	2R	4	R	RT	A1RM    	 				 
2002082600005	20020826	00005	CE  	2002	8	26	2002FA0000998    	1	20020823	G	2810		SPACER          			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	FUEL CELL	BURNED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10						421C0031	608206H	891998		LT ENGINE AUX FUEL TANK ASSY HAS INCURRED HEAT RELATED DAMAGE ON THE ENGINE FIREWALL SIDE.  THE FIRE SPACER SCREEN AND T	HE RETARDANT COATING ON THE TANK ASSY HAS SINGED AND MELTED ALONG THE FIREWALL SIDE AND UNDERSIDE OF ASSY.  IN SOME AREA	S THE COATING HAS RECEDED EXPOSING THE ALUMINUM LINER.  THE VENT LINE FROM THE ENGINE HAS MELTED AN IMPRESSION INTO THE 	COATING.  ADHESIVE USED TO SECURE THE TANK WAS SIMILIARLY DAMAGED.  DAMAGE IS APPARENT BOTH ON THE TANK BODY AND IN THE 	CAVITY.		1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2002082700004	20020827	00004	EU  	2002	8	27	2002FA0001000    	1	20020808	G	5523	115C1155	BRACKET         			GROB  	G115  	G115C       	1660303	EU  	LYC   	O320  	O320*       	41508	EA  					ELEVATOR TRIM	CORRODED        	B			GZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	115SR	1872 				82036C				SUBJECT PART IS A BRACKET MOUNTING, A TORQUE TUBE FOR THE ELEVATOR TRIM CONTROL SYSTEM TO THE REAR SPAR OF THE HORIZONTA	L STABILIZER, AND WAS BEING REPLACED DURING COMPLIANCE OF MFG SB.  PART WAS FOUND WITH SEVERE EXFOLIATION CORROSION OF T	HE ALUMINUM UNDER THE SURFACE PLATING.  POSSIBLY A PROBLEM IN THE FABRICATION OF THE BASE MATERIAL OR THE PART ITSELF.  	CONDITION OF THIS COMPONENT SHOWS POTENTIAL FOR SAME PROBLEM TO BE FOUND ON COMPONENTS OF SIMILAR CONSTRUCTION ON THIS M	ODEL AIRCRAFT.		1	L	7	1 	3O	3	O	NT	A57EU   	E274				 
2002082700005	20020827	00005	EA  	2002	8	27	2002FA0001001    	2	20020808	G	8500		PLUG            			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					PULLEY DRIVE	MISSING         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	61426	1565 				0062	L3448236A			SCHEDULED INSPECTION AND MAINTENANCE, WHILE PERFORMING A COMPRESSION CHECK, IT WAS NOTED THAT THE ENGINE TURNING TOOL WE	NT INTO THE LOWER PULLEY DRIVE SPLINE FARTHER THAN NORMAL.  FURTHER INVESTIGATION REVEALED THE ENGINE DRIVE SHAFT TO BE 	IMPROPERLY POSITIONED IN THE LOWER PULLEY.  THE BELT DRIVE ASSEMBLY WAS REMOVED FROM THE HELICOPTER.  EXAMINATION OF THE	 ENGINE-MOUNTED DRIVE ADAPTER REVEALED THE PN 77416 FORWARD LOWER COUPLING BUMPER PLUG WAS MISSING.  THIS PLUG DETERMINE	S THE POSITION OF THE DRIVE SHAFT IN BOTH THE ENGINE AND THE LOWER PULLEY OF THE BELT DRIVE.		1	G	7	1 	3O	3	O	O	4H12    	E286				 
2002082700006	20020827	00006	CE  	2002	8	27	2002FA0001002    	1	20020729	G	2421		SCREW           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					ALTERNATOR	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	185BF		103  			18503590				THIS OVERHAULED ALTERNATOR WAS INSTALLED 06/28/02 AT TACH:642.0.  REMOVED 07/27/02 TACH:745.0.  PILOT COMPLAINED OF LOW 	READING ON AMG GAUGE.  UPON INSPECTION OF THE ALTERNATOR,  FOUND 1 CASE SCREW MISSING AND THE OTHER 2 COMING OUT OF CASE	 HALF.  THESE SCREWS WERE NOT SAFETY WIRED NOR DID THEY HAVE HOLES FOR WIRE.				1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2002082700007	20020827	00007	EU  	2002	8	27	2002FA0001003    	1	20020801	G	2497	2N5684	TRANSISTOR      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					POWER REG UNIT	INOPERATIVE     	C				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	01	6088B	3100 				2691	9747			PILOT REPORTED AIRCRAFTS RADIOS BEGAN TO SHUT DOWN FOLLOWED BY THE INDICATORS BECOMING ERRATIC.  PILOT BEGAN TO SHUT DOW	N NON ESSENTIAL ELECTRICAL LOADS.   ELECTRICAL SYSTEM BEGAN TO OPERATE NORMALLY.  PILOT RETURNED TO MAINTENANCE FACILITY	 AND LANDED WITH NO FURTHER PROBLEMS NOTED.  TECH. TROUBLESHOT PROBLEM ISOLATED TRANSISTOR IN POWER REGULATION UNIT.  GR	OUND RUNS SHOWED NO DEFECT AFTER REPLACEMENT.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002082700008	20020827	00008	EU  	2002	8	27	2002FA0001004    	1	20020801	G	2435		BRUSHES         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					STARTER GEN	FAILED          	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	01	6088B	2922 				2691	9747			PILOT REPORTED ELECTRICAL SYSTEM FAILURE AND ACCOMPLISHED AN EMERGENCY LANDING AT AIRPORT.  REMOVED STARTER/ GENERATOR, 	SUBSEQUEANT INSPECTION REVEALED ONE SET OF BRUSHES HAD FAILED.  THE SESULT OF THIS WAS A GRADUAL DROP OF OUTPUT COMPENSA	TED FOR BY THE AIRCRAFT BATTERY UNTIL THE BATTERY WAS DEPLETED.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002082700009	20020827	00009	CE  	2002	8	27	2002FA0001005    	1	20020813	G	2421		BEARING         			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520BA     	17032	SO  					ALTERNATOR	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	119RB	1267 				D8231				BEARING FAILURE IN ALTERNATOR CAUSED FAILURE OF CLUTCH ASSEMBLY.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002082700010	20020827	00010	SW  	2002	8	27	2002FA0001006    	1	20020716	G	6210	407015001117	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	DELAMINATED     	C				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			NM	01	175PA	2967 				53154				DURING HEAVY RAINFALL, AIRCRAFT EXPERIENCED VIBRATION ON MAIN ROTOR SYSTEM.  PILOT PERFORMED A PRECAUTIONARY LANDING.  M	ECHANIC INSPECTED THE MAIN ROTOR BLADES AFTER SHUT DOWN.  MECHANIC FOUND BOTTOM SIDE OF ONE BLADE 2 INCHES AFT OF LEADIN	G EDGE WITH METAL SKIN DELAMINATED FROM COMPOSITE BLADE.				1	G	7	1 	3U	3	U	O	H2SW    	E4CE				 
2002090400048	20020904	00048	CE  	2002	9	4	2002FA0001011    	1	20020628	G	2434	DOFF10300JR	PULLEY          			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300*       	17022	SO  					ALTERNATOR	LOOSE           	B			N9VR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	1684F					17255079				PILOT REPORTED NO ALTERNATOR OUTPUT.  INSPECTION FOUND PULLEY LYING INSIDE COWLING FROM ALTERNATOR.  ALTERNATOR STILL ON	 MOUNTS, BUT LOOSE.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002090400049	20020904	00049	EA  	2002	9	4	2002FA0001012    	2	20020801	G	7320	48E21297EPAJAY	CONTROLLER      			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					MANIFOLD PRESS	DAMAGED         	B			N9VR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	944S				70211207	4636306				CONTROLLER HAD AXIAL PLAY ON SHAFT FOR CONTROL ARM.  ENGINE WAS BACKING.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2002090400064	20020904	00064	SO  	2002	9	4	2002FA0001016    	2	20020816	G	8530	646657A2	CYLINDER        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					NR 2	CRACKED         	C				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			WP	07	58H					414A0314				UPON LANDING, PILOT REPORTED EXTREMELY ROUGH RUNNING ENGINE ON RIGHT SIDE.  INSPECTED AND FOUND NR2 CYLINDER ON RIGHT SI	DE TO BE CRACKED ALL THE WAY AROUND CYLINDER BETWEEN HEAD AND BARREL.  PILOT ALSO REPORTED ENGINE HAD HIGH CHT JUST BEFO	RE CHT DROPPED TO (0).				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002090400066	20020904	00066	CE  	2002	9	4	2002FA0001018    	1	20020821	G	2434	991059111	ALTERNATOR      			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	7265Z	116  				17280769				THE ALTERNATORS INSTALLED ARE FAILING CONSISTENTLY.  THEY USUALLY LAST BETWEEN 100 AND 500 HOURS FOR WHATEVER REASON THE	 RESISTANCE IN THE FIELD CIRCUIT INCREASES TO THE (MEGA OHM) RANGE, RENDERING THE ALTERNATOR TOTALLY INOPERATIVE DUE TO 	THE NATURE OF THE WARRANTY I AM NOT PERMITTED TO OPEN THE ALTERNATOR TO DETERMINE THE EXACT CAUSE.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002090400068	20020904	00068	CE  	2002	9	4	2002FA0001026    	1	20020821	G	2910		LINE            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					HYD SYSTEM	FAILED          	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	05	21PL					R18201983				WHEN PILOT SELECTED GEAR DOWN AND PRESSURE WAS APPLIED TO DOWN HOSE.  THE HOSE FAILED AT THE SWAGED END BLOWING ALL HYDR	AULIC FLUID OVERBOARD.  RECOMMEND CLOSER INSPECTION OF HOSES AND A MANDATORY TIME CHANGE OR BOTH HOSES.  (PN S217840102)	 DOWN AND (PN S217840096) UP.				1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2002090400070	20020904	00070	NE  	2002	9	4	2002FA0001027    	2	20020729	G	7320		O-RING          								LYC   	LTS101	LTS101750B2 	41560	NE  					ACTUATOR	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	13		5952 	12   		503					WITHIN THE FIRST FEW HOURS OF OPERATION SINCE OVERHAUL/ REPAIR THE ACTUATOR WILL FAIL TO ACTUATE OR ENGINE WILL EXHIBIT 	TORQUE SPLITS.  CAUSE: ORING/ PACKINGS USED DURING THE OVERHAUL/ REPAIR PROCESS.										3	U			E5NE				 
2002091900012	20020919	00012	EA  	2002	9	19	2002FA0001028    	2	20020826	G	7414	6381	MAGNETO         			CESSNA	182   	T182T       	       	CE  	LYC   	O540  	TIO540AK1A  	 	EA  					ENGINE	DAMAGED         	B			NM4R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SO	15	24712	205  				T18208027				OWNER COMPAINED WHEN RT MAGNETO WAS SELECTED ENGINE WOULD QUIT.  AFTER REMOVING MAGNETO FOUND MANY INTERNAL PARTS BURNED	.  REPLACED WITH NEW MAGNETO.  					1	H	7	1 	3O	3	O	NT	3A13    	 				 
2002090400044	20020904	00044		2002	9	4	2002FA0001029    	4	20020827	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	789EP	1801 				172S8135				AIRCRAFT UNDERGOING PHASE 1 INSPECTION, MAINTENANCE FOUND AFT PROPELLER SPINNER BULKHEAD CRACKED.  A ONE INCH PIECE OF T	HE BULKHEAD WAS BROKEN OFF CONTAINING 1 NUTPLATE.  REPLACED SPINNER BULKHEAD, REINSTALLED PROPELLER, OPERATIONAL CHECK S	AT.  				1	H	7	1 	3O			NT	3A12    					 
2002090400045	20020904	00045	SO  	2002	9	4	2002FA0001030    	2	20020829	G	8540	653631	GEAR            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	CRANKSHAFT	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	5119X					U20605571	818118R			DURING PRE-FLIGHT INSPECTION PROPELLER WAS ROTATED BACKWARDS BY HAND TO CHECK COMPRESSION OF CYLINDERS.  PROPELLER PHYSI	CALLY STOPPED BY SOMETHING INTERNAL IN ENGINE.  AFTER INSPECTION BY REMOVING THE STARTER ADAPTER ASSEMBLY, THE CRANKSHAF	T GEAR WAS FOUND TO BE MISSING ONE TOOTH FROM THE GEAR.				1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL	 
2002090400046	20020904	00046	SO  	2002	9	4	2002FA0001032    	2	20020903	G	8540	626739	COLLAR          								CONT  	O520  	IO520D      	17032	SO  					CRANKSHAFT	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07							282740R			AT INSTALLATION OF A NEW GOVERNOR OIL TRANSFER COLLAR IT WAS DISCOVERED THAT THE ASSEMBLY HALVES WERE IRREGULAR AT THE P	ARTING SURFACE.  THE INSIDE DIAMETER LOOKED SMOOTH AND REGULAR WHEN REMOVED FROM THE PACKAGE.  ONCE DISASSEMBLED AND REA	SSEMBLED AND TORQUED, THE INSIDE DIAMETER AT THE PARTING SURFACE EXHIBITED A STEP AND BECAME TIGHT ON THE CRANKSHAFT JOU	RNAL.  IT SEEMS THAT THE COLLAR WAS UNDER A STRESS THAT WAS RELIEVED AT THE FIRST DISASSEMBLY RESULTING IN THE MISALIGNM	ENT.  ANOTHER NEW COLLAR WAS ORDERED AND IT SHOWED THE SAME PROBLEM AS WELL.							3	O			E5CE				 
2002090400047	20020904	00047	SO  	2002	9	4	2002FA0001033    	2	20020903	G	8520	654068	ROD BOLT        								CONT  	O520  	IO520D      	17032	SO  					ENGINE	STRETCHED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07							566793			AT INSTALLATION OF THE NEW CONNECTING ROD BOLT AND NUT IT WAS NOTED THAT PROPER TORQUE WAS NOT ACHIEVED WITH THE SAME AM	OUNT OF TURNS AS THE OTHER ROD BOLTS AND NUTS.  A VISUAL INSPECTION SHOWED THAT MORE THREADS WERE SHOWING PAST THE NUT T	HAN OTHER BOLTS ON THE SAME CRANKSHAFT.  THE BOLT MEASURED .054 INCH LONGER THAT THE ADJACENT BOLT ON THE CONNECTING ROD	.  UPON DISASSEMBLY A VISUAL INSPECTION SHOWED THE THREADS TO BE DEFORMED, THE SHANK NEAR THE HEAD EXHIBITED SIGNS OF ST	RETCHING AND THE BEARING FACE OF THE HEAD SHOWED SOME GALLING.  IT IS POSSIBLE THE BOLT WAS SOFT AND NOT PROPERLY HEAT T	REATED.						3	O			E5CE				 
2002090400125	20020904	00125	CE  	2002	9	4	2002FA0001034    	1	20020823	G	3230	14141162	SPRING          			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					NLG UPLOCK	STRETCHED       	B			EW0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	35007	2867 				177RG1036				DURING LANDING GEAR RETRACTION TEST, NOSE GEAR WOULD NOT FULLY RETRACT.  THE BELLCRANK WAS FOUND OVERCENTER, CAUSING THE	 ROLLER TO MISS THE UPLOCK HOOK AND RESTRICT THE NOSE GEAR TRAVEL.  THE SPRING WAS FOUND STRETCHED AND NOT PROVIDING ADE	QUATE TENSION.  THE SPRING WAS REPLACED AND OPERATION WAS NORMAL.  THIS DEFECT CAUSED THE NOSE GEAR TO STAY PARTIALLY OU	T OF THE WHEEL WELL AND THE GEAR DOORS TO REMAIN APPROXIMATELY 30 DEGREES OPEN.  THIS COULD RESULT IN FAILURE OF THE DOO	RS AND POSSIBLE JAMMING OF THE NOSE GEAR.		1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2002090400155	20020904	00155	CE  	2002	9	4	2002FA0001035    	1	20020814	G	5511	053200198	SPAR            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					HORIZONTAL STAB	CRACKED         	D			KM9S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	6231D					17272649				CRACKS IN FORWARD OVERLAPPING SPARS FOUND AT LIGHTENING HOLE LOCATED IN CENTER OF HORIZONTAL STABILIZER.  100 HOUR INSPE	CTION WAS BEING PERFORMED ATH THIS TIME.  UPON REMOVAL, ADDITIONAL CRACKS WER FOUND ON THE OVERLAPPING SKIN.  THE ADDITI	ONAL CRACKS COULD NOT BE SEEN UNLESS HORIZONTAL STABILIZER IS REMOVED.  PROBABLE CAUSE: HIGH STRESS IN FLIGHT OR PUSHING	 DON ON OUTBOARD OF TAL.  POSITIVELY SURFACE CORROSION ALSO LOCATED IN THE AREA.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002090600199	20020906	00199	CE  	2002	9	6	2002FA0001036    	1	20020901	G	2910	208010015	HYDRAULIC LINE  			CESSNA	177   	177RG       	2073709	CE  										NLG	SEPARATED       	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	05	2002Q					177RG0402				HOSE ASSEMBLY SEPARATED AT SWEDGED END/ AT ACTUATOR NO CHAFFING OR OTHER APPARENT WEAR ON HOSE.						1	H	7	1 	3O			 	A20CE   					 
2002091000114	20020910	00114		2002	9	10	2002FA0001037    	4	20020905	G	3197		WIRE HARNESS    			CESSNA	172   	172R        	2072401	CE  										INSTUMENT PANEL	CHAFED          	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SO	07						17280548				WHEN THE PILOTS CONTROL COLUMN WAS PULLED AFT AND ROTATED, THE AILERON CABLE TURNBUCKLES AND ASSOCIATED HARDWARE CHAFED 	AGAINST A WIRE BUNDLE FORWARD OF THE INSTRUMENT PANEL.  THIS CAUSED TWO WIRES FROM THAT BUNDLE TO SHORT OUT AND BREAK, T	HUS RESULTING IN SPARKS COMING FROM UNDER THE INSTRUMENT PANEL.  BOTH FUEL QUANTITY INDICATORS IMMEDIATELY LOST POWER AN	D WENT TO ZERO.			1	H	7	1 	3O			NT	3A12    					 
2002091000117	20020910	00117	NE  	2002	9	10	2002FA0001038    	2	20020905	G	7250	3040761	STATOR          			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TURBINE SECTION	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	550DS	1755 	1755 			S5500154	PCE102316			AT HOT SECTION INSPECTION THE HT STATOR WAS FOUND TO HAVE AXIAL CRACKS IN SEVERAL PLACES IN THE INNER SHROUD RUNNING FRO	M THE TRAILING EDGE FORWARD TO 1/2IN. FROM INNER LUGS. AT ONE CRACK THE INNER SHROUD TRAILING EDGE LIFTED UP ENOUGH TO M	AKE CONTACT WITH THE HT DISK FRONT FACE IN THE FIR TREE AREA.				1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2002091000122	20020910	00122	GL  	2002	9	10	2002FA0001042    	1	20020816	G	3210	10209001	GROMMET         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					MLG	DEFORMED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	415GE	566  				0067				DURING ANNUAL INSPECTION FOUND MAIN GEAR LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. HAVE	 FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS.  TOTAL	 FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE.  SUGGEST	 CLOSE ATTENTION TO THESE PARTS DURING SCHEDULED INSPECTIONS AND AFTER HARD LANDINGS.			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2002091000123	20020910	00123	SO  	2002	9	10	2002FA0001043    	1	20020909	G	2913		PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  	HYD SYSTEM	FAILED          	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			GL	07	316GC					8152015	RL192368A			THE RIGHT ENGINE HYDRAULIC PUMP FAILED SOON AFTER TAKE OFF.  THE LANDING GEAR FAILED TO RETRACT FULLY.  THE PILOT TRIED 	SEVERAL TIMES TO EXTEND THE LANDING GEAR, AND FINALLY MANAGED TO GET THEM ALL IN A SAFE DOWN AND LOCKED POSITION, TO MAK	E A LANDING.   UPON INVESTIGATION, IT WAS FOUND THAT THE HYDRAULIC PUMP DRIVE SHAFT SEAL WAS BROKEN.  THIS WAS CAUSED BY	 A VALVE INSIDE THE PUMP THAT WAS STUCK IN THE OPEN POSITION, AND ALLOWED THE HYDRAULIC FLUID TO BE PUMPED OVERBOARD.  P	UMP MAY NOT HAVE BEEN CORRECTLY TESTED BY THE OVERHAULER.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P52GL	 
2002091000124	20020910	00124		2002	9	10	2002FA0001044    	4	20020811	G	2561	GA12P0201101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOTATION DEVICE FAILED, MANUFACTURER RECOMMENDED PRESSURE TEST IAW MM.  DOM: NOV 1984.																			 
2002091000125	20020910	00125	NM  	2002	9	10	2002FA0001045    	1	20020715	G	5730	143279	DOUBLER         			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	972TC18DA*  	 	EA  					WING	CRACKED         	B			NI6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	14447	10100				8010				DOUBLER FAILURE DUE TO IMPROPER MANUFACTURE PROCESS.  DOUBLER BROKE AT MACHINE RADIUS AND CORNER OF FUEL ACCESS PANEL LO	CATED IN LOWER INBOARD WING SKIN AREA.  WING SKIN DEVELOPED CRACKS LOCALIZED TO CORNER OF ACCESS PANEL.  REMOVED PAINT A	ND DYE PEN.  INSPECTED ALL CORNERS OF PANELS.  INSTALLED EXTERNAL DOUBLERS OVER SKIN CRACKED.  (SW)				2	M	7	2 	2R	4	R	RT	A1RM    	 				 
2002091100089	20020911	00089	EA  	2002	9	11	2002FA0001046    	2	20020823	G	8530	74230	VALVE GUIDE     			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					EXHAUST	SEIZED          	B			VY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	926WB					18280819	L2758248			NR 2 CYLINDER EXHAUST VALVE SIEZED IN VALVE GUIDE POSSIBLY DUE TO CARBON BUILD UP.  NR 2 PUSHROD AND PUSHROD SHROUD WERE	 BENT.  NR 2 EXHAUST PLUNGER ALSO REPLACED AT MFG RECOMMENDATION.					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2002091100090	20020911	00090	SO  	2002	9	11	2002FA0001047    	2	20020718	G	8530	641917	CYLINDER        								CONT  	C90   	C9014F      	17009	SO  					ENGINE	BROKEN          	D			HBKA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21		2486 					46942			THE ROCKER SHAFT ON THE EXHAUST PORT SIDE OF THE NR 1 CYLINDER FAILED.  INSPECTION OF THE OTHER THREE CYLINDERS SHOWED L	OOSE BUSHINGS IN THE SAME BOSS ON ALL THREE.  THE VALVE SPRING SEAT (PN 24027) WAS ALSO BROKEN, APPARENTLY INCIDENTAL TO	 THE ROCKER SHAFT BOSS FAILURE.  MORE FREQUENT DYE PENETRANT INSPECTION OF THE SUBJECT AREA IS NEEDED.									3	O			E252				 
2002091100088	20020911	00088	GL  	2002	9	11	2002FA0001048    	1	20020910	G	3210	10209001	GROMMET         			CIRRUS	SR    	SR22        	2130001	GL  										MLG	DEFORMED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	248CG	222  				0092				DURING ANNUAL INSPECTION FOUND BOTH MAIN GEAR LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED.	 HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. T	OTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE. SUGG	EST CLOSE ATTENTION TO THESE PARTS DURING SCHEDULED INSPECTIONS AND AFTER HARD LANDINGS.			1	L	7	1 	3O			NT	A00009CH					 
2002091900003	20020919	00003	CE  	2002	9	19	2002FA0001054    	1	20020822	G	3230	08421211	TUBE            			CESSNA	320   	320D        	2074512	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG DRIVE	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	09	320F					320D0020				NOSE GEAR FAILED TO RETRACT ON CROSS COUNTRY FLIGHT.  PILOT LANDED AT DESTINATION WITH MAINS LOCKED, AND HITTING THE NOS	E, NOSE GEAR DOORS AND BOTH PROPS (SEVERE) UPON LANDING.					1	L	7	2 	3O	3	O	 	3A25    	E5CE				 
2002091900004	20020919	00004	SW  	2002	9	19	2002FA0001055    	1	20020327	G	5511		SPAR            			GULSTM	500   	500A        	0141104	SW  	CONT  	O470  	IO470*      	17026	SO  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	471D	4592 				500A124070				FORWARD SPAR CRACKED IN RADIUS OF BEND.  SB COVERS THIS CONDITION.						1	H	7	2 	3O	3	O	 	6A1     	E1CE				 
2002091900005	20020919	00005	CE  	2002	9	19	2002FA0001056    	1	20020822	G	5751		HINGE           			BEECH 	58    	58          	1152740	CE  	LYC   	O360  	O360*       	41514	EA  					AILERON	MISALIGNED      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	793DW	78   				TH1421				DURING ROUTINE MAINTENANCE, TECH NOTICED LT AILERON MISALIGNED WITH TRAILING EDGE OF WING AT AILERON WELL.  FOUND THAT O	UTBOARD AILERON HINGE BOTTOM ATTACH SCREWS NOT IN HINGE ATTACH HOLES BUT CAUGHT BETWEEN AFT PORTION OF HINGE AND AILERON	 ATTACH HOLES.  SCREWS HAD ENOUGH BINDING FORCE TO FEEL AS THOUGH THREADING IN HINGE ATTACH HOLES, THIS CONDITION CAUSED	 AILERON MISALIGNMENT.  AIRCRAFT PAINTED 12/01 HAD FLIGHT CONTINUES REMOVED AND BALANCED.  AIRCRAFT FLEW 78 HOURS IN THI	S CONDITION.		1	L	7	2 	3O	3	O	 	3A16    	E286				 
2002091900006	20020919	00006	CE  	2002	9	19	2002FA0001059    	1	20020827	G	3110	10238400415	PANEL           			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COCKPIT	SHORTED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	17	68BB	3649 				TJ317				PANEL ON SWITCH PANEL LIGHTING SHORTED WHICH MADE THE INVERTER EMITTED SMOKE INTO THE COCKPIT.  BOTH PARTS WERE REPLACED	 WITH NEW PARTS FROM MFG.					1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2002091900007	20020919	00007	CE  	2002	9	19	2002FA0001060    	1	20020830	G	3230	MS252534	SWITCH          	CESSNA      		CESSNA	402   	402B        	207590P	CE  										MLG	FAULTY          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	13	5403M					402B0003				LANDING GEAR WILL NOT RETRACT.  DURING NORMAL TAKEOFF, FAULTY SWITCH FOUND ON.  SAFETY SWITCH ASSEMBLY ON LT MLG ASSEMBL	Y.  REPLACED SWITCH AND CHECK OPS OK.  AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3O			 	A7CE    					 
2002091800073	20020918	00073	NM  	2002	9	18	2002FA0001061    	1	20020828	G	8000	V31001	SWITCH          			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360*       	41514	EA  					ACTUATOR	FAILED          	C				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	17	7087X	24   				2829				ENGINE WOULD NOT CRANK, NOR WOULD CLUTCH ENGAGE (BELT TENSION MOTOR WOULD NOT ENERGIZE); ELECTRIC POWER DID NOT PASS THR	OUGH A NORMALLY CLOSED SWITCH IN THE ACTUATOR ASSEMBLY.  REMOVED ASSEMBLY FROM AIRCRAFT;  REMOVED SWITCH FROM ASSEMBLY. 	 THE SWITCH WAS INOPERATIVE AND HAD LOOSE COMPONENTS RATTLING INSIDE ITS CASE.				1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2002091800105	20020918	00105	SO  	2002	9	18	2002FA0001062    	2	20020911	G	8550	625207	TUBE            								CONT  	O520  	IO520D      	17032	SO  					OIL SUMP	DEFECTIVE       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07										AT ENGINE OVERHAUL, PRIOR TO INSTALLING OIL SUCTION TUBE ASSY'S IN TWO IO-520D ENGINES, BOTH WERE DISCOVERED TO BE DEFEC	TIVE.  ONE TUBE WOULD NOT FIT PROPERLY AND APPEARED TO HAVE NOT BEEN JIGGED PROPERLY IN THE WELDING PROCESS.  THE OTHER 	TUBE HAD SPOT WELDS BROKEN LOOSE AND THE BRAZING PROCESS WAS INCOMPLETE.									3	O			E5CE				 
2002091800106	20020918	00106	CE  	2002	9	18	2002FA0001063    	1	20020911	G	3240	03018901	BRAKE ASSY      			CESSNA	500   	550         	2076604	CE  										MLG	LOCKED          	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	11	15JA	177  	177  			5500035				R/H BRAKE ASSY LOCKED UP UPON LANDING CAUSING DAMAGE TO INBOARD WHEEL HALF.						1	L	7	2 	4F			 	A22CE   					 
2002091800109	20020918	00109	CE  	2002	9	18	2002FA0001064    	1	20020911	G	5347	051418215	SEAT TRACK      			CESSNA	172   	172P        	2072436	CE  										COCKPIT	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	381J	10012				17274183				AN INSPECTION OF THE SEAT FRAME REVEALED WEAR BETWEEN THE PEDESTAL FRAMES AND THE TORQUE TUBES. THIS ALLOWED THE SEAT FR	AME TO "RACK" FROM SIDE TO SIDE WITH THE WEIGHT OF THE PILOT SITTING IN IT. AT TIMES THIS WOULD CAUSE ONLY ONE SEAT PIN 	TO PARTIALLY ENGAGE THE SEAT RAIL.  WIGGLING THE SEAT AROUND WOULD ALLOW BOTH SEAT PINS TO FULLY ENGAGE THE SEAT RAILS. 	WITHOUT THE WEIGHT OF A PERSON IN THE SEAT THE SEAT PERFORMED SATISFACTORILY. THE AIRCRAFT WAS IN COMPLIANCE WITH AD 87-	20-03 R2 AND THE SEAT RAILS HAD BEEN REPLACED 1159 HOURS AGO. THE AIRCRAFT HAD 183 HOURS SINCE ITS LAST ANNUAL INSPECTIO	N.	1	H	7	1 	3O			NT	3A12    					 
2002091800110	20020918	00110	CE  	2002	9	18	2002FA0001065    	1	20020916	G	2822	LW15473	PUMP            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	2272H	779  				17280688	L2791051A			BOLTS LOOSE IN FUEL PUMP DIAPHRAGM.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002091800111	20020918	00111	CE  	2002	9	18	2002FA0001066    	1	20020916	G	3232	28233330511	BRACKET         			RKWELL	NA265 	NA26565     	7630107	CE  										LT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	670AS	9263 				58				DURING GEAR RETRACTION TEST, LT MLG DOOR ACTUATOR ATTACH BRACKET BROKE AT GEAR DOOR.						2	L	7	2 	4J			 	A2WE    					 
2002091800112	20020918	00112	CE  	2002	9	18	2002FA0001067    	1	20020917	G	2800	51001101	LINE            			CESSNA	414   	414A        	2075907	CE  										FUEL VENT	CHAFED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	10	414ST	6990 				414A0614				FUEL RUNNING OUT OF LEFT VENT WHEN TOPPED OFF. INSPECTION REVEALED LEFT VENT TUBE HAD A HOLE CHAFED IN IT BY FUEL FILLER	 PORT SCREEN. THIS AIRCRAFT HAD RAM WINGLETS INSTALLED SEVERAL HOURS BEFORE THIS OCCURED. LINE MAY HAVE BEEN BENT DURING	 THIS INSTALLATION, CAUSING LINE TO CHAF ON FILLER PORT SCREEN. INSPECTED RIGHT SIDE WITH NO CHAFING FOUND. RECOMMEND TH	IS LINE TO BE INSPECTED WHEN FUEL TANKS ARE OPENED, OR VISUAL INSPECTION THRU FILLER PORT.			1	L	7	2 	3O			 	A7CE    					 
2002092000035	20020920	00035	SO  	2002	9	20	2002FA0001068    	1	20020829	G	2910	3153600	LINE            			PIPER 	PA23  	PA23250     	7102308	SO  										HYD SYSTEM	BROKEN          	B			VT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	508UU					277954001				DURING LANDING APPROACH, LANDING GEAR FAILED TO EXTEND EITHER NORMALLY OR BY USING HAND PUMP.  LANDING GEAR WAS EXTENDED	 BY USING BLOW DOWN BOTTLE, NOSE AND RIGHT REAR DID NOT EXTEND AND AIRCRAFT WAS SUBTANTIALLY DAMAGED DURING LANDING.  IN	SPECTION REVEALED THE RIGHT MAIN LANDING GEAR DOWN INE IN NACELLE HAD FAILED AT THE SLEEVE/FLARE AREA.				1	L	7	2 	3O			 	1A10    					 
2002092000036	20020920	00036	SW  	2002	9	20	2002FA0001069    	1	20020828	G	6220	407310102101	BEARING         	BELL        		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					M/R HUB	SEPARATED       	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PR	3247 			A254	53232				ELASTOMERIC PORTION OF BEARING COMPLETELY DEBONDED FROM BASE.  FOUND AT ROUTINE INSPECTION.   THIS BEARING IS ONE OF A B	ATCH OF DEFECTIVE BEARINGS MANUFACTURED BEFORE 1998.  RECOMMEND THAT BEARING BE BONDED WITH BETTER MATERIAL OR ADHESIVE.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002092000037	20020920	00037	SW  	2002	9	20	2002FA0001070    	1	20020806	G	5302	2060313291	FITTING         			BELL  	206   	206B        	1181511	SW  										TAILBOOM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	3202X	21498				3939				DURING A 100 HOUR, INSPECTION, THE LEFT UPPER TAILBOOM ATTACH FITTING WAS FOUND TO BE CRACKED.  THE CRACK WAS FROM THE L	OWER AFT RIVET HOLE, THRU THE UPPER AFT RIVET HOLE, AND EXTENDED TO THE UPPER EDGE OF THE FITTING.  (WPO12002B6504)					1	G	7	1 	3U			 	H2SW    					 
2002092000039	20020920	00039	CE  	2002	9	20	2002FA0001072    	1	20020902	G	2823	07161114	SHUTOFF VALVE   			CESSNA	172   	172S        	2072439	CE  										FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	3513K	153  				172S8917				DURING ANNUAL INSPECTION, FOUND FUEL SHUT-OFF VALVE LEAKING EXTERNALLY AT COVER.  REPLACED WITH NEW PART.						1	H	7	1 	3O			NT	3A12    					 
2002092000040	20020920	00040	CE  	2002	9	20	2002FA0001074    	1	20020806	G	3222	08421201	TUBE            			CESSNA	320   	320         	2074502	CE  										NOSE GEAR	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09		4500 				320D0020				TUBE ASSEMBLY.  DURING LANDING APPROACH THE NOSE GEAR DID NOT EXTEND, AND THE GEAR DOWN GREEN LIGHT DID NOT ILLUMINATE. 	 AIRCRAFT LANDED AND NOSE GEAR COLLAPSED.  INSPECTION REVEALED FAILURE OF NOSE GEAR TUBE ASSY.  RECOMMEND THIS TUBE REPL	ACED BY ACCUMULATION OF CYCLES.				1	L	7	2 	3O			 	3A25    					 
2002092000041	20020920	00041		2002	9	20	2002FA0001076    	4	20020903	G	2562	450017	ANTENNA         																	ELT	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09										(ELT ANTENNA)  THE ELT DID NOT TRANSMIT WHEN TESTED ON THE AIRCRAFT AT 100 HOUR INSPECTION.  ELT WORKED WHEN PORTABLE AN	TENNA USED.  VISUAL INSPECTION FOUND MAST LOOSE.  THE ANTENNA WAS MACHINED TO A DIAMETER OF .040 TO .050 AT THE BNC REDE	SIGN USING A FLEXIBLE MAST AND BETTER BASE CONNECTION.																	 
2002092000042	20020920	00042	EA  	2002	9	20	2002FA0001077    	2	20020904	G	8530	1519995735	PUSHROD         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENGINE	BENT            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	9290P	697  				4496019				THE NUMBER 2 CYLINDER EXHAUST PUSH ROD BENT IN FLIGHT.						1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002092000043	20020920	00043	CE  	2002	9	20	2002FA0001078    	1	20020904	G	7603	640791A5	THROTTLE CONTROL			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LEFT ENGINE	BINDING         	D				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NM	07	146Z	100  				TJ426	822553			PILOT REPORTED BINDING OF LEFT ENGINE THROTTLE.  INVESTIGATION REVEALED GALLING OF MIXTURE ADJUSTMENT ROD WHERE IT ATTAC	HES TO THE THROTTLE LEVER, WITH A SIGNIFICANT AMOUNT OF TRANSFER OF METAL FROM THE LEVER TO THE ROD, PREVENTING FULL THR	OTTLE MOVEMENT.  THIS THROTTLE LEVER APPEARS TO BE MADE FROM A MATERIAL DIFFERENT FROM WHAT WAS PREVIOUSLY USED.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2002092000044	20020920	00044	CE  	2002	9	20	2002FA0001079    	1	20020905	G	7600	3012534	BOLT            			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					GOVERNOR CONTROL	CRACKED         	D			T40R	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NE	03	965LG	5858 				LW204	PCE24731			RIGHT ENGINE HAD NO REVERSE, FOUND FORWARD REVERSING CABLE/GOVERNOR BLEED LINK BOLT CRACKED AND SPLIT OPEN AT HOLE IN BO	LT FOR REVERSING CABLE TO THREAD THROUGH.  REVERSING CABLE COULD MOVE FORWARD AND AFT WITHOUT CONTROLLING GOVERNOR.  POS	SIBLE BOLT HAD BEEN OVERTORQUED IN THE PAST.  C/A:  INSTALLED NEW BOLT PN 3012534, AND RIGGED CONTROL. (NE032002B6857)				1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2002092000030	20020920	00030	EA  	2002	9	20	2002FA0001084    	2	20020919	G	7310		MANIFOLD        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	FUEL SYSTEM	MALFUNCTIONED   	B				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SO	15	428ER					17280607	L2724059A	TI039		THE CREW REPORTED A MOMENTARY POWER ROUGHNESS. THE AIRCRAFT FUEL CONTROL SYSTEM AND IGNITION SYSTEM WERE INSPECTED. THE 	FUEL MANIFOLD WAS REPLACED ALONG WITH 2 INJECTOR NOZZLES. A GROUND OPERATIONAL CHECK WAS PERFORMED. FOLLOWING THAT A FUN	CTIONAL CHECK FLIGHT WAS PERFORMED. NO DISCREPANCIES DURNING THAT FLIGHT WERE NOTED. THIS OPERATOR HAS MANY 172R AND 172	S MODEL AIRCRAFT. THERE HAVE BEEN NUMEROUS MOMENTARY POWER LOSS, ROUGHNESS REPORTS AND IRREGULAR IDLE DIFFICULTIES WITH 	THIS MODEL AIRCRAFT.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2002092000031	20020920	00031	CE  	2002	9	20	2002FA0001085    	1	20020722	G	7810	NH10089740	CLAMP           			CESSNA	310   	T310Q       	2074244	CE  	CONT  	O520  	TSIO520*    	17040	SO  					EXHAUST SYSTEM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	650PC					310Q0465				THIS CLAMP ATTACHES TAILPIPE TO TURBOCHARGER OUTLET.  DURING COMPLIANCE WITH AD2000-1-16 FOUND CLAMP SPLIT AT THE APEX O	F THE "V" AROUND 4.75" TO 5.0" OF CIRCUMFERENCE. PER AD2000-1-16 THIS CLAMP IS NOT LIFE-LIMITED.					1	L	7	2 	3O	3	O	 	3A10    	E8CE				 
2002092000032	20020920	00032	SO  	2002	9	20	2002FA0001086    	1	20020919	G	2750	67201101	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  										TE FLAPS	FRAYED          	B				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SO	15	492B	731  	50   			2844051				PILOT REPORTED AN 'UNUSUAL FEEL TO THE FLAP CONTROL. INVESTIGATION REVEALED THAT THE FLAP EXTENSION CABLE WAS SEVERELY F	RAYED. IT WAS REPLACED..					1	L	7	1 	3O			 	2A13    					 
2002092000034	20020920	00034	EA  	2002	9	20	2002FA0001088    	2	20020903	G	8500		ENGINE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	NACELLE	ROUGH           	B				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SO	15	470ER					17280614	RL2931751A	TI058		DURING FLIGHT, THE CREW REPORTED A ROUGH ENGINE. THE FLIGHT WAS TERMINATED AND MAINTENANCE WAS PERFORMED. THE SPARK PLUG	S WERE CLEANED AND THE INJECTOR NOZZLES INSPECTED..					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2002092000133	20020920	00133	CE  	2002	9	20	2002FA0001089    	1	20020905	G	3213	50810318	AXLE            			BEECH 	100   	A100        	1152915	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	18AH	1546 				B118				PISTON/ AXLE ASSEMBLY HOUSING HAS AN INDICATION OF A CRACK ON BOTH SIDES AT THE CASTING LINE.  ONE SIDE HAS AN INDICATIO	N APPROXIMATELY 2 INCHES LONG.  THE OTHER SIDE HAS AN INDICATION APPROXIMATELY 0.5 INCH LONG THESE INDICATIONS WERE FOUN	D DURING A ROUTINE 6 YEAR INSPECTION.				1	L	7	2 	3T			 	A14CE   					 
2002092000134	20020920	00134	CE  	2002	9	20	2002FA0001090    	1	20020905	G	5720		BRACKET         			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  					WING ROOT	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	2523Z	1141 				33777				DURING AN ANNUAL INSPECTION, FOUND WING ROOT FAIRING BRACKET AGAINST LOWER PART OF FORWARD SPAR (LEFT WING).  THE BRACKE	T APPEARS TO HAVE BEEN INSTALLED TOO CLOSE TO THE SPAR AT MANUFACTURE, CAUSING LOCAL MINOR DAMAGE.  REPAIRED LOCAL DAMAG	E.  INSPECTED ENTIRE LENGTH OF FORWARD AND AFT SPARS IN BOTH WINGS AND FOUND NO OTHER DAMAGE.				1	H	7	1 	3O	3	O	 	A21CE   	1E10				 
2002092000135	20020920	00135	EA  	2002	9	20	2002FA0001091    	2	20020905	G	8520		LIFTER          			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					ENGINE	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	18292					P433	L138259			SEVEN SPALLING OF LIFTERS AND CAM SHAFT WITH ONLY 130 HOURS USE.  ALSO FAILED WITH 60 HOURS USE.						1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2002092000136	20020920	00136	SO  	2002	9	20	2002FA0001092    	1	20020910	G	3220	83699003	ROD             			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	1AM					4622061				NOSE GEAR EMERGENCY EXTENSION DOWN SPRING ROD.  BROKEN AT 71 CYCLES DUE TO INFERIOR WELD OF THE FITTING ON THE END OF TH	E ROD.  VIOLENTLY SEPARATES FROM THE AIRCRAFT WHEN EITHER END BRAKES.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2002092400015	20020924	00015	EA  	2002	9	24	2002FA0001093    	2	20020701	G	7414	10357174	POINTS          	BENDIX      		PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					MAGNETO	BURNED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	15	814RC	195  			8050704	301202				DURING ENGINE RUN AND MAGNETO CHECK, MAGNETO WOULD RUN.  FOUND POINTS BURNED, PITTED AND WORN.  TOTAL HOURS ON ITEM: 195	.0, REPLACED BREAKER POINTS.  (SW15200210915)					1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2002092400016	20020924	00016	SO  	2002	9	24	2002FA0001094    	1	20020701	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					STABILATOR ROD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	8030Y					301139				DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 	AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUB AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS (PN AN175C33A) T	HAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED.  HORN ASSEMBLY, TOTAL AIRFRAME APPRO	XIMATELY 7565.0.  NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY.    (SW15200210914)			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2002092400017	20020924	00017	SO  	2002	9	24	2002FA0001095    	1	20020701	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					STAB TORQUE TUBE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	814RC					301202				DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 	AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS (PN AN175C33A) 	THAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED.  HORN ASSEMBLY, TOTAL AIRFRAME APPR	OXIMATELY 5050.0 NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY.  FILED FAA.   (SW 15200210910)			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2002092400018	20020924	00018	SO  	2002	9	24	2002FA0001096    	1	20020325	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					STAB TORQ TUBE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	7008Y					309				DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 	AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS (PN AN175C33A) 	THAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED.  HORN ASSEMBLY, TOTAL AIRFRAME APPR	OXIMATELY 5050.0 NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY.  FILED WITH FAA.  (SW15200208047)			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2002092400019	20020924	00019	SO  	2002	9	24	2002FA0001097    	1	20020325	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					STABILATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	7425P					242613				DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 	AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS (PN AN175C33A) 	THAT ATTACHES THE STABILATOR HORN ASSEMBVLY TO THE TORQUE TUBE WERE SEVERLY CORRODED.  HORN ASSEMBLY, ALSO BOLTS , TORQU	E TUBE HAD CORROSION ALSO.  THAT AIRFRAME, APPROXIMATELY 3073.0, NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUS	LY.  ALSO NOTED THAT THIS AIRPLANE WAS LOCATED IN FLA. FOR PART OF ITS LIFE.  FILED WITH FAA.  (SW15200208048)		1	L	7	1 	3O	3	O	 	1A15    	E295				 
2002092400020	20020924	00020	SO  	2002	9	24	2002FA0001098    	1	20020707	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360*       	41514	EA  					STABILATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	6841P	5515 				241974				DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 	AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS (PN AN175C33A) 	THAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED.  HORN ASSEMBLY,BOLTS, TOTAL AIRFRAM	E APPROXIMATELY 5515.0.  NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY.  FILED WITH FAA.  (SW15200210929)			1	L	7	1 	3O	3	O	 	1A15    	E286				 
2002092400021	20020924	00021	SO  	2002	9	24	2002FA0001100    	1	20020607	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  										STABILATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	GBZRO					301923				DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 	AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS (PN AN175C33A) 	THAT ATTACHES THE STABILARTOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED.  HORN ASSEMLBY, BOLTS, TOTAL AIRFR	AME APPROXIMATELY UNKNOWN.  AIRPLANE IS CURRENTLY LOCAKED IN UK.  NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOU	SLY.  FILED WITH FAA.		1	L	7	2 	3O			 	A1EA    					 
2002092400022	20020924	00022	CE  	2002	9	24	2002FA0001101    	1	20020822	G	2710	0523807	HINGE PIN       			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300*       	17022	SO  					AILERON	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	6643A					28743				DURING AN ANNUAL INSPECTION IT WAS FOUND THAT THE RIGHT OUTBOARD AILERON HINGE PIN HAD COME OUT OF THE HINGE ABOUT 5 INC	HES.  ONE COTTER PIN WAS STILL IN PLACE AND THE OTHER COTTER PIN WAS ONLY HALF THERE.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002092400023	20020924	00023	EA  	2002	9	24	2002FA0001102    	2	20020830	G	8520	LW12440	CAMSHAFT        			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541*     	41536	EA  					ENGINE	ERODED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	265D	35   				P548	L179059			WITH NO PROBLEMS TO 1952 HRS SINCE NEW (TBO1600), THIS ENGINE WAS OVERHAULED IN FEB 99.  NOTHING BUT PROBLEMS SINCE.  AT	 FIRST OIL CHANGE, AFTER OVERHAUL (35 HOURS) ABNORMAL METAL SLIVERS FOUND IN OIL FILTER.  CONTINUED FLYING.  MORE FERROU	S METAL AT 2ND OIL CHANGE (70 HOURS); UNACCEPTABLE AMOUNT AT 3RD (100 HOURS).  OVERHAULER REPLACED CAMSHAFT AND ALL LIFT	ERS WITH NEW MFG PARTS.  EXACTLY SAME RESULTS AT SAME TIMES AFTER REPLACEMENT, VOLUNTARILY GROUNDED AIRPLANE ON 4 FEB 20	02  WAITING MODIFIED CAMSHAFT NEARING STC APPROVAL.  UNDERSTAND STC IS LOW PRIORITY.  PLEASE EXPEDITE.		1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2002092400024	20020924	00024	EA  	2002	9	24	2002FA0001103    	2	20020803	G	8520	LW15861	LIFTER          			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541*     	41536	EA  					ENGINE	ERODED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	265D	35   				P548	L164859			WITH NO PROBLEMS TO 1952 HOURS SINCE NEW (TBO1600), THIS ENGINE WAS OVERHAULED IN FEB 99.  NOTHING BUT PROBLEMS SINCE.  	AT FIRST OIL CHANGE AFTER OVERHAUL (35 HOURS) ABNORMAL METAL SLIVERS FOUND IN OIL FILTER.  CONTINUED FLYING.  MOR FEROUS	 METAL AT 2ND OIL CHANGE(70 HOURS); UNACCEPTABLE AMOUNT AT 3RD (100 HOURS).  OVERHAULER REPLACED CAMSHAFT AND ALL LIFTER	S WITH NEW MFG. PARTS.  EXACTLY SAME RESULTS AT SAME TIMES AFTER REPLACEMENT, VOLUNTARILY GROUNDED AIRPLANE (DUKE B60) O	N 4 FEB 02 WAITING MODIFIED CAMSHAFT NEARING STC APPROVAL.  UNDERSTAND STC IS LOW PRIORITY.  PLEASE EXPEDITE.  (HAVE PHO	TOS)	1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2002092400025	20020924	00025	SO  	2002	9	24	2002FA0001104    	1	20020827	G	5730	5102299902	PANEL           			AMRGEN	AA5   	AA5         	0631410	SO  	LYC   	O320  	O320*       	41508	EA  					WING	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1317R					AA50717				HONEYCOMB SIDEPANELS HAVE BECOME DELAMINATED IN NUMEROUS AREAS, EVEN IN THE AREA THAT THE CARRY THROUGH SPAR IS BOLTED T	O.  THE DELAMINATION OF THE HONEYCOMB PANELS IN THIS AREA REDUCE THE STRUCTURAL INTEGRITY AND MAY ALLOW POSSIBLE SPAR SL	IPPAGE AFFECTING THE ANGLE OF INCIDENCE OF THE WINGS WHICH WILL DIRECTLY AFFECT THE FLIGHT CONTROLS BY BINDING THE FLAP 	AND AILERON TORQUE TUBES.  LARGE AMOUNT OF MFG AIRCRAFT WERE BUILT USING A PURPLE GLUE.  THIS GLUE WAS WIDELY USED IN TH	E MID 1970`S AND WAS SUSCEPTIBLE TO BONDED SKIN SECTIONS AND REFERS TO DELAMINATION.  (200206996)		1	L	7	1 	3O	3	O	 	A16EA   	E274				 
2002092400014	20020924	00014	SO  	2002	9	24	2002FA0001105    	1	20020906	G	2810	UNKNOWN	FUEL CAP        			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320A2A     	41508	EA  					RT TANK	BLOCKED         	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	01	2626P					222963	384827			AIRCRAFT WAS AT A CRUISE ALTITUDE OF 1800 FT WHEN ENGINE QUIT RUNNING. MADE AN EMERGENCY LANDING IN A HAY FIELD. FUEL SE	LECTOR WAS SELECTED ON RT TANK. POST INSPECTION FOUND ORIGINAL TYPE FUEL CAP VENTING WAS BLOCKED (RT TANK).  INSPECTION 	OF FUEL AND OIL SCREENS WERE NORMAL. ENGINE SUBSEQUENTLY STARTED AND RAN NORMALLY. CAUSE OF BLOCKAGE IN FUEL CAP IS UNKN	OWN.			1	H	7	1 	3O	3	O	 	1A6     	E274				 
2002092500002	20020925	00002	NM  	2002	9	25	2002FA0001110    	1	20020912	G	5102	RX83242	SPRING          			AROSTR	RX8   	RX8         	7487008	NM  										VALVE HANDLE	HUNG UP         	B			OG2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	7146J					RX83242				MALFUNCTION OF GLOW BURNER, VALVE HANDLE HANGING UP ON SPRING, CAUSING IT TO CONTINIOUSLY DISCHARGE PROPANE.  VALVE COUL	D NOT RETURN TO CLOSED POSITION.  TO PREVENT RECURRENCE, REPLACE WITH METAL HANDLE IN PLACE OF PLASTIC.  (SW)					1	B	0	0 	  			 	A15CE   					 
2002092700019	20020927	00019	GL  	2002	9	27	2002FA0001111    	1	20020925	G	3211	10209001	GROMMET         			CIRRUS	SR    	SR22        	2130001	GL  										MLG	DEFORMED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	929R	141  				0133				DURING A SCHEDULED INSPECTION FOUND BOTH MAIN GEAR LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTO	RTED. HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOU	RS. TOTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE.	 SUGGEST CLOSE ATTENTION TO THESE PARTS DURING SCHEDULED INSPECTIONS AND AFTER HARD LANDINGS.			1	L	7	1 	3O			NT	A00009CH					 
2002092700001	20020927	00001	GL  	2002	9	27	2002FA0001113    	3	20020920	G	6110	F7666A2	BLADE           	HARTZL      		AMTR  	STEEN 	STEENSKYBOLT	       	GL  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER	DAMAGED         	B			FR6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	302JS	3455 	135  		CH13880	100163		CH13880		PROP WAS REMOVED WITH 135.0 HOURS SINCE OVERHAUL.  REASON FOR REMOVAL WAS TO EVALUATE PROP FOR POSSIBLE TRADE IN. DURING	 PRELIMINARY INSPECTION OF BLADE WIDTH AND THICKNESS FOR VALUE ASSESSMENT,  BOTH BLADES WERE FOUND TO BE BELOW MFG MINIM	UM SPECS AT 34 INCH STATION.  ONE BLADE MEASURED 3.656 INCHES.  VISUAL CONDITION OF PROPELLER BLADES ARE NEARLY AS IF TH	EY WERE JUST OUT OF OVERHAUL, MEANING NO FILING HAS BEEN DONE ON LEADING EDGES OF BLADES AND THERE IS VERY LITTLE IF ANY	 PITTING FROM STONE DAMAGE.  PAINT ALSO LOOKS ORIGINAL FROM OVERHAUL AND HAS NOT BEEN REPAINTED.		1	Q	7	1 	3O	3	O	NC	EXPA1Q71	1E10	5	C	P920	 
2002092700002	20020927	00002	CE  	2002	9	27	2002FA0001114    	1	20020730	G	2821	7560097	FILTER          			CESSNA	188   	A188B       	2073005	CE  	CONT  	O520  	IO520D      	17032	SO  					FUEL SYSTEM	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	9639G					18801575	563319			THE FUEL FILTER SUFFERED CONTAMINATION TO THE POINT OF ENGINE LEANING, REDUCING POWER TO LOW TO MAINTAIN FLIGHT WHILE IN	 AERIAL APPLICATION WORK.  THE ALTITUDE WAS APPROXIMATELY .5000 FT AGL THE SPEED OVER THE CROP WAS 115 MPH.  REPOSITIONI	NG THE FUEL FILTER STRAINER DRAIN SO ONE COULD SEE THE CONDITION OF THE FUEL BEING DRAINED WOULD UNDOUBTLY HELP TO DETER	MINE IF CONTAMINATION IS PRESENT IF AT ALL IN THE FUEL.			1	L	7	1 	3O	3	O	 	A9CE    	E5CE				 
2002092700003	20020927	00003	CE  	2002	9	27	2002FA0001115    	1	20020913	G	3233	AN6227B9	O-RING          	CESSNA      		CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520*      	17032	SO  					ACTUATOR	LEAKING         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2398F	3708 				21058598				AIRCRAFT LANDED WITH MAIN LANDING GEAR UP AND NOSE GEAR DOWN.  CAUSE OF INCIDENT WAS A FAILED ORING IN NOSE LANDING GEAR	 ACTUATOR.  LEAK RATE DEPLETED RESEVOIR AND WAS TOO GREAT FOR HAND PUMP VOLUME.  MM HAS NO REPLACEMENT SCHEDULE FOR THES	E ORINGS.				1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2002092700004	20020927	00004	EA  	2002	9	27	2002FA0001116    	2	20020916	G	8530		INTAKE VALVE    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					CYLINDER	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	4074F	577  				318052164	L708261			INTAKE VALVE BROKEN AT CLIP END,  UNDER CRUISE POWER, VALVE REMAINED IN CYLINDER.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002092700016	20020927	00016	GL  	2002	9	27	2002FA0001117    	1	20020925	G	5751	10332002	FITTING         			CIRRUS	SR    	SR22        	2130001	GL  										AILERON HINGE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	929R	141  				0133				DURING INSPECTION FOUND LT INBOARD AILERON HINGE LOOSE.  CONDITION FOUND BY FEELING A CLUNK WHILE MOVING TRAILING EDGE O	F AILERON UP AND DOWN SLOWLY.  TRAILING EDGE OF AILERON HINGE ABLE TO BE MOVED 1/8" UP AND DOWN.  FOUND EVIDENCE OF "TOR	QUE-SEAL" ON ATTACH BOLT NUTS AND THREADS.  CONTINUED MOVEMENT OF AILERON HINGE COULD POTENTIALLY DAMAGE ATTACH HARDWARE	 AND CAUSE SEPARATION OF AILERON FROM WING.			1	L	7	1 	3O			NT	A00009CH					 
2002092700017	20020927	00017	GL  	2002	9	27	2002FA0001118    	3	20020926	G	6110	S90AT8	BLADE           			CESSNA	185   	A185F       	2072821	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	1056F	1855 				18502712		747226		RECEIVED PROPELLER FOR ROUTINE OVERHAUL. NO OVERHAUL OR INSPECTION SINCE 1982 (START OF LOG BOOK). PENETRANT INSPECTION 	OF PARTS REVEALED CRACK IN 1ST THREAD OF NR 1 BLADE. CONFIRMED WITH EDDY CURRENT. PROP WAS OIL FILLED IN 1982. NO INSPEC	TIONS PERFORMED ON BLADES AS WAS NOT A REQUIREMENT AT THAT TIME.				1	H	7	1 	3O			 	3A24    		5	C	P3EA	 
2002101100060	20021011	00060	EA  	2002	10	11	2002FA0001123    	2	20020919	G	7414	10382585	POINTS          	BENDIX      		BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720*      	41546	EA  					MAGNETO	MELTED          	B			KZ5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	103BA				B003505	LD435	L132654A			MELTING OF NYLON WHERE IT CONTACTS POINT ARM DURING OPENING AND CLOSING OF POINTS DURING OPERATION.  INFERIOR NYLON USED	, NOT RESISTANT TO WEAR OR HEAT.					1	L	7	2 	3O	3	O	 	3A20    	1E15				 
2002101100061	20021011	00061	EA  	2002	10	11	2002FA0001124    	2	20020920	G	7322		FLOAT           	PRECISION   		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CARBURETOR	DAMAGED         	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					CK611523					CARBURETOR SEAT IN FOR REPAIR BECAUSE IT WAS LEAKING.  AFTER DISASSEMBLY ONE PONTOON OF (AP) FLOAT WAS FILLED WITH FUEL.	  OPPOSITE PONTOON HAD MARK FROM RUBBING HOUSING.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002101100062	20021011	00062	CE  	2002	10	11	2002FA0001125    	1	20020914	G	3211	12414231	SADDLE          			CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2398F	2441 				21058598				BOTH MLG SADDLES WERE FOUND TO BE CRACKED IAW AD.  PREVIOUS INSPECTION WAS 132 HOURS BEFORE THIS INSPECTION.						1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2002101100063	20021011	00063	WP  	2002	10	11	2002FA0001126    	1	20020903	G	7910	3406220602	OIL TANK        			CVAC  	340   	340CVAC     	242270A	WP  	PWA   	R2800 	R2800*      	52026	NE  					ENG NACELLE	RUPTURED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	153JR					117				THE OIL TANK WAS OVERFILLED ON LEFT ENGINE.  ON TAKE OFF ROLL, THE PRESSURE FROM THE OVERFILL CAUSED THE TANK TO RUPTURE	.  OIL THEN BEGAN TO SPRAY ONTO THE EXHAUST SYSTEM.  THIS OIL IGNITED AND THE SUBSEQUENT FLAMES DAMAGED THE NACELLE IN T	HE AREA AFT OF THE OIL TANK, PRIMARILY ABOVE AND OUTBOARD.				2	L	7	2 	4R	4	R	 	6A6     	5E8				 
2002101100064	20021011	00064	CE  	2002	10	11	2002FA0001128    	1	20020911	G	2730	SAR21534	CABLE           			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320E2A    	41508	EA  					DOWN ELEV CABLE	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	1843G					78	L358555A			THE DOWN ELEVATOR CONTROL CABLE FAILED AT THE REAR PULLEY BELOW BATTERY BOX.  THE PULLEY HAD STOPPED TURNING THUS CUTTIN	G OR WEARING CONTROL CABLE TO A CONDITION IT WHERE IT FAILED WITH HARD FORWARD STICK.  METER SHOWED .5 AND GS.					1	H	7	1 	3O	3	O	 	A759    	1E12				 
2002101100073	20021011	00073	EA  	2002	10	11	2002FA0001130    	2	20020909	G	7322	MA4SPA	CARBURETOR      			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	43473	4000 				287415504	L3757427A			(CARBURETOR) AN ALUMINUM SLIVER, .188 LONG, .018 THICK, .023 WIDE WAS FOUND BETWEEN THE NEEDLE VALVE AND SEAT.  PREVENTI	NG OPERATION OF NEEDLE VALVE.  THE SLIVER APPEARS OF THE THROTTLE BODY ASSEMBLY,  WHERE THE FUEL INLET AND STRAINER ASSE	MBLY IS INSTALLED.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002101100074	20021011	00074	SO  	2002	10	11	2002FA0001131    	1	20020905	G	3211		BOLT            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					LT MLG	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	2171D	12250				287916146				LT GEAR ASSEMBLY SHEARED UPPER AND LOWER RETAINING BOLTS.  UPON LANDING, AIRCRAFT USED FOR STUDENT TRAINING AND HAS OVER	 12200.0 HOLES, SUSPECT HARD LANDINGS WAS CAUSE.  REPLACE BOLTS AND INSPECT MOUNTING AREA AT 5000 HOURS.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002101100075	20021011	00075	CE  	2002	10	11	2002FA0001133    	1	20020531	G	2820	AN91220	FITTING         	CESSNA      		CESSNA	172   	172RG       	2072438	CE  										FUEL SYSTEM	CRACKED         	B			LW5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	9515B					172RG0846				THE FUEL STRAINER ON THIS PARTICULAR AIRCRAFT IS NOT MOUNTED RIGIDLY TO THE AIRFRAME.  THEREFORE IT IS SUPPORTED BY THE 	FUEL LINES ATTACHED TO IT.  THE VIBRATIONS CAUSED THIS FITTING TO CRACK.  MFG MM LATER MODELS USE BRACKET FOR MOUNTING.					1	H	7	1 	3O			 	3A17    					 
2002101100077	20021011	00077	EU  	2002	10	11	2002FA0001134    	1	20020910	G	2150	20388022	BLADE           			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					COOLING TURBINE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	799S	1790 				258019				FAILURE OF TURBINE BLADE IN COOLING TURBINE RESULTING IN VIOLENT VIBRATION CAUSING CRACKING TO THE HEAT EXCHANGER ASSEMB	LY.  THE CURRENT INTERVAL ON THIS COMPONENT IS O/C.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002101100080	20021011	00080	GL  	2002	10	11	2002FA0001135    	3	20020830	G	6110	E697711D	BRACKET         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCA3V	HCA3V*      	GL  	PROP BLADE CUFF	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	44US	400  				BB56	PCE80109	BUA22847		THE BRACKETS (PN E6977-11D) THAT SUPPORT THE QUICK DISCONNECT PLUG ASSEMBLY FOR THE PROP DEICE BOOT DUG INTO THE PROPELL	ER BACKPLATE.  THIS WAS DONE TO VARYING DEGREES AT EACH BLADE POSITION ON THE BACKPLATE.  THIS OCCURRED ON BOTH PROPS AL	THOUGH IT WAS WORSE ON THE RIGHT PROP.  THIS IS THE PROP REFERENCED ON THE FORM.  THE HITTING OF THE BACKPLATE BY THE DE	ICE BRACKET ONLY OCCURS WHEN THE PROP GOES TO MAX REVERSE.  THE PROPS ARE NOW AT THE PROP SHOP FOR INVESTIGATION.			1	L	7	2 	4T	3	T	 	A24CE   	E2NE	5	C	P6EA	 
2002101100081	20021011	00081	CE  	2002	10	11	2002FA0001136    	1	20020815	G	5542		SKIN            			BEECH 	200   	B200        	1152922	CE  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	942CE	595  				B1731				FOUND A 3.5 INCH CRACK APPROXIMATELY 6 INCHES DOWN AND .0200 INCH ON THE RIGHT SIDE TRAILING EDGE OF THE RUDDER.						1	L	7	2 	4T			 	A24CE   					 
2002101100095	20021011	00095	GL  	2002	10	11	2002FA0001139    	3	20020826	G	6111	72R3BD	BLADE           			AMTR  	GLASTR	GLASTAR     	05605M8	GL  	LYC   	O320  	O320*       	41508	EA  	AMTR	T6801	WRAPDRIVE   	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	99DF	37   				5221		T8021		PROPELLER BLADE SHANK CRACKED RADIALLY AT THE JUNCTION OF THE SHANK AND THE BLADE.  SLIGHT FORE AND AFT BLADE MOVEMENT D	ETECTABLE.  ALL 3 BLADES CRACKED.  INSTALLATION LOOKED PROPER WITH CORRECT TORQUE ON HUB AT BLADE ATTACH POINT.					1	H	7	1 	3O	3	O	NC	EXPA1H71	E274	5	C	EXPA5C	 
2002101100097	20021011	00097	CE  	2002	10	11	2002FA0001140    	1	20020918	G	5521		SPAR            			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520*      	17032	SO  					LT ELEVATOR	CRACKED         	B			LC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	7952M	3500 				TE192				REMOVED LT ELEVATOR AND FOUND REAR SPAR CRACKED AT TRIM TAB ACTUATOR.  TECH SUPPORT AND CONSENSUS IS TO REPLACE REAR SPA	R.					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002101100105	20021011	00105	CE  	2002	10	11	2002FA0001142    	1	20020911	G	5523	50340091	STRUCTURE       			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ELEVATOR TAB	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	616RM	5800 				4140375				DURING 100 HOUR INSPECTION, ELEVATOR TRIM BEARINGS WERE SUSPECTED TO BE LOOSE AND REQUIRE REPLACEMENT.  TO REPLACE THESE	 BEARINGS, ELEVATOR TRIM TAB HORN WAS REMOVED.  WHEN FORCE WAS APPLIED TO TWO OF  FOUR ATTACHING NUTS TO EFFECT THEIR RE	MOVAL FROM THE MATING SCREW, THEY SEPARATED, BROKE OFF INSIDE OF TRIM TAB.  WHEN FULL REMOVAL OF TWO OF SCREWS WAS EFFEC	TED IT WAS NOTED THAT ONE HAD RUST CORRODED OVER 90 PERCENT OF ORIGINAL DIAMETER AND SECOND SCREW HAD A FULL 100 PERCENT	 LOSS.  ONLY ATTACHMENT OF THESE SCREWS WERE FROM THE COATING OF PAINT APPLICATION.		1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2002101100108	20021011	00108	SO  	2002	10	11	2002FA0001143    	2	20020925	G	7414		DISTRIBUTOR BLK 			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					MAGNETO	BURNED          	D			GMZ2	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	01	5227K	200  				3449205	322103			DURING MAGNETO PERFORMANCE, CHECK PRIOR TO FLIGHT, PILOT NOTED ENGINE WANTED TO QUIT RUNNING WITH RIGHT MAGNETO SELECTED	 TO OFF.  EXTERNAL INSPECTION OF MAGNETO LEFT CHECKED GOOD. REMOVED LEFT MAGNETO AND INSPECTED INTERNALLY.  INSPECTION R	EVEALED .5000 INCH SECTION OF DISTRIBUTOR BLOCK BURNED AWAY.  UNKNOWN CAUSE AND NO RECOMMENDATION AT THIS TIME.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002101100109	20021011	00109	NM  	2002	10	11	2002FA0001144    	1	20020925	G	2741	6355B000103	MOTOR           			BOEING	737   	737*        	       	NM  										STAB TRIM	INOPERATIVE     	B			VK6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	09										THE UNIT PASSED ALL TESTS AND WAS READY TO BE SHIPPED BACK TO THE CUSTOMER.  WHEN THE TECHNICIAN NOTICED A RATTLE INSIDE	 THE UNIT.  THE UNIT WAS OPENED AND A WASHER WAS FOUND LOOSE INSIDE.  THE WASHER WAS NOT A PART OF THE ASSEMBLY AND ITS 	ORIGIN WAS UNKNOWN.  THE WASHER WAS REMOVED AND THE UNIT WAS RETESTED, TESTED GOOD AND WAS RETURNED.				2	L	7	2 	4F			RT	A16WE   					 
2002101100111	20021011	00111		2002	10	11	2002FA0001145    	4	20020906	G	2562	4520130	BATTERY         	ARTEX       		BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					ELT	CRACKED         	B			AKGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	05	128JG				64155	E3332				IN COMPLETING 14 CFR ON THIS ELT, IT WAS NOTED THAT MOUNTING TRY HAS SOME KIND OF WHITE RESIDUE IN IT, INSPECTION OF THE	 ELT FOUND A CRACK IN THE BATTERY HALF OF THRU ELT CASE.  OPENED UP ELT AND INSPECTION OF BATTERY ASSEMBLY SOUND THAT ON	E OF THE CELLS HAD RUPTURED.				1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2002101100113	20021011	00113	CE  	2002	10	11	2002FA0001146    	1	20020919	G	5740	351150581	FITTING         			BEECH 	45    	A45         	1152006	CE  	CONT  	O470  	O470*       	17026	SO  					RT WING	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	421NM					G720				REMOVED WING LOWER ATTACH FITTING COVERS IN PREPARATION FOR EDDY-CURRENT INSPECTION IAW T34 REPORT.  BEFORE BEGINNING ED	DY-CURRENT INSPECTION NOTED DEEP TOOL MARKS/GOUGES IN RIGHT WING LOWER AFT BATHTUB FITTING INTERIOR.  ALSO NOTED SIMILAR	 MARKS IN LEFT WING LOWER FORWARD FITTING DAMAGE APPEARS TO HAVE BEEN CAUSED BY ROUGH, IMPROPER WING ATTACH BOLT REMOVAL	/ INSTALLATION TECHNIQUES DURING PREVIOUS MAINTENANCE.  NO FURTHER ACTION TAKEN.			1	L	7	1 	3O	3	O	 	5A3     	E273				 
2002101000012	20021010	00012	GL  	2002	10	10	2002FA0001147    	2	20020722	G	7250	23071311	SHAFT           			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ON VISUAL INSPECTION OF SHAFT,  FOUND EXCESSIVE PITTING ON INNER RACE AREA.   EXCESSIVE CORROSION ON INNER RACE SURFACE.	  PROTECTIVE GREASE WAS ON SURFACE OF INNER RACE.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002101000011	20021010	00011	SW  	2002	10	10	2002FA0001149    	1	20020809	G	6300	77416	BUMPER BLOCK    			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HIO360C1A   	41514	EA  					ENGINE	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	61426					0062	L3448236A			DURING A SCHEDULED INSPECTION, THE LOWER PULLEY DRIVESHAFT WAS FOUND TO HAVE AN ABNORMAL AMOUNT OF MOVEMANT. UPON REMOVI	NG THE SHAFT, THE CRANKSHAFT BUMPER BLOCK WAS FOUND TO BE MISSING. IT SHOULD BE NOTED THAT THIS PART IS NOT IN EITHER TH	E AIRFRAME OR THE ENGINE MANUFACTURERS PUBLICATIONS. THERE IS NO STEP TO INSTALL OR INSPECT FOR INSTALLATION OF THIS BUM	PER IN THE ENGINE INSTALLATION PROCEDURES.			1	G	7	1 	3O	3	O	O	4H12    	1E10				 
2002101000117	20021010	00117	CE  	2002	10	10	2002FA0001151    	1	20020927	G	2140	551130101	ELEMENT         			LEAR  	35    	31A         	5170531	CE  										HEATER	BLISTERED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	77PY					089				UPON DISASSEMBLY AND INSPECTION OF EMERGENCY POWER SUPPLY, FOUND THE HEATER BLANKET ELEMENT TO HAVE BECOME HEAT DAMAGED 	SEVERELY ENOUGH TO SEPERATE THE LAMINATION SURROUNDING THE CONDUCTIVE ELEMENT.					2	L	7	2 	4F			RT	A10CE   					 
2002101000134	20021010	00134	EA  	2002	10	10	2002FA0001152    	2	20020927	G	8530	72057	VALVE SEAT      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  					CYLINDER	MISREPAIRED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	571ER	129  				4496147	L74171A			DURING ROUTINE COMPRESSION TEST FOUND NR 3 CYL COMPRESSION LOW.  REMOVED CYLINDER AND FOUND THE INTAKE VALVE SEAT HAD BE	EN INSTALLED AND GROUND CROOKED AT THE FACTORY.  SEAT WAS REINSTALLED AND GROUND CORRECTLY AND CYL REINSTALLED ON ENGINE	.				1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002101100115	20021011	00115	SO  	2002	10	11	2002FA0001153    	2	20020822	G	8550	640926	DRIVE SHAFT     			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					OIL PUMP	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	8385C	1700 				347670134	233882H			RT ENGINE LOST OIL PRESSURE AFTER TAKEOFF DISASSEMBLY REVEALED BROKEN OIL PUMP DRIVE SHAFT/GEAR.  SHAFT IS THE WEAK LINK	.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002101000136	20021010	00136	EA  	2002	10	10	2002FA0001154    	2	20020927	G	8530	72057	VALVE SEAT      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	MISREPAIRED     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	575ER					4496151	L3873736A			DURING ROUTING COMPRESSION TEST FOUND NR 4 CYLINDER COMPRESSION LOW.  REMOVED CYLINDER AND FOUND THE INTAKE VALVE SEAT H	AD BEEN INSTALLED AND GROUND CROOKED AT THE FACTORY.  SEAT REINSTALLED AND GROUND CORRECTLY AND REINSTALLED ON THE ENGIN	E.				1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002101000137	20021010	00137	EU  	2002	10	10	2002FA0001155    	1	20020927	G	2497	6141H82	CIRCUIT BREAKER 			ISRAEL	1124  	1124        	4500102	EU  										AFT BAY	BURNED          	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	09	30GF	5050 				401				INVESTIGATION HAS REVEALED A FAILURE OF THE LT MAIN FUEL BOOST PUMP.  THE NATURE OF THE FAILURE HAS RESULTED IN CATASTRO	PHIC DAMAGE TO THE WIRING AND POWER DISTRIBUTION SYSTEMS.  IN REVIEWING THE ELECTRICAL DISTRIBUTION SYSTEM IT APPEARS TH	AT THE CIRCUIT PROTECTION DEVICES FAILED TO PROTECT THE SYSTEM.  HAVE UNCOVERED THAT THE PUMP WIRING TO THE AFT JUNCTION	 BOX IS BURNED BEYOND RECOGNITION AND PRELIMINARY CHECKS HAVE CONFIRMED EXTENSIVE DAMAGE TO THE LT CONTACTOR BOX.  WE SU	SPECT THAT THE LT MAIN BOOST PUMP FAILED AND THE REMOTE CIRCUIT BREAKER DID NOT OPEN CAUSING THE WIRES TO OVERHEAT TO TH	 JOINT THAT THE INSULATION MELTED OFF WHICH CAUSED EXPOSED WIRES TO BURN INTO THE WIRING TO THE LT ALTERNATE FUEL PUMP.	2	M	7	2 	4F			 	A2SW    					 
2002101000138	20021010	00138		2002	10	10	2002FA0001156    	4	20020930	G	6113	D7582	BULKHEAD        	MCAULY      		MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  	MCAULY	2A34C	2A34C*      	GL  	SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	101DX	42   	42   			290221	679463	992954		THE SPINNER BULKHEAD WAS FOUND CRACKED COMPLETELY AROUND THE CIRCUMFERENCE OF THE MOUNTING FLANGE.  THE TOTAL TIME ON TH	E SPINNER ASSEMBLY IS 315.5 HOURS.  THIS IS THE THIRD CRACKED BULKHEAD FOUND ON THIS AIRCRAFT.  THE TIME IN SERVICE OF T	HIS BULKHEAD IS 42.8 HOURS.  THE FIRST BULKHEAD WAS FOUND CRACKED (SEPARATED FROM PROP HUB) AT 104.6 HOURS TIS.  THE SEC	OND WAS FOUND CRACKED AT 168.1 HOURS TIS.  MCCAULEY SERVICE BULLETIN 237 WAS COMPLIED WITH AT THE FIRST REPLACEMENT.  SB	 237A WAS COMPLIED WITH AT THE SECOND REPLACEMENT.		1	L	7	1 	3O	3	O	RT	2A3     	E3SO	5	C	P3EA	 
2002101000139	20021010	00139	EA  	2002	10	10	2002FA0001157    	2	20020921	G	8550	76617	LINE            			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					ENG OIL	FAILED          	G				A				UNSCHED LANDING         				B	K	R	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	CR	CRUISE         	1			GL	11	6231U					2070	L510036			DURING FLT,SHORTLY AFTER DEPARTURE FROM LAF,  IN CRUISE AT 3,000 FT,   PILOT HEARD A POP FROM THE ENGINE. SMOKE FROM FRO	NT COWLING, AND IN THE COCKPIT. CONTACTED TOWER TO ADVISE OF SITUATION AND BEGAN 180 DEGREE TURN TO RETURN TO LAF. HEARD	 TWO MORE POPS FROM ENGINE AND BEGAN LOSING POWER.  COULD NOT MAINTAIN ALTITUDE. ADVISED TOWER OF PUTTING AIRCRAFT DOWN 	IN A FIELD. AIRCRAFT LANDED IN FIELD APPROXIMATELY 12 MILES NW OF LAF. NO DAMAGE TO AIRCRAFT DURING THE EMERGENCY LANDIN	G. INSPECTION OF THE AIRCRAFT REVEALED THE PROP GOVERNOR EXTERNAL OIL LINE FRACTURED AT THE B-NUT CAUSING LOSS OF OIL. T	HE NR  2 CYLINDER AFT PUSH ROD FAILED DUE TO LACK OF OIL AND CREATED A HOLE IN THE ENGINE CASE.	1	L	7	1 	3O	3	O	 	2A3     	E286				 
2002101100118	20021011	00118	SO  	2002	10	11	2002FA0001159    	2	20021002	G	7421	RHB32E	SPARK PLUG      			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					ENGINE	FOULED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	23	421G	125  				421C0664				ROUGH MAGNETO ON RT ENGINE DURING RUN UP.  PULLED SPARK PLUGS ON LT MAGNETO SIDE.  FOUND ONE SPARK PLUG SHORTED OUT (OUT	SIDE ELECTRODE TOUCHING CENTER ELECTRODE).  WHEN THE OUTER ELECTRODES WERE TOUCHED THEY WERE FOUND TO BE VERY LOOSE AND 	FLOATING.  SUSPECT THAT SPARK PLUG WAS MANUFACTURED POORLY.				1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2002101100119	20021011	00119	CE  	2002	10	11	2002FA0001160    	1	20020929	G	5610	5111604202	WINDSHIELD      			CESSNA	421   	421B        	2076014	CE  										COCKPIT	FAILED          	C				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	04	421DK					421B0825				DURING CRUISE FLIGHT NEAR SHR AT 25000 FT., RT WINDSHEILD SUSTAINED AN EXPLOSIVE DECOMPRESSION. PILOT PERFORMED EMERGENC	Y PROCEDURES AND LANDED WITHOUT FURTHER INCIDENT.					1	L	7	2 	3O			 	A7CE    					 
2002101100120	20021011	00120	CE  	2002	10	11	2002FA0001161    	1	20020905	G	2910	572700258	LINE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					HYD SYSTEM	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	30832	3750 				4410342				HYDRAULIC LINE FAILED DURING FLIGHT AND AIRCRAFT LOST ALL HYDRAULIC PRESSURE.  LANDING GEAR WAS EXTENDED BY EMERGENCY BL	OW DOWN BOTTLE.  LINE IS ON LEFT SIDE, AFT OF FIREWALL BETWEEN FILTER AND FLOW VALVE.  FAILURE APPEARS TO BE MANUFACTURE	R DEFECT.				1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2002101100001	20021011	00001	EA  	2002	10	11	2002FA0001162    	1	20020925	G	2420	756654A	ADG             			CNDAIR	CL600 	CL6002B16   	1900305	EA  										ELECTRICAL	FAILED          	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	371CL					5371				INSTALLED A LOANER AIR DRIVEN GENERATOR (ADG) DUE TO SURFACE CORROSION ON THE GENERATOR SHAFT AND NUT THAT WAS FOUND ON 	AN INSPECTION. COMPLETED AN IN-FLIGHT CHECK TO OPERATE THE ADG AND FOUND THE ADG INOPERATIVE AT THAT TIME.  RETURNED TO 	HANGAR AND REINSTALLED THE PREVIOUSLY REMOVED ADG.  TROUBLESHOOTING REVEALED THAT THE LOANER ADG HAD DAMAGED TWO OTHER C	OMPONENTS IN THE SYSTEM DURING THE OPERATIONAL CHECK.  THE ADG AUTO CONTROL UNIT AND THE ADG GENERATOR CONTROL UNIT.  IN	STALLED NEW PARTS AND THEN COMPLETED A SATISFACTORY IN FLIGHT OPERATIONAL CHECK OF THE ADG SYSTEM.		2	L	7	2 	4F			RT	A21EA   					 
2002101100002	20021011	00002	SO  	2002	10	11	2002FA0001163    	2	20021008	G	8530		CYLINDER HEAD   								CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	SEPARATED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		650  								ENGINE CYLINDER HEAD AND BARREL SEPERATED DURING ENGINE RUN.											3	O			E8CE				 
2002101100003	20021011	00003	SO  	2002	10	11	2002FA0001164    	2	20021008	G	8530		CYLINDER HEAD   								CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	SEPARATED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		650  								ENGINE CYLINDER HEAD AND BARREL SEPERATED.											3	O			E8CE				 
2002101100004	20021011	00004	CE  	2002	10	11	2002FA0001165    	1	20021009	G	3211	22411001	FITTING         			CESSNA	182   	TR182       	2072735	CE  										MLG	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	6584S	9500 				R18201692				MLG AXLE ATTACHMENT FITTING,  FOUND CRACKED AT TOP OUTBOARD EDGE.  CRACK IS VISIBLE WITHOUT ADDITIONAL AIDS.  CRACK ORIG	INATES AT THIN EDGE WHERE FITTING WAS MACHINED DURING MANUFACTURE.  CRACK IS ALSO IN ALIGNMENT WITH FORGING LINE.					1	H	7	1 	3O			 	3A13    					 
2002101100005	20021011	00005	GL  	2002	10	11	2002FA0001166    	1	20021001	G	3211	10209001	GROMMET         			CIRRUS	SR    	SR22        	2130001	GL  										MLG	DEFORMED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	25MV	124  				0095				DURING A SCHEDULED INSPECTION FOUND BOTH MLG LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. 	 HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. T	OTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE.				1	L	7	1 	3O			NT	A00009CH					 
2002101100006	20021011	00006	GL  	2002	10	11	2002FA0001167    	3	20021009	G	6114		HUB             	MCAULY      	3AF32C505B  	CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER	MAKING METAL    	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23	TZAMS		374  		841637	402C0517		841637		OIL WAS DETERMINED TO BE LEAKING FROM THE PACKING AROUND THE BLADE AND NOT FROM THE CRANKSHAFT SEAL.  PROPELLER WAS REMO	VED FROM ENGINE AND DISASSEMBLED.  HUB WAS CONFIRMED TO BE FILLED WITH ENGINE OIL.  UPON FURTHER EXAMINATION, AN EXCESSI	VE AMOUNT OF SCORING WAS FOUND ON THE PISTON ROD ASSEMBLY AND THE HUB AND THE PACKING WAS DAMAGED.  IN ADDITION, METAL S	HAVINGS WERE FOUND IN THE CYLINDER ASSEMBLY AND THE PISTON ASSEMBLY COULD NOT BE REMOVED FROM THE PISTON ROD ASSEMBLY. T	HIS IS THE SECOND PROPELLER FAILURE OF THIS KIND IN THE PAST YEAR.		1	L	7	2 	3O			 	A7CE    		5	C	P22EA	 
2002101100122	20021011	00122	SO  	2002	10	11	2002FA0001168    	2	20020813	G	8500		ENGINE          			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					NACELLE	MALFUNCTIONED   	G				A				UNSCHED LANDING         				E	M	J	VIBRATION/BUFFET          	OVER TEMP                 	WARNING INDICATION        	LD	LANDING        	1			SO	17	704TJ					15078858	23480A			AIRCRAFT LANDED ON THE ROADWAY BECAUSE PILOT STATED HE COULD NOT AMINTAIN ALTITUDE AT 1200 FT,   THE ENGINE STARTED BACK	FIRING AND SOUNDED LIKE IT WAS MISSING.  ALL OTHER INSTRUMENTS APPEARED NORMAL, AND THE WEATHER WAS CLEAR AND 85 DEGREES	.  THIS WAS NOT THE FIRST TIME FOR THIS AIRCRAFT.  OTHER PILOTS HAVE STATED THAT THEY HAVE HAD THE SAME PROBLEM.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002101100123	20021011	00123	CE  	2002	10	11	2002FA0001169    	1	20020904	G	3246	300257	WHEEL           			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A6       	52043	EA  					MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	3195Q	375  				LJ1595				FOUND WHEEL HALF CRACKED FROM BOLT HOLE CAUSING LEAK DOWN OF TIRE.  THERE WERE NO SIGNS OF OVER TORQUE OR EXCESSIVE WEAR	.  TT 375 HOURS.  CASTING OR MANUFACTURE DEFECT.  PART WAS SENT TO MFG FOR EVALUATION.					1	L	7	2 	3T	3	T	RT	3A20    	E4EA				 
2002101100124	20021011	00124	CE  	2002	10	11	2002FA0001170    	1	20020926	G	3211	504100112	BELLCRANK       			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT MLG WHEEL WEL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	340FS					340A0801				RIGHT MAIN LANDING GEAR COLLAPSED ON ROLLOUT AFTER TOUCHDOWN.  INITIAL INSPECTION REVEALED OUTBOARD MAIN LANDING GEAR RE	TRACTION LINK (PN 504100112) SEPARATED FROM RIGHT MAIN LANDING GEAR STRUT AT ITS TWO ATTACH POINTS.  BOTH BREAKS APPEAR 	TO BE INSTANTANEOUS AND UPPER STRUT ATTACH LUG AND BOLT WERE SHEARED.  NO OBVIOUS CAUSE FOR THE BREAKS WERE APPARENT.				1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2002101100125	20021011	00125	CE  	2002	10	11	2002FA0001171    	1	20020924	G	5320	3634031015	CHANNEL         			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					FUSELAGE	CRACKED         	B			YWBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	801NH	5697 				E2692	686008			DURING ROUTINE INSPECTION AFT RADIO (AVIONICS) SHELF ATTACH BRACKET WAS FOUND CRACKED AT AFT END IN BEND RADIUS.  BRACKE	T IS LOCATED ON RIGHT SIDE BETWEEN BS 179.00 TO 207.00.  VIBRATION AND TIME IN SERVICE IS PROBABLE CAUSE.  AVIONICS SHEL	F ASSEMBLY ALSO FOUND CRACKED IN BEND RADIUS.				1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2002101100126	20021011	00126	EA  	2002	10	11	2002FA0001173    	2	20021001	G	8500		ENGINE          			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360C1A    	41514	EA  					NACELLE	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	9878F					17280438	L2749551A			ENGINE SHUT DOWN IN FLIGHT.  ABLE TO RESTART ON GROUND RUNUP INDICATES NO PROBLEMS.  REMOVED FUEL SERVO FOR BACK/FLOW CH	ECK FOUND OIL IN SERVO NOT DETERMINED IF CAUSE OF SHUTDOWN.  FLOW DIVIDER OVERHAULED.  IGNITION SWITCH DISASSEMBLED/REPA	IRED.  FUEL VENT SYSTEM CHECKED, OK.  CAUSE OF SHUTDOWN UNKNOWN.  NOT ABLE TO DUPLICATE.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002101500004	20021015	00004	SO  	2002	10	15	2002FA0001174    	1	20020929	G	5711		SPAR            			LUSCOM	8     	8A          	8190104	SO  	CONT  	A65   	A65*        	17003	SO  					LT & RT WINGS	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1291B					5918				INTERGRANULAR CORROSION, FOUND IN THE FOLLOWING WING COMPONENTS DURING A REPAIR/REBUILD PROCESS.  LT AND RT MAIN SPAR BE	AMS, REAR, LEFT MAIN SPAR BEAM, FRONT.					1	H	7	1 	3O	3	O	 	A694    	E205				 
2002101500005	20021015	00005	CE  	2002	10	15	2002FA0001175    	1	20020820	G	1430	10161000013	RIVET           			BEECH 	200   	A200        	1152921	CE  										TRIM TAB	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	1554	10   				BC21				ELEVATOR TRIM TABS ON AIRCRAFT WERE INSPECTED FOR RIVETS.  FOUND LT ELEVATOR TRIM TAB THAT WAS INSTALLED 10 HOURS PRIOR,	 TO BE MISSING ALL RIVETS.  THE SKINS WERE BONDED BUT RIVETS WERE NEVER INSTALLED.  THE TRIM TAB HAD BEEN SITTING ON OUR	 SHELF FOR 2 YEARS BEFORE INSTALLATION.  THOUGH INSPECTION OF TRIM TABS BEFORE INSTALLATION TO VERIFY RIVET INSTALLATION	.			1	L	7	2 	4T			 	A24CE   					 
2002101500006	20021015	00006	SW  	2002	10	15	2002FA0001177    	1	20020407	G	3230	71461	LEG ASSY        			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360*       	41514	EA  					MLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	2693Z					26878				LEFT MAIN GEAR LEG BROKE AT ATTACHING CLAMP ON LANDING.  EVIDENCE OF CHAFING AT FORWARD LOWER SURFACE WHERE UNDETECTED F	LAW IS NOTED.  NO INJURIES TO PILOT, OUTBOARD RIB BENT, PROP STRIKE.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002101500007	20021015	00007	WP  	2002	10	15	2002FA0001179    	1	20020717	G	6420	369D2172121	BEARING         			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	LOOSE           	B			EOOR	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AL	03	CGLNQ					2006620				AIRCRAFT WAS EXPERIENCING INCREASED TAIL ROTOR VIBRATIONS IN THE TAIL ROTOR FORK, UPON REMOVAL,  ONE BEARING POPPED OUT.	  IT APPEARS THAT IT HAD ALREADY BEEN LOOSE AND ROTATING WITHIN THE FORK.					1	G	7	1 	3U			 	H3WE    					 
2002101500001	20021015	00001	SW  	2002	10	15	2002FA0001180    	1	20021012	G	7603	660017003	CLAMP           			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  					THROTTLE BODY	WORN            	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	19	101DX	320  				290221	679463			OWNER COMPLAINED THAT HE WAS UNABLE TO CLOSE THROTTLE TO LAND. THE MIXTURE HAD TO BE MOVED TO CUT-OFF TO LAND.   INVESTI	GATION REVEALED THAT THE THROTTLE CABLE HOUSING WAS MOVING IN THE CLAMP LOCATED AT THE THROTTLE BODY PREVENTING THE THRO	TTLE FROM CLOSING ALL THE WAY.  THE CLAMP HALVES WERE WORN INTERNALLY TO THE POINT THAT THEY NO LONGER WERE TIGHT.   THE	 INTERNAL RIDGE IN THE CLAMP HALVES THAT CONTACTS A GROOVE IN THE THROTTLE CABLE HOUSING WAS WORN AWAY.  THE WEAR APPEAR	S TO HAVE BEEN CAUSED BY VIBRATION.  THE CLAMP IS MADE OF ALUMINUM.  IT WOULD SEEM THAT A HARDER MATERIAL WOULD BE APPRO	PRIATE.   AT THE SAME TIME THE MIXTURE CABLE CLAMP WAS FOUND WORN AND CLOSE TO FAILURE.  THIS IS THE SAME CLAMP USED ON 	1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2002101500002	20021015	00002	CE  	2002	10	15	2002FA0001181    	1	20021013	G	3252	66082788	COMPUTER        			LEAR  	35    	35A         	5170602	CE  										NLG STEERING	MALFUNCTIONED   	D				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			WP	28	10AH					657				NOSE WHEEL STEERING WILL NOT ARM.  FOUND NO OUTPUT VOLTAGE ON P224 PIN A.  1.0 VAC REQUIRED FROM THIS PIN.						2	L	7	2 	4F			 	A10CE   					 
2002101500003	20021015	00003		2002	10	15	2002FA0001183    	4	20021014	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	789EP	82   	34   			172S8135				FOUND AFT PROPELLER SPINNER BULKHEAD CRACKED AT ONE FLANGE AT PROPELLER BLADE CUT OUT.  EDGE WITH NUTPLATE AND SCREW STI	LL ATTACHED TO PROPELLER SPINNER. CESSNA SERVICE BULLETIN SB02-61-01 WAS ACCOMPLISHED 34.0 HOURS PREVIOUSLY AND THE AFT 	SPINNER BULKHEAD REPLACED AT 82.2 HOURS WITH. THIS IS AN ONGOING PROBLEM AND HAS NOT BEEN RESOLVED WITH THE NEW -11 BULK	HEAD NOR CESSNA SERVICE BULLETIN SB02-61-01.			1	H	7	1 	3O			NT	3A12    					 
2002101500008	20021015	00008	SO  	2002	10	15	2002FA0001184    	2	20021014	G	8550	626739	COLLAR          								CONT  	O520  	IO520D      	17032	SO  					ENGINE	DISTORTED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07							566793			IN ASSEMBLING A NEW STANDARD GOVERNOR OIL TRANSFER COLLAR TO THE CRANKSHAFT IT WAS FOUND TO BIND ON THE JOURNAL.  PRIOR 	TO DIASSEMBLING THE COLLAR HALVES THE INSIDE DIAMETER WAS NOTED TO BE SMOOTH AND COLLAR TO JOURNAL CLEARANCE WITHIN NEW 	LIMITS.  ONCE THE COLLAR HAD BEEN DISASSEMBLED AND REASSEMBLED A STEP OF APPROXIMATELY .001 INCH WAS FOUND AT THE PARTIN	G SURFACES. INSTALLING THE COLLAR ON THE CRANKSHAFT AND TORQUING IT IN PLACE CAUSED IT TO BIND IN AN INTERFERENCE FIT. I	T APPEARS THE TWO HALVES ARE UNDER SOME TORSIONAL STRESS WHICH IS RELIEVED UPON TAKING THEM APART. THIS IS NOW THE FOURT	H CONSECUTIVE COLLAR ORDERED FROM OUR AVIALL DISTRIBUTOR TO EXHIBIT THESE CHARACTERISTICS.  CALLS HAVE BEEN MADE TO TELE						3	O			E5CE				 
2002102200011	20021022	00011	CE  	2002	10	22	2002FA0001186    	1	20021008	G	2915	HE151854SN1	PRESSURE SWITCH 			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					NR 2 HYD SYSTEM	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	11	1630	428  				258557				HYD FLUID SQUIRTING FROM UPPER PART OF PRESSURE SWITCH.						2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002102200012	20021022	00012	EA  	2002	10	22	2002FA0001187    	2	20020923	G	7414	LW15416	ADAPTER         			CESSNA	150   	150H        	2071818	CE  	LYC   	O360  	O360A4A     	41514	EA  					MAGNETO	MISSING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	22159	392  				15068106	L2554236A			PULLED THE MAGNETOS FOR INSPECTION, AND FOUND THAT THE RT MAGNETO DRIVE ADAPTER HAS SOME DAMAGED BEARINGS.  PULLED THE D	RIVE ADAPTER, AND FOUND THAT PIECES OF THE BEARING CAGE WERE MISSING, AND THE BEARINGS WEREN`T SPACED PROPERLY.  PULLED 	THE OIL FILTER, SCREEN, AND OIL SUMP IAW, AND FOUND 6 PIECES OF STEEL.  REASSEMBLED THE ENGINE, AND RETURNED TO SERVICE.	  INFORMATION FROM THE MAGNETO DRIVE ADAPTER ASSEMBLY WERE AS FOLLOWS.			1	H	7	1 	3O	3	O	 	3A19    	E286				 
2002102200013	20021022	00013	EA  	2002	10	22	2002FA0001188    	2	20020823	G	8500	LW13885M06	BEARING         								LYC   	O540  	TIO540*     	41532	EA  					NR 2	DELAMINATED     	B			VD3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01		11   					L2177248A			BEARING FAILURE OF FRONT MAIN BEARING IN THE NR 2 POSITION.  FLAKING, BENT, AND DELAMINATED OVER ENTIRE WIDTH OF NR 2 PO	SITION.  MOST OF BEARING SURFACE STILL CONNECTED TO SHELL.  DELAMINATION OF BEARING CRANKSHAFT AND CRANKCASE NOT SERVICE	ABLE AFTER DAMAGE.  C/A: CHANGE BACK TO TRIMETAL BEARINGS FROM THESE ALUMINUM/STEEL BACKED TYPE.									3	O			E14EA				 
2002102200014	20021022	00014	GL  	2002	10	22	2002FA0001189    	3	20020925	G	6114	83410	COLLAR          			BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  	HARTZL	HCA2V	HCA2V*      	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	34TT					D4737				GUIDE COLLAR CRACKED DUE TO VIBRATION FROM PROPELLER.  BOTH BLADES SLIPPED IN CLAMP CREATING A SPLIT IN ANGLES.  THIS CA	USED VIBRATION.					1	L	7	1 	3O	3	O	 	A777    	E267	5	C	P24EA	 
2002102200015	20021022	00015	GL  	2002	10	22	2002FA0001190    	3	20020925	G	6114	B4460	PIN             			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BB     	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	PROPELLER	BROKEN          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	2061A		750  			E1425				ACTUATING PIN BROKE AT BASE OF THREADS DUE TO IMPROPERLY DRILLED HOLE TO ACCEPT PIN.  SHALLOW DEPTH NOT TAPPED TO THE BO	TTOM OF THE HOLE.					1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2002102200016	20021022	00016	EA  	2002	10	22	2002FA0001191    	2	20021003	G	8520	61156	LOCK            			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					CRANKSHAFT	OVERTORQUED     	C			KKCS	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07	837KS					M2076	L3022436A			LOCKPLATE FOR CRANKSHAFT GEAR RETAINING BOLT NOT SUFFICIENTLY BENT ALLOWING CRANKSHAFT GEAR BOLT TO LOOSEN.  CRANKSHAFT 	GEAR DOWEL PIN SHEARED.  RECOMMENDATION TO PREVENT RECURRENCE:  CRANKSHAFT GEAR BOLT TORQUE SHOULD BE VERIFIED AT 204IN/	LBS AND LOCKPLATE INSPECTED TO ENSURE PROPER LOCKING OF THE PLATE AGAINST THE BOLT HEAD.				1	L	7	1 	3O	3	O	 	A1CE    	E286				 
2002102200017	20021022	00017	SW  	2002	10	22	2002FA0001192    	1	20021003	G	3710	211CC	PUMP            			GULSTM	112   	112TC       	7630306	SW  	LYC   	O360  	IO360A1A    	41514	EA  					VACUUM SYS	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	4613W					13103	L22109A			VACUUM PUMP FAILED IN NIGHT IFR CONDITIONS.						1	L	7	1 	3O	3	O	 	A12SO   	1E10				 
2002102200018	20021022	00018	EA  	2002	10	22	2002FA0001193    	2	20021001	G	7414	ES10682054	DISTRIBUTOR BLK 	BENDIX      		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					MAGNETO	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03					4081110					DISTRIBUTOR GEAR TOOTH DAMAGE.  SEVERAL GEAR TEETH BROKEN ON BOTH GEARS.  NEW GEARS WERE FOUND TO BIND ON ROTOR PINION G	EAR EVERY 90 DEGREES.  NO ROTOR TO HOUSING INTERFERENCE INDICATED.  VISUAL INSPECTION REVEALED NO CRACKS OTHER THAN ACCE	PTABLE STRESS CRACK AT BEARING BORE IN BLOCK.  GEAR AXLE BUSHINGS APPEAR SECURE, MAY BE MISALIGNED FROM WARPAGE OR MANUF	ACTURE DEFECT.  SCREW THREAD INSERTS FOR CONTACT ASSY.  PULL OUT BEFORE REACHING MINIMUM TORQUE.  BLOCK HAS A 94 DATE CO	DE.  REPLACED BLOCK, MAGNETO FUNCTIONS PROPERLY.		1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2002102100001	20021021	00001	CE  	2002	10	21	2002FA0001194    	1	20020920	G	1430	8178610	BOLT            			BEECH 	100   	B100        	1152919	CE  										WING	CRACKED         	W			D7FF	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		2716 				BE15				LEFT AFT UPPER WINGBOLT CRACK FOUND WHERE SHAFT CONNECTS TO BOLT HEAD.  WINGBOLT INSPECTION CARRIED OUT IAW AD.  BOLT WA	S INSPECTED  1 YEAR/ 324 HOURS, PRIOR.  BOLT, TT 2716.5 HOURS, 2544 A/C CYCLES.  INSTALLED APRIL 1991.					1	L	7	2 	4T			 	A14CE   					 
2002102200019	20021022	00019	NE  	2002	10	22	2002FA0001195    	2	20020819	G	7250		RIVET           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					TURBINE WHEEL	ERODED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	457CW	2505 				RK57	PCE100294			HIGH TURBINE BLADE RETAINING RIVETS AND COLLARS APPEAR TO BE SUFFERING EROSION, CAUSING RIVET TAILS TO FALL BELOW THE .0	50 INCH PROTRUSION AS OUTLINED IN MFG MM.  IF LEFT IN SERVICE THIS SITUATION COULD CAUSE THE HIGH TURBINE BLADES TO SHIF	T AND/OR FAIL, CAUSING ENGINE FAILURE.  ALL 71 RIVETS  AND 71 COLLARS ARE BEING REPLACED WITH NEW.				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2002102300063	20021023	00063	SO  	2002	10	23	2002FA0001196    	2	20021015	G	8530	655469A7	CYLINDER        								CONT  	O520  	IO520D      	17032	SO  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07							282740R			A CRACKED CYLINDER HEAD FIN WAS DISCOVERED ON NR 1 CYLINDER FOLLOWING THE ACCEPTANCE RUN AFTER THE ENGINE HAD BEEN OVERH	AULED.  AN ATTEMPT TO DRESS IT OUT INDICATED THAT THE CRACK EXTENDED ON TO THE BASE OF THE FIN AND POSSIBLY CYLINDER HEA	D.  CYLINDER WAS REMOVED AND REPLACED UNDER FACTORY WARRANTY.									3	O			E5CE				 
2002102200020	20021022	00020	CE  	2002	10	22	2002FA0001197    	1	20020913	G	2752		SHAFT           			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A6       	52043	EA  					FLAP ACTUATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	394B					LJ1553				DURING A ROUTINE PHASE 1 AND 2 INSPECTION ON THIS AIRCRAFT,  LUBRICANT WAS FOUND ACCUMULATING AT ACTUATOR HOUSING.  FURT	HER INSPECTION REVEALED A CRACK IN THE CHROMED SHAFT RUNNING PARALLEL WITH THE SHAFT STARTING AT THE ROD-END.  THIS CRAC	K WAS APPROXIMATELY 2.75 INCHES IN LENGTH.  THE ACTUATOR WAS REPLACED WITH A NEW ASSEMBLY.  NO RECOMMENDATIONS CAN BE MA	DE TO PREVENT THIS OCCURANCE.			1	L	7	2 	3T	3	T	RT	3A20    	E4EA				 
2002102300064	20021023	00064	EU  	2002	10	23	2002FA0001198    	1	20021017	G	2520	T700A251000710	SEAT BELT       			SOCATA	TBM   	TBM700      	8682000	EU  										CABIN	FAILED          	B			BNGR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	19	700SP	1333 				98				SEAT BELT BUCKLE CAME APART WITH A SIMPLE JERK TEST.  WITH A STEADY PULL  ON THE SEAT BELTS THE BELTS HOLD OK. ALL BELTS	 IN THE AIRCRAFT DID THE SAME THING.  SEAT BELTS ARE MANUFACTURED BY ANJOU AERONAUTIQUE,  THERE IS A SOCATA SERVICE LETT	ER SL70-027 THAT INFORMS USERS ABOUT POSSIBILITY OF REPLACEMENTS AND MENTIONS FRENCH AD 2002-104 & 2002-105, BUT DOES NO	T INDICATE THE SERIOUSNESS OF THE PROBLEM.  THE SUBMITTER BELIEVES THAT THIS IS A SERIOUS SAFETY ISSUE AS THEY HAVE FOUN	D ALL LIKE BELTS IN ANOTHER AIRCRAFT WILL FAIL TO HOLD IN THE SAME MANOR AND RECOMMENDS IMMEDIATE INSPECTION AND REPLACE	MENT OF THE EFFECTED SEAT BELTS. THIS ORGINALY SUBMITED TO GL-19 BY PAT BEATY @ IMAGE AIR, INC. (BNGR)	1	L	7	1 	3T			RT	A60EU   					 
2002102300060	20021023	00060	CE  	2002	10	23	2002FA0001199    	1	20021022	G	2842	S33311	TRANSMITTER     			CESSNA	172   	172S        	2072439	CE  										RT FUEL TANK	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	03	789EP	1893 				172S8135				RT FUEL QUANTITY WENT TO "0" IN FLIGHT, AIRCRAFT RETURNED TO HOME STATION.  MAINTENANCE FOUND FUEL QUANTITY TRANSMITTER 	FLOAT SEPERATED FROM THE TRANSMITTER.  THE FLOAT ATTACH ARM BROKE OUTBOARD OF THE FLOAT WHERE IT WAS CRIMPED AND THE END	 PIECE, WASHER AND FLOAT SEPERATED. THE PIECES WERE FOUND INSIDE THE FUEL CELL. REPLACED THE TRANSMITTER, RESEALED THE T	ANK ACCESS COVER, RESERVICED, RECALIBRATED AND LEAK CHECKED SATISFACTORY.			1	H	7	1 	3O			NT	3A12    					 
2002102400002	20021024	00002	CE  	2002	10	24	2002FA0001204    	1	20021023	G	3234	8857K44	SELECTOR SWITCH 			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					MLG	MISINSTALLED    	D				O				OTHER                   				W			INADEQUATE Q C            			LD	LANDING        	1			CE	07	8971M	2319 				177RG0371				PILOT INEVERTANTLY BUMPED MLG SWITCH ON SHORT FINAL WHILE MOVING THE TRIM WHEEL, CAUSING A GEAR-UP LANDING. THE SAFETY F	AILED TO WORK ON MLG SWITCH. UPON INVESTIGATION FOUND THAT THE SWITCH KNOB WHEN SCREWED COMPLETLY ONTO SWITCH CAUSED THE	 SPRING LOADED SAFETY TO COME OFF THE SWITCH. THIS CAUSED THE SAFETY NOT TO WORK AND MADE IT EASY TO MOVE THE SWITCH WIT	HOUT PULLING OUT ON THE KNOB TO MOVE SWITCH INTO THE UP POSITION OR DOWN POSITION. INSTALLED A NEW SWITCH AND KNOB AND C	HECKED THE OPERATION AND WAS FOUND TO WORK PROPERLY.		1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2002102500006	20021025	00006	EA  	2002	10	25	2002FA0001205    	2	20021017	G	8520	05K19987	BOLT            			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					CRANKSHAFT	DEFECTIVE       	B			DPOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07	9562D					18280239				FINAL TORQUE OF CRANKSHAFT BOLT COULD NOT BE REACHED, AFTER REMOVAL OF BOLT, IT WAS FOUND TO BE DEFFECTIVE, AND TAPPERED	 TOWARDS THE CENTER OF THE SHANK.					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2002102500007	20021025	00007		2002	10	25	2002FA0001206    	4	20021009	G	2561	KD9P0101	LIFE VEST       																		FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE PRESERVER FAILED, MFG RECOMMEDNED CELL PRESSURE TEST IAW MM. DOM JANUARY 1983																			 
2002102500008	20021025	00008		2002	10	25	2002FA0001208    	4	20021016	G	3452	411230027	TRANSISTOR      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200*       	17020	SO  					TRANSPONDER	UNAPPROVED PART 	B			BIER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	19255					15074278				TRANSPONDER FAILURE:  IDENT PULSE PRESENT AND REPLY LAMP LIT WHEN UNIT HOT.  (NOT COMMANDED)  FOUND Q22 AND ASSORTED CIR	CUIT VERY TEMPERATURE SENSITIVE.  REPLACED COMPONENTS AND FOUND Q22 NOT STANDARD PART.  PART INSTALLED AN ECG TPE 123.  	PART REPLACED WITH ARC PART RENDERING UNIT SERVICEABLE.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002102500009	20021025	00009	SW  	2002	10	25	2002FA0001209    	1	20020909	G	2730	740009007	UNIVERSAL JOINT 			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360*    	17025	SO  					PITCH TRIM	INOPERATIVE     	B			MGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	231GE					250233				DURING INVESTIGATION OF AUTO PILOT PITCH OSOLATIONS.  FOUND UNIVERSAL JOINT AT PITCH TRIM JACK SCREW SQUARE DRIVE ISSING	 ONE OF THE FOUR STAKED IN ROLL PINS.					1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2002102500001	20021025	00001	SO  	2002	10	25	2002FA0001210    	1	20021024	G	7160	950618283	SPACER          			PIPER 	PA44  	PA44180     	7104402	SO  										CARB HEAT	MISSING         	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	28	571ER	160  				4496147				DURING LANDING ROLLOUT THE RIGHT ENGINE QUIT.  ENGINE WAS RESTARTED AND RUNUP NORMAL EXCEPT FOR CARB HEAT OPERATION.  MA	INTENANCE FOUND BOTH LT & RT CARB HEAT CONTROLS NOT RIGGED RIGHT.  MECHANIC OPENED CONSOLE AND FOUND THE SPACERS FOR BOT	H CARB HEAT LEVERS HAD NOT BEEN INSTALLED AT THE FACTORY AND THIS ALLOWED THE CARB HEAT CONTROL LEVERS  TO HANG UP ON TH	E CONSOLE FRAME			1	L	7	2 	3O			 	A19S0   					 
2002102500002	20021025	00002	SO  	2002	10	25	2002FA0001211    	1	20021024	G	3233		SEAL            			PIPER 	PA44  	PA44180     	7104402	SO  										MLG ACTUATOR	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	28	574ER	49   				4496150				RIGHT MAIN GEAR ACTUATOR LEAKING AT SHAFT SEAL.  ACTUATOR REPLACED. ACTUATOR PREVIOUSLY REPLACED AT 32.3 HOURS AFTT.  TH	IS IS AN ONGOING PROBLEM WITH PIPER ACTUATOR. SO FAR ON A FLEET OF ONLY 7 PA-44 AIRCRAFT WE HAVE REPLACED 18 ACTUATORS S	INCE AUGUST 2002.  PIPER FACTORY HAS BEEN AWARE OF THE PROBLEM AND ARE WORKING WITH  ON A NEW SEAL.  WE FIND THE ACTUATO	R SHAFTS HAVE BEEN LEFT WITH VERY SHARP EDGES ON THE OUTER END WHERE IT IS MACHINED.  WE HAVE ALSO FOUND THE WITNESS HOL	E FOR THE ROD END NOT CHAMFERED TO GET RID OF BURRS.  THESE ARE TEARING UP THE SEALS.  IT IS ALSO NOTED THAT THE SEALS S	EEM TO BE VERY SOFT. AN ALTERNATE SEAL (O-RING) IS LISTED IN THE PARTS CATALOG.	1	L	7	2 	3O			 	A19S0   					 
2002102500003	20021025	00003	EU  	2002	10	25	2002FA0001212    	1	20021024	G	2842	522304010	TRANSMITTER     			AVIONS	R2160 	R2160       	0960101	EU  										FUEL QTY	DAMAGED         	G				A				UNSCHED LANDING         				N			FALSE WARNING             			AB	AEROBATIC      	1			WP	05	216RN	7011 				NR200				FUEL QUANTITY TRANSMITTER, HAS INTERNAL DAMAGE CAUSING THE RHEOSTAT TO STICK.  CONDITION ALLOWED THE TRANSMITTER TO SEND	 AN ERRONEOUS SIGNAL TO THE FUEL QUANTITY INDICATOR.					1	L	7	1 	3O			RT	A48EU   					 
2002102500004	20021025	00004		2002	10	25	2002FA0001213    	4	20021024	G	2562	4520130	BATTERY PACK    	ARTEX       	ELT1104     															ELT	CRACKED         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19					61297					ON ANNUAL INSPECTION DISCOVERS BATTERY PACK ON ELT1104 CRACKED AND BATTERY ACID LEAK.  FOUND ON TWO SEPARATE UNITS, SAME	 LOCATION AND SAME FAILURE.  BATTERY PACKS PURCHASED IN OCT-2000 DUE FOR REPLACEMENT NEXT MONTH.  DAMAGE WAS NOT PRESENT	 AT PREVIOUS ANNUAL IN OCT-2001.																	 
2002102800004	20021028	00004	GL  	2002	10	28	2002FA0001214    	3	20021010	G	6114	D5044	HUB             	MCAULY      		CESSNA	177   	177         	2073704	CE  						MCAULY	2D34C	B2D34C207   	GL  	PROPELLER	CORRODED        	C			L2PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13								742422		RETIRED HUB DUE TO SURFACE CORROSION ON EXTERIOR, HUB NOT PAINTED.						1	H	7	1 	3O			NT	A13CE   		5	C	P7EA	 
2002102800005	20021028	00005	GL  	2002	10	28	2002FA0001215    	3	20020919	G	6114	698500	HUB             			CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520*    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	MISMANUFACTURED 	B			L2PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	6221Q					401A0021		756476		BLADE RETENTION NUT TO HUB LOCK PLUG HOLE MACHINED IN WRONG LOCATION AT LAST OVERHAUL OR LAST ASSEMBLY.  HUB RETIRED FRO	M SERVICE.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002102800006	20021028	00006	GL  	2002	10	28	2002FA0001216    	3	20020919	G	6114	D5892C87	HUB             			CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	MISMANUFACTURED 	B			L2PR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	13	6221Q					401A0021		791238		BLADE FERRULE ACTUATING PIN HOLE DRILLED IN WRONG LOCATION IAW MM.  (MIN. EDGE DISTANCE BETWEEN HOLE 1 INCH)  HUB RETIRE	D FROM SERVICE.					1	L	7	2 	3O			 	A7CE    		5	C	P22EA	 
2002102800007	20021028	00007	GL  	2002	10	28	2002FA0001217    	3	20020919	G	6114	D5892C87	HUB             			CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	MISMANUFACTURED 	B			L2PR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	13	6221Q					401A0021		791238		BLADE RETENTION NUT TO HUB LOCK PLUG HOLE DRILLED TO IMPROPER DEPTH.  HUB RETIRED FROM SERVICE.						1	L	7	2 	3O			 	A7CE    		5	C	P22EA	 
2002102800008	20021028	00008	CE  	2002	10	28	2002FA0001218    	1	20021016	G	2435	300SGL129Q	STARTER GEN     			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					RIGHT	INOPERATIVE     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	19	400LX	950  				5600453				GENERATOR DROPPED OFF LINE DURING FLIGHT AND WAS ABLE TO BE RESET.  AFTER LOADS WERE SHED.  AFTER LANDING AND SHUTDOWN S	TARTER WOULD NOT ROTATE FOR NEXT START.  REPLACED RIGHT STARTER GENERATOR.  CHECKED OK.					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2002102800009	20021028	00009	CE  	2002	10	28	2002FA0001219    	1	20021011	G	5711	17107036	SPAR            			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	2692V	3040 				177RG0659				OBSERVED THE CARRY THRU SPAR CORROSION WHEN LOOKING AT THE AIRCRAFT.  THIS ITEM HAD SURFACE CORROSION THAT HAS BLISTERIN	G THAT COULD BE PICKED AT AND MOST OF THE SURFACE AREA HAD WHITE DUSTING AND DISCOLORATION INDICATING CORROSION THAT REQ	UIRES TREATMENT.  CAUSE IS PROBABLY FROM EXPOSURE TO OUTSIDE STORAGE.				1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2002102800010	20021028	00010	EA  	2002	10	28	2002FA0001220    	2	20020809	G	8530		BOLT            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					NR 3 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32481	722  				28R7535061				NR 3 CYLINDER CONNECTING ROD BOLT BROKE.  ENGINE WAS DESTROYED.  PROBABLE CAUSE, POSSIBLE OVER-TORQUED.						1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002102800011	20021028	00011	SW  	2002	10	28	2002FA0001222    	1	20020930	G	7722	580505	INDICATOR       			GULSTM	690TP 	690B        	7630516	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					EGT	DEFECTIVE       	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	690HT	214  				11467				NON-LINEAR ERROR GAGE READS COOLER THAN INPUT 5 DEGREE AT 400, 6 DEGREE C 500, 7 DEGREES C 600 AS HIGH AS 10 DEGREE AT T	IMES ZERO ERROR AT 200 DEGREE.  DEFECT FOUND DURING CALIBRATION OF EGT DUE TO TEMP SPLITS.					1	H	7	2 	3T	3	T	 	2A4     	E2WE				 
2002103000220	20021030	00220		2002	10	30	2002FA0001223    	4	20021008	G	2210	SVO8513	SERVO           			ISRAEL	GALAXY	GALAXY      	4500307	EU  										AUTOPILOT	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	25	83EJ	344  				009				SERVO CAUSED AUTOPILOT MISTRIM CONDITION AND EVENTUALLY DID NOT PERMIT AUTOPILOT TO ENGAGE.						2	L	7	2 	4F			RT	A53NM   					 
2002103000222	20021030	00222		2002	10	30	2002FA0001224    	4	20021009	G	6122		SETSCREW        			RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  	MUHBR	MTV	MTV9*       	EU  	PROP GOVERNOR	BACKED OUT      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	162FC					135	L2790648A	01088		PROPELLER GOVERNOR SET SCREW INSIDE CASE HALVES, BACKED OUT CAUSING A CHAIN REACTION OF ENGINE DAMAGE.  ALL MAJOR ENGINE	 COMPONENTS BROKEN (NON-REPAIRABLE), RESULTING IN AN ENGINE FAILURE AND A FORCED LANDING.					1	M	7	1 	3O	3	O	NC	EA67U   	1E4	5	C	P24NE	 
2002103000223	20021030	00223	SO  	2002	10	30	2002FA0001225    	2	20021012	G	7414	6320	MAGNETO         			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					ENGINE	INOPERATIVE     	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CE	07	5034U	173  				3449200	322096			WHILE TRAINING, A/C SIMULATED ZERO THRUST SINGLE ENGINE APPROACH.  WHEN POWER WAS REAPPLIED, ENGINE WAS FOUND DEAD AND W	OULD NOT RESPOND TO ANY INPUTS FOUND IN EMERGENCY PROCEDURES CHECKLIST.  A SINGLE ENGINE LANDING WAS MADE WITHOUT INCIDE	NT.  FOUND BOTH MAGNETOS FAILED FROM SEVERE INTERNAL CORROSION AND BOTH COILS WERE SHORTED AND BURNED THROUGH IN THE SAM	E LOCATION.  REMOVED AND INSP BOTH MAGS ON THE OTHER ENG AND FOUND THE LEFT MAG WITH SEVERE CORROSION AND PRESSURIZED AN	D FILTERS APPEARED IN GOOD CONDITION.  THESE MAGS HAVE VERY SMALL VENT HOLES THAT WERE ALL PLUGGED.  THE MAG THAT WAS IN	 GREAT SHAPE HAD A DISTORTED HSG SEAL THAT OBVIOUSLY ALLOWED THE NEEDED VENTILATION THAT THE OTHER MAGS DID NOT GET.	1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002103000224	20021030	00224	CE  	2002	10	30	2002FA0001226    	1	20021002	G	8011	C12ST1	STARTER         			CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE	INOPERATIVE     	B			DD2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5711B					33711				STARTER DOES NOT ALLOW THE STARTER ADAPTER TO DISENGAGE WHEN THE ENGINE STARTS.  THE RESULT IS EXCESSIVE HEAT AND WEAR W	HICH RAPIDLY DESTROYS THE EFFECTIVENESS OF THE ADAPTER.  WITHIN 30-60 HOURS THE ADAPTER MUST BE REPLACED.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002103000229	20021030	00229	SO  	2002	10	30	2002FA0001227    	1	20021022	G	5712	356171	RIB             			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	515MS	148  				2842157				DURING INSPECTION NOTED CRACK AROUND STIFFENER BEAD.  CRACK APPEARED TO BE PRESENT AT MFG.  CONTACT WITH MFG MADE AND A 	REPAIR SCHEME DONE IAW SB.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002103000230	20021030	00230	SO  	2002	10	30	2002FA0001229    	1	20021015	G	2820	98044072	LINE            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					FUEL SYSTEM	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	21411	4150 				287990044				FUEL LINE CORRODED UNDER CUSHION CLAMP TO A POINT OF LEAKING INSIDE CABIN.  OTHER AREAS OK.  SUSPECT REPEATED EXPOSURE T	O MOISTURE AROUND DOOR OPENING AND CARPET AND INSULATION CONTRIBUTED TO CONDITION.  THE SEVERITY OF THE CORROSION COULD 	NOT BE SEEN UNTIL CLAMP WAS REMOVED.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002103000232	20021030	00232		2002	10	30	2002FA0001230    	4	20021010	G	2561	AV8AS2100	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOATATION DEVICE FAILED, MFG RECOMMENDED CELL PRESSURE TEST.																			 
2002103000214	20021030	00214	CE  	2002	10	30	2002FA0001231    	1	20021025	G	5210		LINE            			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE7314R    	01518	WP  					DOOR SEAL	CHAFED          	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	23		3525 	2462 			7046				PILOT CLOSED MAIN CABIN DOOR.  UPON LOCKING DOOR CREW HEARD HISSING NOISE FROM DOOR AND DOOR SEAL WOULD NOT INFLATE.  IN	SPECTION BY MAINTENANCE DISCOVERED LINE HAD BEEN CHAFED THROUGH BY A FLIGHT CONTROL CABLE.  LINE IS FOR MAIN ENTRANCE DO	OR SEAL INFLATION.  HOWEVER OPENING AND CLOSING OF DOOR STILL PUSHES THE LINE IN AND OUT ALLOWING IT TO CHAFED. THIS ARE	A IS INSPECTED EVERY PHASE 5 WHICH IS 1200 HOURS OR 36 MONTHS WHICH EVER OCCURS FIRST.  SUGGEST THIS AREA BE INSPECTED D	URING ONE THE PHASE ONE THROUGH FOURS.		2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2002103000215	20021030	00215		2002	10	30	2002FA0001232    	4	20021028	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										PROP SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	949SP	1756 				172S8145				DURING PHASE 1 INSPECTION, MAINTENANCE FOUND AFT PROPELLER SPINNER BULKHEAD CRACKED AT ONE FLANGE BY THE PROPELLER BLADE	 CUT OUT ON ONE SIDE.  REPLACED PROPELLER AFT SPINNER BULKHEAD & REINSTALLED PROPELLER.					1	H	7	1 	3O			NT	3A12    					 
2002103000216	20021030	00216	EU  	2002	10	30	2002FA0001233    	1	20021028	G	7910		VALVE           			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					OIL DRAIN	ERODED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	242MC					0671	L2624051A			OIL DRAIN VALVE WAS REMOVED BECAUSE OF LEAK, UPON REMOVAL IT WAS DISCOVERED THAT SMALL NUT HOLDING SLUDGE VALVE ASSY TOG	ETHER WAS WORE TO MIN AMOUNT AND MISSING ONE HALF, IF NUT HAD COME OFF VALVE ASSY WOULD OPEN CAUSING ENGINE OIL TO COMPL	ETLY DRAIN.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002103000217	20021030	00217	CE  	2002	10	30	2002FA0001234    	1	20021028	G	2720	4555400001V3800	RUDDER          			LEAR  	45    	45LEAR      	5170805	CE  										EMPENNAGE	OUT OF RIG      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	882CA	601  				155				UPON RE-INSTALLATION OF RUDDER AFTER INSTALLATION OF S/B 45-55-6, FOUND THAT THE RUDDER TRAVEL WAS APPROXIMATELY 25 DEGR	EES IN LIEU OF 30 +/-1 DEGREES AS PER LEARJET AMM 27-20-00.  WHEN TRAVEL WAS CORRECTED, DISCOVERED THAT THE BOTTOM SKIN 	OF RUDDER WAS CONTACTING THE SKIN PRIOR TO ACHIEVING FULL TRAVEL.. THE RUDDER WAS REPLACED WITH SAME P/N (S/N 0155). NO 	OTHER ACTION WAS REQUIRED AT THAT TIME.			2	L	7	2 	4F			RT	T00008WI					 
2002103000218	20021030	00218	CE  	2002	10	30	2002FA0001235    	1	20021029	G	2701	24600352	GUIDE           			CESSNA	172   	172S        	2072439	CE  										CONTROL COLUMN	DAMAGED         	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	28	528ER	1055 				172S8926				PILOT'S YOKE BINDS WHEN PULLED FULL AFT WITH LEFT HAND CREATING A SIDE LOAD ON COLUMN (IE. FLYING SINGLE HANDED).  MAINT	ENANCE FOUND THE YOKE ROLLER NOT FULLY ENGAGING IN GUIDE.  YOKE CLEARANCE IS WITHIN SPECIFIED .100 INCH CALLED OUT IN SB	99-53-03, HOWEVER, THE ROLLER RIDES TOO LOW IN THE GUIDE AND WILL POP OUT OF THE GUIDE IF ANY SIDE PRESSURE IS APPLIED. 	 PER SB99-53-03 A AN970-3 SPACER WASHER WAS INSTALLED ALLOWING THE ROLLER DEEPER ENGAGEMENT IN THE GUIDE WITHOUT THE ROL	LER BOLT HEAD SCRAPING THE TOP OF THE GUIDE.		1	H	7	1 	3O			NT	3A12    					 
2002103000219	20021030	00219	SO  	2002	10	30	2002FA0001236    	1	20021029	G	2497	455151	CONTACTOR       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	COCKPIT	BURNED          	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NE	01	5675V	300  				287790493	L2321536A	15426K		A/C DIVERTED DUE TO THE SEVERE CHOKING SMOKE.  PILOT DECLARED AN EMERGENCY AND SQUAWKED 7700 STATING THAT DUE TO THE SMO	KE HE WOULD HAVE TO DITCH IN THE OCEAN.  HE SAW THE BLOCK ISLAND AIRPORT AND LANDED LONG AND FAST RUNNING OFF THE END OF	 THE RUNWAY INTO A PERIMETER FENCE.  PILOT STATED HE HAD A HARD TIME STARTING THE ENGINE AND CRANKED THE ENGINE CONTINUO	USLY UNTIL THE BATTERY WENT DEAD.  HE GOT A JUMP-START FROM A VEHICLE USING THE CORRECT PLUGS AND 12 VOLT BATTERY.  IT A	PPEARS THAT THE POWER RELAY CONTACTOR PIPER FAILED, PERHAPS SHORTED INTERNALLY.  STARTER, ALTERNATOR, REGULATOR, START S	WITCH, STARTER SOLENOID ALL CHECKED GOOD.  THIS CONTACTOR WAS CHANGED TWO MONTHS PRIOR TO THIS FAILURE.	1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2002110100001	20021101	00001	CE  	2002	11	1	2002FA0001237    	1	20021015	G	2823	05160194	SHAFT           			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					FUEL SELECTOR	MISMANUFACTURED 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	54661					17275028				TOP FUEL SELECTOR SHAFT AT SELECTOR HANDLE ATTACH AREA NOT MANUFACTURED CORRECTLY CAUSING INADVERTENT MISCLOCKING OF SEL	ECTOR HANDLE.  OLD SHAFT AND NEW SHAFT BOTH HAVE GLOB OF ALUMINUM WELDED ON TOP OF SHAFT TO PREVENT THIS, BUT THE WELD G	LOB NEEDS TO EXTEND TO TOP OF SHAFT, AND THEN SHAPED TO EXCEPT HANDLE IN ONE DIRECTION ONLY.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002110100002	20021101	00002	GL  	2002	11	1	2002FA0001238    	1	20020913	G	5540	2055450000WIP	HINGE           			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O200  	O200*       	17020	SO  					RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	986CT	1497 				C0086				DURING 100 HOUR INSPECTION MECHANIC DISCOVER THAT THE LOWER LEFT CORNER OF THE LOWER RUDDER HINGE SUPPORT TOWER HAD A CR	ACK.  EVIDENCED BY LINE OF BROWN RUST RESIDUE VISIBLE AGAINST THE BLACK PAINT, AND ADJACENT TO THE WELD.  PART WAS REPLA	CED.				1	L	7	1 	3O	3	O	NT	TA4CH   	E252				 
2002110100003	20021101	00003	GL  	2002	11	1	2002FA0001239    	1	20020913	G	5540	2055450000WIP	HINGE           			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240A      	 	SO  					RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	978CT	1126 				C0078				DURING 100 HOUR INSPECTION MECHANIC FOUND CRACK ON LOWER RIGHT CORNER OF LOWER RUDDER HINGE SUPPORT TOWER NEXT TO THE WE	LD LINE.  PART WAS REPLACED WITH NEW PART.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2002110100004	20021101	00004		2002	11	1	2002FA0001240    	4	20021014	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	789EP	82   				172S8135				FOUND AFT PROPELLER SPINNER BULKHEAD, CRACKED AT ONE FLANGE AT PROPELLER BLADE CUT OUT.  EDGE WITH NUTPLATE AND SCREW ST	ILL ATTACHED TO PROPELLER SPINNER.  AFT SPINNER BULKHEAD REPLACED AT 82.2 HOURS .					1	H	7	1 	3O			NT	3A12    					 
2002110100098	20021101	00098	CE  	2002	11	1	2002FA0001241    	1	20021031	G	3233	97343	SPRING          	RAYTHN      		BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					LT UPLOCK	DISTORTED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	26TM				A13084	MC638	L1977151A			LT MLG UPLOCK ACTUATOR WOULD NOT RELEASE THE LANDING GEAR DURING 'FREE FALL' TEST. DISSAMBLY OF ACTUATOR REVEALED A NON 	APPROVED SPRING THAT WAS 0.125 INCHES SHORTER THAN THE ORIGINAL MANUFACTURER.  THE SCARCITY OF REPLACEMENT PARTS FOR THI	S UNIT MAY HAVE CAUSED A PREVIOUS REPAIRER TO USE UNAPPROVED PARTS.				1	L	7	1 	3O	3	O	 	A1CE    	1E10				 
2002110100101	20021101	00101	CE  	2002	11	1	2002FA0001242    	1	20021031	G	3211		SUPPORT         			BEECH 	23    	C24R        	1151254	CE  										LT & RT MLG	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	26TM	3138 				MC638				LT AND RT MLG FORWARD PIVOT SUPPORT ATTACHMENT 'JO-BOLTS' WERE FOUND LOOSE AND COULD BE ROTATED BY HAND. MORE THAN HALF 	OF THE 26 TOTAL FASTENERS HAD TO BE REPLACED.					1	L	7	1 	3O			 	A1CE    					 
2002110100106	20021101	00106	CE  	2002	11	1	2002FA0001243    	1	20021031	G	5610	51116041	WINDSHIELD      			CESSNA	421   	421B        	2076014	CE  										COCKPIT	MISINSTALLED    	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			W	D		INADEQUATE Q C            	INFLIGHT SEPARATION       		CR	CRUISE         	1			SO	07	333CJ	4550 	43   			421B0313				ON 27 JUNE 2002 WHILE AT CRUISE ALT FL240, PILOTS FRONT WINDSHIELD DEPARTED THE AIRCRAFT ALONG WITH PART OF THE INSTRUME	NT GLARE SHIELD AND PILOTS SUN VISOR.  LABORATORY EXAMINATION OF THE WINDSHIELD DID NOT REVEAL THE POINT OF FAILURE BUT 	DID STATE NUMEROUS INSTALLATION DISCREPANCIES ISSUES AT THE TIME OF MANUFACTURE/INSTALLATION AT THE MANUFACTURER.  RECOR	DS REVIEW DID NOT SHOW THAT THIS WINDSHIELD HAD EVER BEEN REPLACED SINCE MANFACTURE. MAINTENANCE  RECORD DID SHOW A REPA	IR WAS ACCOMPLISHED TO CORRECT A PRESSURIZATION LEAK AT THE 7 O' CLOCK POSITION ON THE WINDSHIELD.  SIX PLASTIC INSERTS 	WERE INSTALLED.   DISCREPANCIES PERTAINING TO REPAIRS TO THE WINDSHIELD HAVE BEEN REPORTED TO THE FAA PMI OF THE RESPONS	1	L	7	2 	3O			 	A7CE    					 
2002110100108	20021101	00108	CE  	2002	11	1	2002FA0001244    	1	20021031	G	5510	66312024	CLIP            			CESSNA	560   	560XL       	2076702	CE  										VERTICAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03		1195 				5605081				CRACKS AT TWO FASTENER HOLES ATTACHING NOTED CLIP TO THE VERTICAL STABILIZER AFT SPAR.						2	L	7	2 	4F			RT	A22CE   					 
2002110100111	20021101	00111	SO  	2002	11	1	2002FA0001245    	1	20021025	G	5610	1159SCB51023	WINDSHIELD      			GULSTM	G1159 	GIV         	3980115	SO  										COCKPIT	CRACKED         	C				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			GL	03	1990C	3831 				1276				OUTER PANE ON CO-PILOT WINDSHIELD CRACKED						2	L	7	2 	4F			RT	A12EA   					 
2002110100112	20021101	00112	SO  	2002	11	1	2002FA0001246    	2	20021031	G	8550	535810	BOLT            								CONT  	O520  	IO520D      	17032	SO  					CRANKCASE	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07							566793			CRANKCASE UPPER TIE BOLT THREADS WERE NOT CUT PROPERLY.  THEY HAD A FLAT PROFILE LIKE THE THREADS WERE NOT CUT DEEP ENOU	GH.  CONDITION DISCOVERED WHEN ATTEMPTING TO INSTALL NUTS ON THE BOLT.										3	O			E5CE				 
2002110600062	20021106	00062	CE  	2002	11	6	2002FA0001248    	1	20021004	G	5511	0532001202	SPAR            			CESSNA	172   	172N        	2072434	CE  										HORIZONTAL STAB	BROKEN          	B			GSZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	172GK	8134 				17271968				HORIZONTAL STABILIZER, SPAR BROKEN THRU LIGHTENING HOLE AS MARKED.  SPAR AND REINFORCEMENT ARE BOTH BROKEN.  UPPER CRACK	 EXTENDS INTO TOP OF REINFORCEMENT.  BOTH CRACKS ARE INBOARD OF STABILIZER ATTACH HOLES.					1	H	7	1 	3O			NT	3A12    					 
2002110600063	20021106	00063	SO  	2002	11	6	2002FA0001249    	2	20021005	G	8530	CCST712	CYLINDER        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			AL	03	8300Q					U20603161				PILOT NOTED ROUGH RUNNING ENGINE AND MADE PRECAUTIONARY LANDING.  LATER INSPECTION REVEALED NR 1 CYLINDER CRACKED AND A 	HOLE BLOWN THROUGH THE EXHAUST SIDE.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2002111400010	20021114	00010	SO  	2002	11	14	2002FA0001250    	2	20021009	G	7310	646207	TUBE            			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					FUEL INTAKE	CRACKED         	B			CQNR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	22166	150  				290225				INSPECTED AIRCRAFT ENGINE DURING ROUTINE OIL CHANGE AND NOTICED FUEL STAIN ON NR 6 INTAKE TUBE.  REMOVED TUBE AND FOUND 	TO BE CRACKED AT FLANGE PART HAD BEEN REPLACED 2 MONTHS EARLIER FOR SAME REASON.  COULD BE CAUSED BY ABNORMAL VIBRATIONS	 OR SHOCK COOLING OF TUBE.				1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2002110700066	20021107	00066	CE  	2002	11	7	2002FA0001251    	1	20020927	G	1430		BOLT            			CESSNA	185   	A185E       	2072818	CE  										TRUNNION	LOOSE           	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	4546F					1851039				FOUND BOTH MAIN GEAR FORWARD TRUNNION BOLTS LOOSE IN SPAR.  THIS WAS FOUND ON AN 100 HOUR INSPECTION.						1	H	7	1 	3O			 	3A24    					 
2002110700067	20021107	00067	EA  	2002	11	7	2002FA0001252    	2	20021002	G	8530	75874	CYLINDER        			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	WORN            	B			ZKGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	7991W		133  			282048				REMOVED 2 CYLINDER ASSEMBLY FROM ENGINE BECAUSE OF LOW COMPRESSION.  CYLINDER WERE REPAIRED AND INSTALLED AT OVERHAUL.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002111400011	20021114	00011		2002	11	14	2002FA0001253    	4	20020924	G	3414		INDICATOR       			CHRIS 	HUSKY 	A1          	221020X	NM  	LYC   	O360  	O360*       	41514	EA  					COCKPIT	CONTAMINATED    	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	2950Q					1046				AFTER RAIN STORM, FOUND WATER IN THE AIRSPEED INDICATOR AND THE ALTERNATOR POSSIBLE CAUSE IS COMING THROUGH THE STATIC P	ORTS ON THE PITOT TUBE.					1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2002110700068	20021107	00068	CE  	2002	11	7	2002FA0001254    	1	20020822	G	7921	627392	OIL COOLER      			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					ENGINE	LEAKING         	B			XYER	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	05	52509					18262652				FACTORY REBUILT ENGINE, INITIAL START UP OIL COOLER LEAKS, REMOVED COOLER AND BASE PLATE AND CHECKED SURFACES,  SURFACES	 FOUND NOT TO BE FLAT.					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2002110700069	20021107	00069	CE  	2002	11	7	2002FA0001255    	1	20021001	G	7921	G02188528	OIL COOLER      			CESSNA	206   	TU206F      	2073353	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	LEAKING         	B			XYER	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	05	603ET					U20602230				UPON INITIAL RUN UP OF FACTORY REBUILT ENGINE, COOLER LEAK NOTED.  REMOVED COOLER AND CHECK BASE PLATE AND COOLER BASE F	OR SURFACE VARIATIONS.  BOTH PIECES DID NOT HAVE SURFACES THAT SHOWED TO BE TRUE AND FLAT.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2002111400012	20021114	00012	SO  	2002	11	14	2002FA0001256    	2	20021002	G	7322		FLOAT           			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					CARBURETOR	SEPARATED       	B			XYER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	6582M	400  			CL01030	18263764				CARBURETOR, LEAKING ON AIRCRAFT.  SUSPECT FLOAT OR FLOAT NEEDLE STUCK.  REMOVED CARBURETOR, REMOVED BOWL.  HALF OF FLOAT	 PONTOON COMPLETELY SEPARATED FROM FLOAT ASSY.  SOLDER JOINT HOLDING  FLOAT TO ARM SEPARATED.					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2002111400013	20021114	00013	GL  	2002	11	14	2002FA0001257    	1	20021022	G	2434		NUT             			AMTR  	LANCAR	LANCAIR     	05616TS	GL  	CONT  	O550  	IO550G      	17042	SO  					ALTERNATOR SHAFT	SEPARATED       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	41MF	141  					679313			NUT SECURING ALTERNATOR DRIVE GEAR CAME OFF.  GEAR SUBSEQUENTLY FELL OFF OF ALTERNATOR SHAFT DAMAGING INTERNAL ENGINE GE	ARS.					1	L	7	1 	3O	3	O	RT	EXPA1L71	E3SO				 
2002111400014	20021114	00014	GL  	2002	11	14	2002FA0001258    	3	20021010	G	6114	B24573	FORK            			CESSNA	175   	175         	2072502	CE  	LYC   	O360  	O360*       	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9391B					55191		CH18963		OVERHAUL WAS BEING ACCOMPLISHED DUE TO HIGH CALENDER TIME, LOW HOURS SINCE NEW.  DURING MAGNETIC PARTICAL INSPECTION, MU	LTIPLE LARGE CRACKS WERE DISCOVERED IN PITCH CHANGE FORK.  FORK APPEARS TO BE MANUFACTURING DEFECTS,  POSSIBLY HEAT TREA	T CRACKS.				1	H	7	1 	3O	3	O	NT	3A17    	E286	5	C	P920	 
2002111400015	20021114	00015	CE  	2002	11	14	2002FA0001259    	1	20021021	G	3222	1018200741	FORK            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A11      	52043	NE  					MLG	CRACKED         	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4PT	6798 	2113 			BB879				FOUND HOLE FORK CRACKED, INSTALLED KIT.						1	L	7	2 	4T	3	T	 	A24CE   	E4EA				 
2002110700070	20021107	00070	CE  	2002	11	7	2002FA0001260    	1	20021029	G	5753	122010024	SKIN            			CESSNA	206   	T206H       	2073303	CE  										T/E FLAP	CRACKED         	B			HLFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	XBASV					08271				RIGHT SIDE FLAP CRACKED SKIN AROUND RIVETS IN INBOARD LEADING EDGE BOTTOM SKIN.						1	H	7	1 	3O			RT	A4CE    					 
2002110700071	20021107	00071	CE  	2002	11	7	2002FA0001261    	1	20021029	G	5753	122010024	SKIN            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					T/E FLAP	CRACKED         	B			HLFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	7277R					T20608073				FLAP HAS SEVERAL CRACKS ON SKIN AROUND RIVETS ON INBOARD LEADING EDGE.						1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2002110700072	20021107	00072	SO  	2002	11	7	2002FA0001262    	1	20021031	G	2720	4004009	TORQUE TUBE     			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER	CORRODED        	B			VQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	596L	2614 				317712036				WHILE COMPLYING WITH SB, WE FOUND EXCESSIVE CORROSION ON RUDDER TORQUE TUBE, RUDDER BUTT RIB AND RUDDER MAIN RIB.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002111400016	20021114	00016	CE  	2002	11	14	2002FA0001263    	1	20021021	G	5544	07436062	FITTING         			CESSNA	182   	182Q        	2072732	CE  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	97784	4085 				18267191				FOUND RUDDER TO BE OUT OF RIG FOR 2ND TIME IN 17 HRS INSPECTED AND FOUND LOWER STRUT FITTING TO BE CRACKED WERE STRUT FI	TTING TO BE CRACKED WERE STRUT ATTACHES TO FITTING.					1	H	7	1 	3O			NT	3A13    					 
2002110700073	20021107	00073	CE  	2002	11	7	2002FA0001264    	1	20021021	G	5521	043200121	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	94268	14155				15285632	L2343615			FOUND CRACK EXTENDING ABOUT.5 INCH FROM OUTBOARD HINGE POINT TO SPAR ATTACHMENT.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002111400017	20021114	00017	SO  	2002	11	14	2002FA0001265    	1	20021017	G	2823		SHUTOFF VALVE   			PIPER 	J3    	J3C65       	7100510	SO  										FUEL SYSTEM	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	17171					19970				DURING AN INVESTIGATION OF AN AIRCRAFT INCIDENT IN WHICH THE AIRCRAFT CRASHED INTO A POND DUE TO FUEL STARVATION.  IT WA	S DETERMINED THAT AN ALTERATION TO FUEL SHUT OFF VALVE HAD BEEN PERFORMED AND WAS NOT APPROVED.  AN EXTENSION TO THE VAL	VE WAS INSTALLED AND THE EXTENSION SWIVELLED ON THE FUEL SHUT OFF VALVE HANDLE CAUSING A FALSE INDICATION IN THE COCKPIT	 SHOWING THE VALVE TO BE OPEN BUT IN REALITY THE VALVE WAS CLOSED.  THE SHUT OFF VALVE WAS PROBABLY PARTIALLY OPEN BUT T	HE EXTENSION WAS 90 DEGREES TO THE HANDLE AND WAS BUMPED DURING FLIGHT WHILE PICTURES WERE BEING TAKEN CAUSING THE FUEL 	SHUT OFF VALVE TO CLOSE AND ENGINE TO QUIT.	1	H	7	1 	3O			 	A691    					 
2002111400018	20021114	00018	EA  	2002	11	14	2002FA0001267    	2	20021015	G	7414		P-LEAD          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	113PF	1636 				17280401				REPORTS OF INTERMITTENT LT MAG FAILURE.  TROUBLESHOT AND REMOVED ENTIRE P-LEAD ASSEMBLY.  FOUND SHIELDING SOLDER / CRIMP	 AT SWITCH END CUT INTO CENTER CORE VERY SLIGHTLY.  REPLACED P-LEAD ASSEMBLY.  NO ADDITIONAL REPORTS OF MAG FAILURE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002111400019	20021114	00019	SO  	2002	11	14	2002FA0001268    	1	20021004	G	3246	40142	BOLT            			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A11      	52043	NE  					MLG WHEEL	CORRODED        	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	5335R	299  				4697100				DURING A TIRE REPLACEMENT ON THE RT MAIN WHEEL ASSEMBLY, ALL WHEEL THRU BOLTS FOUND WORN AND CORRODED.  THERE WAS NO TYP	E OF ANTI-SEIZE LUBRICANT ON THE BOLTS.  PIPER MAINTENANCE MANUAL DOES NOT REQUIRE ANY ANTI-SEIZE LUBRICAN ON THE THRU B	OLTS.				1	L	7	1 	3O	3	T	RT	A25SO   	E4EA				 
2002111400020	20021114	00020	SO  	2002	11	14	2002FA0001269    	1	20021021	G	7160	570473	SCREEN          			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					AIRSCOOP	CRACKED         	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	444SC					428001034				DURING A SCHEDULED EVENT INSPECTION, BOTH ENGINE AIR INLET SCOOP SCREENS WERE FOUND CRACKED IN BOTH FORWARD CORNERS FOR 	EACH ENGINE.  REPAIR WAS NOT FEASABLE DUE TO THE LOCATION DAMAGE.  BOTH INLET SCREEN HAD TO BE REPLACED WITH NEW PARTS.					1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2002111400021	20021114	00021	SO  	2002	11	14	2002FA0001270    	2	20021023	G	8530	539487	CLAMP           			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520*    	17040	SO  					CROSSOVER TUBE	DISCONNECTED    	B			BONR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	7SA					EA427	249089R			PILOT REPORTED HEARING A POP AT 11,000 FT AND IMMEDIATELY LOST MANIFOLD PRESSURE.  PILOT MAKE PRECAUTIONARY LANDING WITH	OUT INCIDENT.  INSPECTION OF ENGINE REVEALED FORWARD CYLINDER INDUCTION MANIFOLD CROSSOVER TUBE HAD BECOME DISCONNECTED 	FROM NR 5 CYLINDER INTERCONNECT HOSE.  IT APPEARS SECURITY CLAMP MAY BE TOO NARROW TO ADEQUATELY SECURE CROSSOVER TUBE T	O NR 5 CYLINDER MANIFOLD ASSEMBLY AND INTERCONNECT HOSE.  ORDERED AND INSTALLED CLAMP IAW IPC.  REPLACEMENT CLAMP IS WID	ER THAN CLAMP REMOVED AND WILL PROVIDE IMPROVED INTEGRITY.		1	L	7	1 	3O	3	O	 	3A15    	E8CE				 
2002111400022	20021114	00022	CE  	2002	11	14	2002FA0001271    	1	20021031	G	3040	51116041	WINDSHIELD      			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					COCKPIT	FAILED          	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SO	07	333CJ					421B0313				WHILE AT CRUISE ALT FL240, PILOTS FRONT WINDSHIELD DEPARTED THE AIRCRAFT ALONG WITH PART OF THE INSTRUMENT GLARE SHIELD 	AND PILOTS SUN VISOR.  LAB EXAM OF WINDSHIELD DID NOT REVEAL POINT OF FAILURE BUT DID STATE NUMEROUS INSTALLATION DISCRE	PANCIES.  MAINTENANCE RECORD DID SHOW A REPAIR WAS ACCOMPLISHED TO CORRECT A PRESSURIZATION LEAK AT THE 7 O`CLOCK POSITI	ON ON THE WINDSHIELD.  SIX PLASTIC INSERTS WERE INSTALLED.			1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2002111400023	20021114	00023	EA  	2002	11	14	2002FA0001272    	2	20021028	G	8530		LIFTER          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NR 2 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	405SP	1636 				172S8298				WHILE DRAINING OIL, FOUND A PIECE OF STEEL WITH A ROUNDED EDGE.  ALSO FOUND METAL IN THE OIL FILTER.  REMOVED NR 2 CYLIN	DER AND FOUND THE INTAKE VALVE LIFTER HAD PIECES FRACTURED OFF OF THE EDGE.  THE CAM WAS SPALLED AND THE NR1 CYLINDER IN	TAKE VALVE LIFTER WAS ALSO SPALLED.  THE SKIRT ON THE NR 2 PISTON HAD SCRATCH MARKS FROM SHIPS OF THE LIFTER.  I COULD F	IND NO OBVIOUS CAUSE TO THE DAMAGED.  SUSPECT MANUFACTURING FLAW IN THE LIFTER BODY.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002111400024	20021114	00024	SO  	2002	11	14	2002FA0001274    	1	20020831	G	2823	66945000	SELECTOR VALVE  			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					FUEL SYSTEM	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	3961K					2823841	L1987927A			FUEL PLACARD, UPSIDE DOWN, FUEL SELECTOR LEVER WOULD TURN ONLY 180 DEGREES, AREA OF TRAVEL, COULD NOT SELECT OTHER 180 D	EGREES.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002111400025	20021114	00025	CE  	2002	11	14	2002FA0001275    	1	20021018	G	5610	10138402516	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	366EA					BB841				WINDSHIELD SHATTERED IN FLIGHT, FROM UNKNOWN CAUSES.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002111400042	20021114	00042	CE  	2002	11	14	2002FA0001276    	1	20021004	G	3340		CURRENT LIMITER 			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					PULSELIGHT	FAILED          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	19	2426					258272				ON A/C WITH BUS-TIE OPEN, LEFT MAIN BUS (PS1) AND RIGHT MAIN BUS (PS2) SHOULD BE SEPARATED.  COULD NOT SEPARATE PS1 AND 	PS2.  THEY WERE INADVERTENTLY LINKED TOGETHER THROUGH A PULSELIGHT INSTALLATION.  HAD A PULSELIGHT SYSTEM INSTALLED, A C	OMPONENT OF THE PULSELIGHT SYSTEM WAS INCORRECTLY INSTALLED.  IT IS THE CURRENT LIMITER.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002111400043	20021114	00043	CE  	2002	11	14	2002FA0001277    	1	20021004	G	3340		CURRENT LIMITER 			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					PULSELIGHT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	2428					258274				ON A/C WITH BUS-TIE OPEN, LEFT MAIN BUS (PS1) AND RIGHT MAIN BUS (PS2) SHOULD BE SEPARATED.  COULD NOT SEPARATE PS1 AND 	PS2.  THEY WERE INADVERTENTLY LINKED TOGETHER THROUGH A PLUSELIGHT INSTALLATION.  HAD A PULSELIGHT SYSTEM INSTALLED, A C	OMPONENT OF THE PULSELIGHT SYSTEM WAS INCORRECTLY INSTALLED.  IT IS THE CURRENT LIMITER.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002111400038	20021114	00038	EU  	2002	11	14	2002FA0001278    	1	20021025	G	2820	200001040	LINE            			REIMS 	177   	F177RG      	7530211	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					FUEL SYSTEM	CORRODED        	B			RH6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	274LH	1650 				0056				FUEL VENT LINES ABOVE HEADLINER CORRODED FROM CLAMPS AND SEAT TUBING TOUCHING LINES CAUSING RAW FUEL AND FUMES TO ENTER 	UPPER CABIN AREA.					1	H	7	1 	3O	3	O	 	A26EU   	1E10				 
2002111400039	20021114	00039	CE  	2002	11	14	2002FA0001279    	1	20021028	G	2434		NUT             			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					ALTERNATOR	LOOSE           	B			RH6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4690N					18267289	467413			ALTERNATOR CHARGE, FAILURE DUE TO LOOSE PULLEY FAN AND SHROUD ASSEMBLY.  UNDER ANY LOAD SLIPPAGE OCCRUED .  HEATED NUT A	ND LOOSENED ASSEMBLY.  KEYWAY INSTALLATION WOULD SOLVE POSSIBLE PROBLEM AND PULLEY SLIPAGE.  AIRCRAFT WAS REPORTING INTO	 IMC PREFLIGHT RUN UP, CHARGING FAILED.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002111400040	20021114	00040	CE  	2002	11	14	2002FA0001280    	1	20021029	G	5753		SKIN            			CESSNA	206   	T206H       	2073303	CE  										TE FLAP	CRACKED         	B			HLFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	XBRRV	114  				08247				RT SIDE FLAP CRACKED SKIN AROUND RIVETS ON LEADING EDGE BOTTOM SECTION.						1	H	7	1 	3O			RT	A4CE    					 
2002111400041	20021114	00041	GL  	2002	11	14	2002FA0001281    	1	20021017	G	2700	11898002	CARTRIDGE       			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					YAW TRIM	DEFECTIVE       	B			V9MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	18DN					0096				DURING COMPLIANCE WITH SB, REPLACEMENT OF TRIM CARTRIDGE NUT THE YAW TRIM CARTRIDGE FAILED TORQUE CHECK.  THE ROD FOR TH	E TRIM CARTRIDGE APPEARS TO BE UNDERSIZE THEREFORE THE NUT WILL ONLY HOLD AT 1 INCH POUND OF TORQUE RATHER THAN 3 INCH P	OUNDS AS REQUIRED IN SB.				1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2002111400044	20021114	00044	GL  	2002	11	14	2002FA0001283    	2	20021106	G	7250	6895801	TURBINE WHEEL   								ALLSN 	250C  	250C28      	03013	GL  					TURBINE SECTION	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	A9UR						CAT70139			AREA OF WHEEL EXCEEDS MAXIMUM LIMITS.  AREA MIN. 4.60, AREA MAX 4.78.  AREA OF THIS WHEEL IS 4.80.											3	U			E1GL				 
2002111400055	20021114	00055	EU  	2002	11	14	2002FA0001284    	1	20021105	G	5500		SPAR            			SPHRTH	CIRRUS	CIRRUSSTD   	38019VE	EU  										STABILATOR	CRACKED         	B			L1MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	44FV	1683 				V1				MAIN SPAR OF TAILPLANE (STABILATOR) WAS FOUND TO CONTAIN MULTIPLE CRACKS IN WOOD STRUCTURE AFT MOUNTING HOLES.  PLYWOOD 	FACE PLATES WERE DELAMINATED AND HIDING CRACKS.  ALL ATTACHMENT HARDWARE WERE RUSTED.  TAILPLANE WAS LOOSE WITH EXCESSIV	E PLAY AFTER HARD LANDING, PILOT INDICATED IT WAS ALWAYS LOOSE.				1	K	0	0 	  			 	G23EU   					 
2002111400072	20021114	00072	SW  	2002	11	14	2002FA0001285    	1	20021101	G	3220	45291401	TORQUE TUBE     			GULSTM	112   	112         	0144701	SW  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	CRACKED         	B			GF4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	1169J	2023 				169				DURING INSPECTION OF THIS LANDING GEAR TORQUE TUBE THE PART WAS CLEANED OFF WITH A RAG AND VISUALLY INSPECTED AS USUAL. 	 PAINT WAS SMOOTH AND UNBROKEN AROUND ENTIRE PART OTHER THAN NORMAL SMALL CHIPS IN PAINT FROM NORMAL USAGE.  THEN SERVIC	ED WITH A HAND OPERATED GREASE GUN ON THE FORWARD ZERK FITTING THE PAINT ON AFT SIDE OF PART SPLIT ALONG APPROXIMATELY F	OUR INCH LENGTH AND GREASE EXITED FROM CRACK.  THIS DEFECT WOULD NOT HAVE BEEN DETECTED DURING THE ANNUAL INSPECTION UNL	ESS THE SERVICE WORK HAD BEEN DONE CONCURRENTLY WITH THE INSPECTION.		1	L	7	1 	3O	3	O	 	A12SO   	1E10				 
2002111400073	20021114	00073	NE  	2002	11	14	2002FA0001286    	2	20021029	G	7240	2A3537	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					ENGINE	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01										SEAL REJECTED FOR CRACK AT 1 PLACE ON BACK WALL OF THE PILOT GROOVE SEAL AS MARKED ON THE PART.											4	F			E311NE				 
2002111400074	20021114	00074	NE  	2002	11	14	2002FA0001287    	2	20021024	G	7240	2A3537	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										SEAL REJECTED AT FPI FOR VOID WITH LINEAR INDICATION ON SEAL LAND EXCEEDING 3X1 LIMIT.											4	F			E311NE				 
2002111400075	20021114	00075	CE  	2002	11	14	2002FA0001288    	1	20021021	G	2497	128364231601	WIRE HARNESS    			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15*       	52060	NE  					MAIN BATTERY	BURNED          	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SO	13	134CM	910  				RK144				WHILE MOTORING ENGINE FOR OTHER MAINTENANCE, FOUND BURNING ODOR AND SMOKE IN AREA OF MAIN BATTERY.  ON VISUAL INSPECTION	, FOUND POSITIVE TERMINAL AND WIRE LEADS OF CONNECTOR BURNED.  ALSO FOUND DAMAGE TO BATTERY TERMINAL.					2	H	7	2 	4F	4	T	RT	A16SW   	E1NE				 
2002111400076	20021114	00076	CE  	2002	11	14	2002FA0001289    	1	20021031	G	3213	10581002367	FRAME           			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360*       	41514	EA  					MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	516MS	6561 				ME166				THE LEFT FRAME WAS NOTED TO HAVE CORROSION PREVENTATIVE OOZING IN THE EXACT AREA OF THE INSPECTION, IN A LINE THAT APPEA	RED AS A CRACK.  THE AREA WAS CLEANED AND A CRACK WAS APPARENT BY USING A GOOD LIGHT AND 10 POWER GLASS.  A DYE CHECK OF	 THE AREA FAILED TO REVEALED THE CRACK.  SUSPECT THE CORROSION PREVENTATIVE FILLS THE CRACK AND IS NOT CLEANED OUT BY TH	E PENETRANT CLEANER SO THE PENETRANT IS NOT ALLOWED TO WORK AS IT IS MEANT TO.			1	L	7	2 	3O	3	O	 	A29CE   	E286				 
2002111400006	20021114	00006	GL  	2002	11	14	2002FA0001290    	1	20021101	G	3210	10209001	GROMMET         			CIRRUS	SR    	SR22        	2130001	GL  										MLG	DEFORMED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	101CD	224  				0101				DURING A SCHEDULED INSPECTION FOUND BOTH MLG LEG ATTACH BRACKET GROMMETS CRACKED AROUND FLANGES AND DISTORTED. HAVE FOUN	D SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TOTAL FAILU	RE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE.				1	L	7	1 	3O			NT	A00009CH					 
2002111400007	20021114	00007	GL  	2002	11	14	2002FA0001291    	1	20021108	G	3210	10209001	GROMMET         			CIRRUS	SR    	SR22        	2130001	GL  										MLG	DEFORMED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	806CD	192  				0106				DURING A SCHEDULED INSPECTION FOUND BOTH MLG LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. 	HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TO	TAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE.				1	L	7	1 	3O			NT	A00009CH					 
2002111400008	20021114	00008	EU  	2002	11	14	2002FA0001293    	2	20021113	G	8520		CRANKCASE       			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912S3  	 	EU  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	87HA	659  				10086	4922711			AIRCRAFT WAS SQUAWKED FOR OIL LEAKING FROM COWL.  UPON INSPECTION THE LEAK WAS DETERMINED TO BE COMMING FROM A CRACK ON 	TOP OF ENGINE UNDER COOLING SHROUD. (COOLING SHROUD HAS TO BE REMOVED TO INSPECT THIS AREA)  THE CRACK WAS APPROXIMATLY 	3 INCHES AND IS ORINTATED FORE AND AFT BETWEEN CYLINDERS 1 AND 3.				1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2002111400009	20021114	00009	EA  	2002	11	14	2002FA0001294    	2	20021113	G	7310		LINE            			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360*       	41514	EA  					ENGINE FUEL SYS	SEPARATED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	84HY	259  				2184	L3851036A			CENTER SUPPLY PRIMER LINE SEPARATED FROM TEE FITTING AT BACK OF ENGINE.  DISCOVERED DURING ATTEMPT AT COLD ENGINE STARTI	NG.  NOTICED DIFFICULTY IN STARTING AND FUEL SMELL.  OPENED COWLING TO DISCOVER PRIMER LINE SEPARATED.					1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2002111500001	20021115	00001		2002	11	15	2002FA0001297    	4	20021114	G	3422		WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  										DIRECTIONAL GYRO	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	1258B	20   				5501037				OPERATOR NOTED NR 2 DIRECTIONAL GYRO CIRCUIT BREAKER POPPING. MAINTENANCE DETERMINED A WIRE BUNDLE ROUTED AROUND THE DAT	A TRANSFER UNIT (DTU) WAS CHAFING AGAINST THE OUTBOARD CONNECTOR PLUG ON THE DTU. ONE WIRE IN THE BUNDLE WAS FOUND SHORT	ED AGAINST THE CONNECTOR PLUG. THE WIRE WAS REPAIRED BY INSTALLING AN ENVIRONMENTAL SPLICE IN THE DAMAGED AREA. SPIRAL W	RAP WAS INSTALLED AROUND THE WIRE BUNDLE AND THE WIRE BUNDLE WAS RELOCATED AS MUCH AS POSSIBLE TO PREVENT A RECURRENCE O	F THE PROBLEM. FUNCTION TEST REVEALED NO FURTHER DEFECTS.		1	L	7	2 	4F			 	A22CE   					 
2002112000022	20021120	00022	CE  	2002	11	20	2002FA0001298    	1	20021106	G	2750	AN460A	BOLT            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					RT FLAP PULLEY	LACK OF LUBE    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	06	52964	8911 				17274645				LACK OF LUBRICATION CAUSED BOLT TO SEIZE IN FLAP DRIVE PULLEY RIGHT BUSHING.  OVER PERIOD OF TIME, WITH EVERY CYCLE OF F	LAPS THIS BOLT ROTATING ELONGATED TOP AND LOWER BRACKETS .  ON PREFLIGHT PILOT NOTED SOMETHING STREAKING FROM LOWER SKIN	.  REPLACEMENT OF BRACKETS, BOLT, BUSHING WERE NECESSARY.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002112000023	20021120	00023	SO  	2002	11	20	2002FA0001299    	2	20021014	G	8520	652832	CRANKSHAFT      								CONT  	O520  	GTSIO520*   	17032	SO  					ENGINE	CRACKED         	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19		2916 					241235R			CRANKSHAFT CRACKED BETWEEN FRONT TWO COUNTERWEIGHTS AND A PIECE MISSING FROM THAT AREA.											3	O			E7CE				 
2002112000024	20021120	00024	SO  	2002	11	20	2002FA0001300    	1	20021106	G	3252		BOLT            			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					SHIMMY DAMPENER	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05	6292H					243189				BOLT WAS INSTALLED BACKWARDS ON SHIMMY DAMPNER.  GEAR WAS LOWERED IN FLIGHT AND HUNG UP ON COWL LT V CHANNEL.  SUBSEQUEN	T DAMAGE WAS CAUSE TO CHANNEL AND REAR SUPPORT.  TIME SINCE LAST WORK TO SHIMMY DAMPENER MOUNT CLAMP UNKNOWN.					1	L	7	1 	3O	3	O	 	1A15    	E295				 
2002112000025	20021120	00025	CE  	2002	11	20	2002FA0001301    	1	20021106	G	3246	D30321	HUB             			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					NOSEWHEEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	5491G	5422 				421C0238				DURING NOSE TIRE CHANGE, DEGREASING OF WHEEL AND HUB, THREE CRACKS WERE FOUND ON CENTER HUB WHERE END PLATES BOLT TO HUB	.  WHEEL ASSEMBLY WAS PREVIOUSLY PAINTED MAKING VISUAL INSPECTION IMPOSSIBLE.  AT TIME OF CHANGE, PAINT FLAKING ALLOWED 	CRACKS TO SHOW UP.  LAST NOSE TIRE CHANGE WAS 2/97 AT TT 4952.4.				1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2002112000027	20021120	00027	CE  	2002	11	20	2002FA0001303    	1	20021116	G	3010	671440238	TUBE            			CESSNA	750   	750         	2076810	CE  										DEICE SYSTEM	FAILED          	D				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CL	CLIMB          	1			NM	09	551AM	670  	220  			7500155				PILOTS COMPLAINT OF RT ANTI-ICE HOT MESSAGE WHEN SYSTEM TURNED ON. VERIFIED SENSOR AND LOGIC CARD OPERATION OK. REMOVED 	RT LEADING EDGE AND FOUND MAIN TUBE HAD BURST WITH A 2.5 X .375 INCH HOLE, BLOWING AWAY INSULATION AROUND ASSEMBLY. THIS	 WAS JUST INBOARD OF THE SLAT ANTI-ICE VALVE. TUBE ASSEMBLY TO BE RETURNED TO MFG FOR EVALUATION. NEW ASSEMBLY INSTALLED	.			2	L	7	2 	4J			RT	T00007WI					 
2002112000028	20021120	00028	CE  	2002	11	20	2002FA0001304    	1	20021107	G	2510	MM201057	ACTUATOR        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					SEAT RECLINE	INOPERATIVE     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	142ME	250  				172S8425				PILOT SEAT RECLINE MECHANISM FAILED.  SEAT RECLINED FULLY AFT, WAS REPEATABLE.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002112000029	20021120	00029	SO  	2002	11	20	2002FA0001307    	1	20020914	G	3213		BOLT            			MAULE 	M5    	M5235C      	5460135	SO  	LYC   	O540  	O540*       	41532	EA  					MLG STRUT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	5636D					7305C				BOLT (NR 32) IS ONE OF FOUR.  THREE APPARENTLY WERE PROBABLY SHEARED FROM PAST ACCIDENT.  SAFETY WIRE HELD 211 BOLTS FRO	M ROTATING.  REMAINING BOLT TORE OUT END OF UPPER TUBE, CAUSING COMPLETE DISASSEMBLY OF UPPER PART OF STRUT.  UPPER ATTA	CH BOLT (NR 17) AND LOWER ATTACH BOLT (NR 16) WERE BENT SLIGHTLY, ALSO.				1	H	7	1 	3O	3	O	 	3A23    	E295				 
2002112000020	20021120	00020	EU  	2002	11	20	2002FA0001308    	1	20021119	G	5311	A102006L	FRAME           			LET   	L13   	L13BLANIK   	1360306	EU  										FUSELAGE AFT	DETACHED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	421BA					028902				DURING ACCEPTANCE INSPECTION UPON DELIVERY FROM THE CZECH REPUBLIC, EXTERNAL DAMAGE WAS NOTED WHERE THE AFT FUSELAGE RES	TS IN THE TRAILER TAIL DOLLY.  INTERNAL INSPECTION OF THE FUSELAGE REVEALED DEFORMED AND TORN FUSELAGE FRAME MEMBERS NR 	11, 12, AND 13.  SUBSEQUENT INSPECTION OF THREE OTHER RECENTLY ACQUIRED AIRCRAFT REVEALED SIMILAR DAMAGE.  THE SUBMITTER	 SUGGESTS TWO POSSIBLE CAUSES FOR THIS DAMAGE.  FIRST, THAT THIS DAMAGE OCCURRED DUE TO LACK OF LOAD DISTRIBUTION ON THE	 AFT FUSELAGE WHILE BEING TRANSPORTED IN THE TRAILER.  SECOND, THAT THE DAMAGE OCCURRED DURING THE MANUFACTURING PROCESS	.  PART NUMBERS OF AFFECTED FRAMES:  FRAME NR 11- A102006L (LT), A102006P (RT)  FRAME NR 12- A102007L, A102007P  FRAME N	1	K	0	0 	  			 	G24EU   					 
2002112000021	20021120	00021	EU  	2002	11	20	2002FA0001309    	1	20021119	G	5311	A102006P	FRAME           			LET   	L13   	L13BLANIK   	1360306	EU  										FUSELAGE AFT	DETACHED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	422BA	80   				028903				DURING ACCEPTANCE INSPECTION UPON DELIVERY FROM THE CZECHOSLOVAKIA SOCIALIST REPUBLIC, EXTERNAL DAMAGE WAS NOTED WHERE T	HE AFT FUSELAGE RESTS IN THE TRAILER TAIL DOLLY.  INTERNAL INSPECTION OF THE FUSELAGE REVEALED DEFORMED AND TORN FUSELAG	E FRAME MEMBERS NR 11, 12, AND 13.  SUBSEQUENT INSPECTION OF THREE OTHER RECENTLY ACQUIRED AIRCRAFT REVEALED SIMILAR DAM	AGE.  THE SUBMITTER SUGGESTS TWO POSSIBLE CAUSES FOR THIS DAMAGE.  FIRST, THAT THIS DAMAGE OCCURRED DUE TO LACK OF LOAD 	DISTRIBUTION ON THE AFT FUSELAGE WHILE BEING TRANSPORTED IN THE TRAILER.  SECOND, THAT THE DAMAGE OCCURRED DURING THE MA	NUFACTURING PROCESS.  PART NUMBERS OF AFFECTED FRAMES:   FRAME NR 11- A102006L (LT), A102006P (RT) FRAME NR 12- A102007L	1	K	0	0 	  			 	G24EU   					 
2002112000050	20021120	00050	CE  	2002	11	20	2002FA0001313    	1	20021111	G	2710	50452133	TUBE            			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  					AILERON	FAILED          	B			NT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	105GB					4140644				AT ANNUAL INSPECTION, A CLICKING NOISE WAS NOTED WHEN LANDING GEAR WAS RETRACTED.  UPON INVESTIGATION, IT WAS DETERMINED	 THAT THE END FITTINGS RIVETED IN THE TUBE ASSEMBLY WERE WORKING.  CATASTROPHIC FAILURE WAS PROBABLY NOT IMMINENT, HOWEV	ER IF LEFT UNATTENDED THE RIVETS WOULD HAVE EVENTUALLY SHEARED ALLOWING THE END FITTING TO SEPARATE FROM TUBE.				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2002112500015	20021125	00015	EU  	2002	11	25	2002FA0001314    	1	20021107	G	2430	51509006C	GCU             			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					NR 1 GENERATOR	INOPERATIVE     	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	03	332WE	556  				257186				PILOTS REPORTED LOSS OF NR 1 GENERATOR INFLIGHT, PROCEEDED TO DESTINATION.  WITHOUT INCIDENT, TROUBLESHOT AND FOUND NR1.	  GCU GENERATOR CONTROL UNIT INOPERATIVE ALSO FUSE F1 ON PANEL ZX OPEN REPLACED GCU AND FUSE OPS CHECKED OK.					2	L	7	2 	4F	4	F	 	A3EU    	E6WE				 
2002112500016	20021125	00016	SO  	2002	11	25	2002FA0001315    	1	20021101	G	2720	4004007	TUBE            			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					RUDDER	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	804C	5113 				31T1166006				RUDDER TUBE ASSY HAS SEVERE CORROSION AND EXFOLIATION,  WHICH HAS CAUSED STRUCTURAL DETERIORATION OF THE COMPONENT.						1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2002112500017	20021125	00017		2002	11	25	2002FA0001316    	4	20021101	G	2562	AK450	ELT             			BEECH 	35    	V35A        	1151544	CE  	CONT  	O520  	TSIO520D    	17040	SO  					CABIN	WILL NOT TEST   	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	03	222S					D9008	180081			ELT  NOT TRANSMITTING ON AM RADIO OR 121.5 VHF FREQUENCIES.  DOES NOT PASS CFR PART 91.207D TEST.  ELT WAS INSTALLED DEC	, 2001 (NEW) AND TESTED PROPERLY AT THAT TIME UNIT HAS BEEN SENT FOR REPAIR.					1	L	7	1 	3O	3	O	 	3A15    	E8CE				 
2002112500018	20021125	00018	EA  	2002	11	25	2002FA0001317    	2	20021017	G	8520	13S19646	GEAR            								LYC   	O320  	O320D3G     	41508	EA  					CRANKSHAFT	MISMARKED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13										THE CRANK GEAR WAS INSTALLED NEW IN A FRESHLY OVERHAULD ENGINE.  THE ENGINE WAS HARD STARTING AND WOULD NOT GIVE A SATIS	FACTORY STATIC POWER CHECK.  TROUBLESHOOTING REVEALED THE OVERHAULER ASSEMBLED THE ENGINE WITH THE TIMING MARKS ALIGNED.	  THE TIMING MARK WAS NOT INDEXED TO THE PROPER TOOTH ON THE GEAR FROM THE FACTORY.									3	O			E274				 
2002112500019	20021125	00019	CE  	2002	11	25	2002FA0001318    	1	20021016	G	7810		FLANGE          			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					EXHAUST WYE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	28RG		1241 			340A0347				THE ATTACHING FLANGES BETWEEN THE EXHAUST WYE AND WASTE GATE ELBOW CRACKED ON BOTH PARTS.						1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2002112500020	20021125	00020	CE  	2002	11	25	2002FA0001319    	1	20021016	G	7810		FLANGE          			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					EXAHAUST WYE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	28RG		1241 			340A0347				THE ATTACHING FLANGES BETWEEN THE EXHAUST WYE AND WASTE GATE ELBOW CRACKED ON BOTH PARTS.						1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2002112500021	20021125	00021	CE  	2002	11	25	2002FA0001320    	1	20021016	G	7920	S112980310	HOSE            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					OIL COOLER	LOOSE           	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	09	6303V	200  				172RG0615				THE OIL RETURN HOSE FROM THE OIL COOLER WORKED ITSELF LOOSE AT THE OIL COOLER FITTING.						1	H	7	1 	3O	3	O	 	3A17    	E286				 
2002112500022	20021125	00022	CE  	2002	11	25	2002FA0001321    	1	20021105	G	7603		SWITCH          			RAYTHN	390   	390         	       	CE  										THROTTLE	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	02	719L	99   				RB25				HIGH RESISTANCE (8 OHMS) IN RIGHT LOW NR THROTTLE LEVER SWITCH.  6 OHMS MAX PER SPEC SHEET.  SPOILER CONTROL UNIT RECEIV	ES ELECTRICAL SIGNAL FROM LOW N1 THROTTLE SWITCH AS A SUBSYSTEM TO SATISFY LIFT DUMP EXTEND AND RETRACT LOGIC.  SCU WILL	 NOT EXTEND OR RETRACT WITHOUT SIGNAL AND AIRCRAFT WILL NOT HAVE DESIGNED BRAKING.				1	7		2 	3F			RT	A00010WI					 
2002112500023	20021125	00023	SO  	2002	11	25	2002FA0001322    	1	20021114	G	3020		ANTI-ICE VALVE  			LKHEED	1329  	1329*       	       	SO  	GARRTT	TFE731	TFE7313     	01518	WP  					NACELLE	INOPERATIVE     	B			QQGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09										ANTI-ICE VALVE RECEIVED FROM OVERHAUL AGENCY WITH A FRESH OVERHAUL, SOLENOID VALVE WAS CLOCKED 90 DEGREE FROM WHERE THE 	PRODUCTION PRINT SHOWED WHERE IT SHOULD BE.  WE WOULD NOT BE ABLE TO INSTALL IT IN THE AIRCRAFT.  THIS HAS BEEN REPORTED	 TO THIS OVERHAUL AGENCY IN THE PAST AND THE PROBLEM HAS NOT BEEN CORRECTED.				2	L	7	4 	4J	4	F	 	2A15    	E6WE				 
2002112500024	20021125	00024	SO  	2002	11	25	2002FA0001323    	1	20021114	G	3020	JC007A	ANTI-ICE VALVE  			LKHEED	1329  	1329        	5263102	SO  	GARRTT	TFE731	TFE7313     	01518	WP  					NACELLE	INOPERATIVE     	B			QQGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09										ANTI-ICE VALVE RECEIVED FROM OVERHAUL AGENCY WITH A FRESH OVERHAUL, SOLENOID VALVE WAS CLOCKED 90 DEGREE FROM WHERE THE 	PRODUCTION PRINT SHOWED WHERE IT SHOULD BE.  WE WOULD NOT BE ABLE TO INSTALL IT IN THE AIRCRAFT.  THIS HAS BEEN REPORTED	 TO THIS OVERHAUL AGENCY IN THE PAST AND THE PROBLEM HAS NOT BEEN CORRECTED.				2	L	7	4 	4J	4	F	 	2A15    	E6WE				 
2002112500025	20021125	00025	SO  	2002	11	25	2002FA0001324    	1	20021023	G	3233	757833	COUPLING        			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					MLG ACTUATOR	BROKEN          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	09	7141P					242306				COUPLING FAILED ON GEAR RETRACTION.  COUPLING FROM MOTOR TO GEAR BOX CAUSING COUPLING TAB TO SLIDE OUT OF SLOTS CAUSING 	GEAR TO LOCK HALF-WAY UP, WOULD NOT EXTEND OR RETRACT.  USED EMERGENCY PROCEDURE TO EXTEND GEAR.  GEAR CIRCUIT BREAKER P	OPPED.  EMERGENCY SPRING WAS BROKEN ON THE JACKSCREW ASSEMBLY, NOT ALLOWING THE JACKSCREW TO DISCONNECT, HAD TO BE MANUA	LLY LIFTED.			1	L	7	1 	3O	3	O	 	1A15    	E295				 
2002112500012	20021125	00012		2002	11	25	2002FA0001325    	4	20021121	G	3197		WIRE HARNESS    			CESSNA	172   	172S        	2072439	CE  										INSTRUMENT PANEL	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	484SP					172S8030				INVESTIGATING AN INOPERATIVE GLARE SHIELD LIGHT, FOUND THAT THE WIRING BUNDLE HAD CHAFED AGAINST THE THROTTLE HOUSING BE	HIND THE INSTRUMENT PANEL, SHORTING THE CIRCUIT.  SEVERAL WIRES WERE DAMAGED.  THERE IS NOTHING TO PROTECT THE WIRES IN 	THIS AREA SINCE THEY ARE LEFT LYING LOOSELY ON TOP OF THE THROTTLE HOUSING.				1	H	7	1 	3O			NT	3A12    					 
2002112500013	20021125	00013	SO  	2002	11	25	2002FA0001327    	2	20021122	G	7414	6310	MAGNETO         			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					ENGINE	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	316RB	590  				TH1947	684363			MAGNETO APPARENTLY SUFFERED A STOPPAGE CONDITION DUE TO UNKNOWN FAILURE OF IMPULSE COUPLING. DISINTEGRATED INTO SEVERAL 	PIECES. PARTS FOUND IN FILTER AND PRESSURE RELIEF VALVE. PROBLEM NOTED AT OIL CHANGE AND PILOT REPORTED GRIP OF LOW OIL 	PRESSURE. MAGNETO HAD BEEN CHANGED PREVIOUSLY AT DIFFERENT LOCATION.				1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2002112500014	20021125	00014	EA  	2002	11	25	2002FA0001328    	2	20021122	G	7414	MS3333	IMPULSE COUPLING	SLICK       		PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					MAGNETO	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4241R				01050291	3240606	L1298248			"ALERT" MAGNETO IMPULSE COUPLING PAWL RIVET (RIVET ATTACHES PAWL TO IMPULSE HUB ASSEMBLY) FAILED ALLOWING PAWL TO WEDGE 	IN MAGNETO DRIVE GEAR CAUSING FAILURE OF DOWEL ON CRAKKSHAFT DRIVE GEAR RESULTING IN COMPLETE STOPPAGE OF ENGINE. IN ADD	ITION, THE MAGNETO FLANGE BROKE AWAY AT THE HOLD DOWN BRACKET.                       				1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2002112600033	20021126	00033	GL  	2002	11	26	2002FA0001329    	1	20021007	G	5540	205540000WIP	SUPPORT         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	974CT	2568 				C0074				THE SUPPORT BRACKET HAS BEEN FOUND CRACKED AT THE WELD ON THE LOWER LEFT SUPPORT LEG.  AIRCRAFT TOTAL TIME 2568.  THE SU	PPORT IS VERY LIGHT AND IS MOUNTED TO THE COMPOSIT VERTICAL SPAR.  THE AREA UNDER THE TOWER IS NOT FLAT AND CAUSES THE T	OWER TO CRACK DUE TO THE UNEVEN FORCE APPLIED WHEN THE MOUNTING BOLTS ARE TORQUED TO THERE PORPER TORQUE.  THE AREA UNDE	R THE TOWER NEEDS TO BE FLAT.  THE TOWER NEEDS TO BE MADE STRONGER WHERE IT IS WELDED TO BASE.			1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2002112600034	20021126	00034	NM  	2002	11	26	2002FA0001330    	1	20021114	G	2435	03600923	BEARING         			DHAV  	DHC8  	DHC8*       	       	NM  										STARTER GEN	FAILED          	B			OL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27		1877 	1809 							STARTER GENERATOR HAD BEARING FAILURE.						2	H	7	2 	4T			RT	A13NM   					 
2002112700035	20021127	00035	EU  	2002	11	27	2002FA0001332    	2	20021107	G	8530	854381	ROCKER          								ROTAX 	912   	ROTAX912S4  	 	EU  					ENGINE CYLINDER	WORN            	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	124XS	336  								WHEN COMPLYING WITH AD, FOUND ROCKER ARMS WORN AT VALVE FACE AREA, AND GALLING AT PUSHROD SOCKETS.  ROTAX SB ADDRESSES T	HIS PROBLEM, HOWEVER IT DOES NOT INCLUDE THIS SN OF ENGINE.										3	O			E00051EN				 
2002112700044	20021127	00044	SO  	2002	11	27	2002FA0001335    	1	20021112	G	2720	767350	TORQUE TUBE     			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A11      	52043	NE  					RUDDER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	195AA	3794 				31T7904001				FLIGHT CONTROLS, RUDDER TORQUE TUBE/ RIBS CORROSION PRESENT, REPAIRABLE.						1	L	7	2 	3T	3	T	 	A8EA    	E4EA				 
2002112700045	20021127	00045	SO  	2002	11	27	2002FA0001336    	1	20021112	G	2720	767350	TORQUE TUBE     			PIPER 	PA31T 	PA31T1      	7103126	SO  	PWA   	PT6   	PT6A11      	52043	NE  					RUDDER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	855JL	3234 				31T8104045				DURING COMPLIANCE OF SB (RUDDER FLIGHT CONTROLS) TORQUE TUBE ASSEMBLY AND ASSOCIATED RIBS WERE NOTED TO BE NON-REPAIRABL	E.  CORROSION PRESENT.					1	L	7	2 	3T	3	T	 	A8EA    	E4EA				 
2002112700046	20021127	00046		2002	11	27	2002FA0001337    	4	20021113	G	2210	0105R2	ROLL SERVO      			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520*      	17032	SO  					AUTOPILOT	DEFECTIVE       	B			DDNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	36VG	21   				E309				SERVO DRIVE MOTOR SEPARATED FROM REDUCTION GEAR ASSEMBLY.  OCCURRED IN NORMAL FLIGHT OPERATIONS.  SECOND OCCURRENCE IN T	HIS AIRCRAFT, IDENTICAL FAILURE.  WARRANTY SERVO INSTALLED 9/27/2002, FAILED 11/12/2002.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2002112700047	20021127	00047	GL  	2002	11	27	2002FA0001338    	2	20021121	G	7313	23055438	NOZZLE          								ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	FAILED          	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17							CAE890553			ENGINE FAILED WHILE AC WAS ON GROUND.  UPON DISASSEMBLY OF ENGINE, FOUND GAS PRODUCER ROTOR TIE BOLT BROKEN IN HALF.  FU	RTHER EXAMINATION FOUND THAT NR 2 NOZZLE, WHICH HAD BEEN OVERHAULED 1751 HOURS PRIOR, WAS MISSING 3 OF 5 KEYS THAT HOLD 	DIAPHRAGM IN PLACE.  INSPECTION OF  WELDS ON THE 2 REMAINING KEYS FOUND THAT THEY WERE NOT WELDED ON 3 SIDES, AS IS REQU	IRED.  THE WELDS APPEARED TO LACK PENETRATION.  THE AREAS WHERE THE MISSING 3 KEYS WERE ATTACHED ALSO HAD EVIDENCE OF WE	LDS THAT DID NOT MEET THE REQUIREMENTS.  IT IS BELIEVED THAT THE FAILURE OF THE WELDS AND THE SUBSEQUENT LOSS OF THE KEY	S AND SHIFTING OF THE DIAPHRAGM RESULTED IN CONTACT OF THE DIAPHRAGM WITH THE ROTOR AND EVENTUALLY FAILURE OF TIE BOLT.						3	U			E1GL				 
2002112700048	20021127	00048	CE  	2002	11	27	2002FA0001339    	1	20021120	G	3340		SWITCH          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					LANDING LIGHT	MELTED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NE	01	20402					17261261				INOPERATIVE LANDING LIGHT TRACED TO A MELTED SWITCH AND BURNED WIRES AT THE SWITCH.  PROBLEM TRACED TO FLIGHT SCHOOL USI	NG LANDING LIGHT FULL TIME AS A RECOGNITION LIGHT.  SWITCH AND WIRING CANNOT STAND A CONTINUOUS 20 AMP LOAD OF THE 250 W	ATT LAMP.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002112700051	20021127	00051	SO  	2002	11	27	2002FA0001340    	1	20021119	G	7110	6520200	LATCH           			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540*       	41532	EA  					ENGINE COWL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	67180	2    				32121				COWL LATCHES ON RIGHT SIDE OF COWL FAILED DURING IFR FLIGHT AND EMERGENCY LANDING MADE SUCCESSFULLY.  LATCHES HAD BEEN R	EPLACED BEFORE THE TRIP.  THIS IS THE THIRD SET OF HINGES INSTALLED AND ALL FAILED AFTER A FEW HOURS.  THE COWL NOW HAS 	A SET OF OLD SERVICEABLE HINGES WHICH SEEM TO BE HOLDING UP OK.				1	L	7	1 	3O	3	O	 	A3SO    	E295				 
2002112700053	20021127	00053	CE  	2002	11	27	2002FA0001342    	1	20021029	G	5753	122010024	SKIN            			CESSNA	206   	T206H       	2073303	CE  										RT TE FLAP	CRACKED         	B			HLFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	XBACL	171  				08210				RIGHT FLAP SKIN CRACKED AROUND LEADING EDGE INBOARD.						1	H	7	1 	3O			RT	A4CE    					 
2002112700058	20021127	00058	GL  	2002	11	27	2002FA0001343    	1	20021119	G	3250	88341602	CONTROL CABLE   			NAMER 	T6    	T6G         	6400432	GL  	PWA   	R1340 	R1340*      	52016	NE  					NLG STEERING	BROKEN          	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03	7197C					492897				AFTER NORMAL LANDING AND ROLLOUT AIRCRAFT SUDDENLY VERIED RT.  PILOT BRAKED BUT AIRCRAFT NOSED OVER AND CAME TO REST UPS	IDE DOWN.  DURING INVESTIGATION FOUND BROKEN STEERING CONTROL CABLE (LEFT).					1	L	7	1 	3R	3	R	 	A2575   	5E2				 
2002112700065	20021127	00065	GL  	2002	11	27	2002FA0001344    	1	20021107	G	2701	35283001	INDICATOR       			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360*       	41514	EA  					TRIM	SEPARATED       	B			S1FR	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SO	23	367SA	24   				2197				TRIM ARM INDICATOR CAME OFF ACTUATOR STUD AND JAMMED TRIM WHEEL.  CAUSE DUE TO NO RETAINING NUT ON ACTUATOR STUD SCREW. 	 INSTALL RETAINING NUT ON ACTURATOR STUD SCREW.					1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2002112700066	20021127	00066	EA  	2002	11	27	2002FA0001345    	2	20021107	G	8550	62817	SCREEN          			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360*       	41514	EA  					OIL SYSTEM	MISSING         	B			S1FR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	367SA	24   				2197				OIL SCREEN MISSING FROM HOUSING.  MISSING INSPECTORS.						1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2002112700068	20021127	00068	CE  	2002	11	27	2002FA0001346    	1	20021114	G	2820	05160167	FITTING         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					FUEL VENT LINE	CORRODED        	G				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	11	737HV	2668 				17269438	L222326			FUEL ODOR IN CABIN, INSPECTED AND FOUND FUEL LINE COUPLERS UNDER HEAD LINER DRY ROTTED.   ON THE LT SIDE, MFG ROUTED THE	 AIR VENT DUCT (SCAT HOSE)  ON TOP OF THE FUEL VENT LINE CORROSION CREATED A HOLE FROM DAMPNESS AND AGE, FUEL SEEPS THRO	UGH THE HOLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002112700069	20021127	00069	CE  	2002	11	27	2002FA0001347    	1	20021114	G	2820	05560203	FUEL LINE       			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	CORRODED        	G				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	11	9223H	1717 				17266024	L4310627A			FUEL ODOR IN CABIN, INSPECTED AND FOUND FUEL COUPLERS UNDER HEAD LINER DRY ROTTED.  ON THE LEFT SIDE MFG ROUTED THE AIR 	VENT DUCT (SCAT HOSE) ON TOP OF THE FUEL VENT LINE, CORROSION CREATED A HOLE FROM DAMPNESS AND AGE.  FUEL SEEPS THROUGH 	THE HOLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002112700015	20021127	00015	SO  	2002	11	27	2002FA0001348    	2	20021126	G	7414	ES10391586	MAGNETO         			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					LEFT	LACK OF LUBE    	D				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CE	05	112RS	10   	10   							ELECTROSYSTEMS DISTRIBUTOR BLOCK FAILED ON TAKEOFF ROLL APPROXIMATELY 10 HOURS AFTER INSTALLATION. IT APPEARS THAT THE O	IL LIGHT BEARING THAT THE ROTOR SHAFT RIDES IN WAS NOT PROPERLY OIL BEFORE INSTALLATION. THE PART WAS INSTALLED IN THE L	EFT MAGNETO ON THE LEFT ENGINE.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2002112700018	20021127	00018	EA  	2002	11	27	2002FA0001349    	2	20021126	G	7414	1038255511	MAGNETO         			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	DETACHED        	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	05	7510V		61   			177RG0808				ON OCT 12, 2002 AT APPROX. 2030, AIRCRAFT WAS SUBSTANTIALLY DAMAGED WHILE EXECUTING AN ENGINE OUT, GEAR UP, FORCED LANDI	NG, NEAR SOUTH VIENNA, OHIO. PILOT AND PASSENGER WERE SERIOUSLY INJURED. ACCORDING TO THE PILOT, HE WAS CRUISING AT 2500	 FT, WHEN HE NOTICED AN UNUSUAL ODOR AND SHORTLY AFTER THAT, THE ENGINE QUIT. AFTER ATTEMPT TO RESTART THE ENGINE, MADE 	A FORCED LANDING. AIRCRAFT TOUCHED DOWN HARD, BREAKING THE LT WING SPAR AND WRINKLING THE FUSELAGE, EMPENNAGE, FIREWALL 	AND DAMAGING THE PROPELLER. EXAMINATION BY AN FAA SAFETY INSPECTOR, REVEALED THAT THE MOUNTING HARDWARE FOR THE SINGLE M	OUNTED, DUAL MAGNETO WAS MISSING AND THE MAGNETO HAD WORKED LOOSE AND WAS LAYING IN THE ACCESSORY SECTION.	1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2002120300029	20021203	00029	EA  	2002	12	3	2002FA0001350    	1	20021118	G	3230	AN676AC13700	WIRE            			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R1340*      	52016	NE  					MLG	FAILED          	G			GMMG	A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	13	7502A	3679 				797B				LANDING WIRE SEPARATED IN FLIGHT ON RT WING.  AIRCRAFT RETURNED FOR LANDING.  RT WING SETTLED TO RUNWAY AS AIRCRAFT SLOW	ED.  WIRE APPEARS TO HAVE SMALL ELECTRICAL ARC AT FAILURE POINT THAT COULD HAVE CREATED AS STRESS RISER OCCURRENCE ON 8/	28/2002.				1	Q	7	1 	3R	3	R	 	1A16    	5E2				 
2002120300030	20021203	00030	EA  	2002	12	3	2002FA0001351    	1	20020616	G	2730	50893	PULLEY          			WACO  	YMF   	YMF         	9600412	EA  										ELEVATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	53WC	2861 				F5C074				THE INCIDENT OCCURRED ON TAKEOFF ROLL, FORWARD PRESSURE WAS APPLIED TO BRING THE TAIL UP, AT THAT POINT THE CONTROL CABL	E BROKE.  FURTHER INSPECTION SHOWED THAT THE OTHER CONTROL CABLE WAS 50 PERCENT WORN.  IT APPEARED THAT THE PULLEYS COUL	D BE CAUSING THE PROBLEM THROUGH MISALIGNMENT.				1	Q	7	1 	3R			 	ATC542  					 
2002120300031	20021203	00031	EA  	2002	12	3	2002FA0001352    	1	20020901	G	2730	50893	PULLEY          			WACO  	YMF   	YMF         	9600412	EA  	JACOBP	R755  	R755B2      	35007	SW  					ELEVATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	96T	1613 				F5C052	17859			ELEVATOR PULLEYS WORN.						1	Q	7	1 	3R	3	R	 	ATC542  	E237				 
2002120300032	20021203	00032	EA  	2002	12	3	2002FA0001353    	1	20021101	G	2730	50893	PULLEY          			WACO  	YMF   	YMF         	9600412	EA  	JACOBP	R755  	R755B2      	35007	SW  					ELEVATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	43064	1873 				F5C062	15886			ELEVATOR PULLEYS 20 PERCENT WORN.						1	Q	7	1 	3R	3	R	 	ATC542  	E237				 
2002120400002	20021204	00002	SO  	2002	12	4	2002FA0001354    	1	20021127	G	7603	455322	THROTTLE CABLE  			PIPER 	PA28  	PA28R200    	7102811	SO  										FUEL CONTROL	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	3982X					28R7535382				UPON INVESTIGATION FOUND THROTTLE CABLE BROKEN JUST AFT OF FULL CONTROL.						1	L	7	1 	3O			 	2A13    					 
2002120400003	20021204	00003	CE  	2002	12	4	2002FA0001355    	1	20021120	G	5412		FIREWALL        			CESSNA	172   	172N        	2072434	CE  										ENGINE BAY	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	4675G	11166				17273301				DURING ROUTINE INSPECTION FOUND CRACK IN FIREWALL EXT POWER PLUG BEHIND AND RADIATING OUT TO COWL SHOCK MOUNT DOUBLER AN	D TOWARD UPPER LT.  ALSO TOWARD LOWER RIGHT.  THIS COULD BE FROM YEARS OF CONNECTING AND DISCONNECTING EXTERNAL POWER FI	REWALL NEEDS TO BE CHECK CLOSELY THIS IS NOT ALWAYS AN EASY CRACK TO SEE.				1	H	7	1 	3O			NT	3A12    					 
2002120400004	20021204	00004	EA  	2002	12	4	2002FA0001356    	2	20021118	G	7414	03000	DISTRIBUTOR BLK 			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					LT MAGNETO	CONTAMINATED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	4295R					288311014				AIRCRAFT MADE OFF-AIRPORT LANDING JUST AFTER TAKE-OFF, DUE TO LOSS OF POWER.  DURING INVESTIGATION, MAGNETO WAS DISASSEM	BLED AND INSPECTED.  LEFT DIDTRIBUTOR TOWER HAD NR 5 TOWER SPRING MISSING AND CORROSION AT CONTACT, GREASE CONTAMINATION	 WAS NOTED INSIDE DIRTRIBUTOR BLAOCKS AND UNDERNEATH DISTRIBUTOR GEARS MIGRATED FROM CENTER AFT BEARING, SIGNS OF ARCING	 AND FLASH-OVER OBSERVED.			1	L	7	1 	3O	3	O	 	2A13    	E295				 
2002121100034	20021211	00034		2002	12	11	2002FA0001358    	4	20021112	G	2561	AV8AS2100	BOTTLE          																	LIFE VEST	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										CARBON DIOXIDE BOTTLE HOUSING WAS BROKEN DUE TO BLUNT IMPACT FORCE APPLIED.																			 
2002121100035	20021211	00035	SO  	2002	12	11	2002FA0001360    	1	20021202	G	5520	710563	SPRING          			PIPER 	PA31  	PA31325     	7103105	SO  										ELEVATOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	13ES	965  				317812046				THE ELEVATOR BUNGE SPRING PART NUMBER 710563 WAS FOUND BROKEN.  THIS SPRING IS LIFE LIMITED TO 1000 HOURS PER AD 98-08-1	8.  THIS SPRING WAS LAST INSPECTED AT 964 HOURS OF SERVICE.					1	L	7	2 	3O			 	A20SO   					 
2002121100036	20021211	00036	CE  	2002	12	11	2002FA0001363    	1	20021101	G	5330	071378775	SKIN            			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	9669X					18268584				DURING A 100 HOUR INSPECTION, A CRACK WAS FOUND IN THE FUSELAGE SKIN JUST BEHIND THE STEP THAT IS ATTACHED TO THE FUSELA	GE TO AID THE PILOT FOR FUEL CAP INSPECTION OR REFUELING.  THIS STEP IS LOCATED ON BOTH SIDES OF THE AIRCRAFT AT STATION	 17.0 AND IS ATTACHED TO BULKHEADS, LEFT AND RIGHT, THE BULKHEADS HAVE FOUND TO BE CRACKED.				1	L	7	1 	3O	3	O	NT	3A13    	E273				 
2002121100024	20021211	00024	CE  	2002	12	11	2002FA0001367    	1	20021203	G	5524	12346603	SKIN            			CESSNA	210   	210J        	2073439	CE  										LT ELEVATOR	WILL NOT BALANCE	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	25	3368S					21059168				AIRCRAFT REPORTED AS NOT HAVING ENOUGH NOSE DOWN TRIM IN CRUISE FLIGHT. AFTER INSPECTION IT WAS NOTED THAT THE TRAILING 	EDGE OF THE LT ELEVATOR WAS CONTOURED DOWN AND A CHECK OF THE BALANCE SHOWED IT TO BE 'UNDERBALANCED' BY ALMOST TWO INCH	 POUNDS. THE TRAILING EDGE SKIN WAS REMOVED AND FOUND TO BE A REPLACEMENT SKIN THAT HAD BEEN INSTALLED WITH SOME TYPE OF	 EXPANDING FOAM TO FILL THE INTERIOR. THIS REPLACEMENT WAS DESIGNED NOT TO HAVE ANY FILLING DUE TO CORROSION PROBLEMS WI	TH THE ORIGINAL.  NO RECORD OF THE REPAIR WAS FOUND IN THE AIRCRAFT RECORDS. A NEW SKIN WAS INSTALLED, THE ELEVATOR CHEC	KED FOR BALANCE, AND THE AIRCRAFT WAS TEST FLOWN SATISFACTORILY.	1	H	7	1 	3O			 	3A21    					 
2002121100025	20021211	00025	CE  	2002	12	11	2002FA0001368    	1	20021204	G	5711		SPAR CAP        			CESSNA	210   	2105A       	2073406	CE  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	8418Z	2800 				418				INSPECTION MADE DURING INSTALLATION OF SHOULDER HARNESSES REVEALED EXFOLIATION OF AFT CARRY THRU SPAR AND ADJACENT SKINS	.  CENTER RUDDER ATTACHMENT POINT WAS CORRODED TO SUCH AN EXTENT THAT THE AIRFRAME SUCH THAT REMOVAL OF RUDDER WAS POSSI	BLE WITHOUT REMOVING THE CENTER BOLT.  MISSING RIVET HEADS AND BULGING SKIN ALONG THE MAIN WING SPAR UNDER BOTH LEFT AND	 RIGHT FUEL TANKS.  EXFOLIATED SKIN ON HORIZONTAL STABILIZER.  AIRCRAFT SPENT MOST OF ITS LIFE IN COASTAL FLORIDA.  AIRC	RAFT RECEIVED AN ANNUAL INSPECTION 1 MONTH PRIOR TO BEING SOLD AND 2 MONTHS PRIOR TO THE INSPECTION LEADING TO THE DISCO	VERY OF THESE DISCREPANCIES. AIRCRAFT DISASSEMBLED AND RETURNED TO OWNER AS SCRAP.	1	H	7	1 	3O			 	3A21    					 
2002121200001	20021212	00001	SO  	2002	12	12	2002FA0001369    	2	20021104	G	7321		LINKAGE         			BEECH 	33    	3533        	1151402	CE  	CONT  	O470  	IO470*      	17026	SO  					THROTTLE BODY	WORN            	B			QC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	808ZA				3057R	CD202				WHILE TROUBLESHOOTING A ROUGH RUNNING ENGINE, FOLLOWING PROBLEMS WERE FOUND WITH THROTTLE BODY.  LINKAGE FROM THROTTLE A	TTACH ARM TO FUEL CONTROL UNIT WAS EXCESSIVELY WORN.  PIN ON THROTTLE BODY SIDE OF LINKAGE HAS SEVERELY WORN, AND AREA A	ROUND HOLE FOR COTTER PIN WAS VERY THIN.  HOLE IN THROTTLE BODY ARM (THAT RECEIVES THE PIN MENTIONED ABOVE) WAS ALSO WOR	N EXCESSIVELY.  BRASS BUSHING WAS INSERTED BY PREVIOUS REPAIR.  PIN HAD WORN THROUGH BUSHING AND WAS STARTING TO CUT INT	O ARM.  WHILE REMOVING THROTTLE BODY,  FOUND MIXTURE CONTROL ATTACHED TO FUEL CONTROL UNIT WITH INCORRECT HARDWARE.  IT 	WAS ATTACHED WITH A PLAIN NUT.  THERE WAS NO SAFETY OF ANY KIND, AND NUT WAS LOOSE.  MECH SPUN NUT OFF BY HAND.	1	L	7	1 	3O	3	O	 	3A15    	E1CE				 
2002121100026	20021211	00026	CE  	2002	12	11	2002FA0001370    	1	20021204	G	3220	1058200155	PIN             			BEECH 	76    	76          	1153005	CE  										NOSE GEAR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	66363	6397 				ME254				AIRCRAFT TAXIED TO A PARKING SPOT AFTER LANDING. THE NOSE GEAR PIN ROTATED IN THE GEAR LEG CAUSING AN INTERFERENCE WITH 	THE DOWN LOCK HOOK TO ENGAGE WITH THE PIN, NOT ALLOWING THE NOSE GEAR TO BE DOWN AND LOCKED. THE DOWN LOCK HOOK ENGAGES 	TO THE FLAT OF THE DOWN LOCK PIN, BUT SINCE IT ROTATED THE RADIUS OF THE PIN STOPPED THE HOOK FROM LOCKING INTO PLACE. T	HE NOSE GEAR COLLAPSED CAUSING DAMAGE TO THE NOSE GEAR DOORS AND NOSE OF THE AIRCRAFT. WHEN THE GEAR WAS CYCLED DOWN, TH	ERE WERE THREE GREEN INDICATED IN THE COCKPIT AND I VERIFIED THAT THE NOSE GEAR WAS NOT DOWN AND LOCKED LIKE IT SHOULD O	F BEEN.	1	L	7	2 	3O			 	A29CE   					 
2002121100027	20021211	00027	SO  	2002	12	11	2002FA0001371    	2	20021204	G	8530	654967	CYLINDER        			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470J       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2922C	383  	383  			30822	469818JR	681575		SIX CYLINDER SET INSTALLED ON ABOVE ENGINE AT ENGINE TOTAL TIME OF 3605.0 (TSO 381.5). AT ENGINE TOTAL TIME OF 3989.0 HE	AD OF CYLINDER NR 4 SEPERATED FROM BARREL. CYLINDER SENT TCM. TCM REPLACING ALL 6 CYLINDERS.					1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P3EA	 
2002121100028	20021211	00028	SW  	2002	12	11	2002FA0001374    	1	20021206	G	2740	10699	PEDESTAL        			AIRTRC	AT500 	AT502B      	0390307	SW  										HORIZONTAL STAB	CRACKED         	B				O				OTHER                   				O			OTHER                     			AG	AGRICULTURE    	1			SW	07	60518	3246 				502B0346				PEDESTAL WAS FOUND TO BE CRACKED DURING INSPECTION.						1	L	7	1 	3T			NC	A17SW   					 
2002121100029	20021211	00029	NE  	2002	12	11	2002FA0001375    	3	20021206	G	6114	54507	NUT             			AIRTRC	AT400 	AT401       	0390204	SW  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	PROP HUB	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	1008Q	280  	280  			4010702		U23037		A NEWLY OVERHAULED "0" TIME PROPELLER WAS INSTALLED 05/31/01.  DURING MAINTENANCE JULY 5, 2002 THE PROPELLER HAD TO BE R	EMOVED TO FACILITATE OTHER WORK.  DURING THE REMOVAL IT WAS DISCOVERED THAT THE PROPELLER RETAINING NUT WAS CRACKED THE 	FULL HEIGHT OF THE NUT AND IT HAD EXPANDER TO THE EXTENT THE SPECIAL SPLINE WRENCH WOULD NOT FIT OVER THE NUT.  THIS CON	DITION COULD LEAD TO THE LOSS OF THE PROPELLER AND WOULD NOT HAVE BEEN DETECTED UNTIL COMPLETE FAILURE OF THE RETAINING 	NUT.  THE NUT WAS NEW AT THE TIME OF INSTALLATION.		1	L	7	1 	3R	3	R	 	A17SW   	5E2	6	C	P719	 
2002121100030	20021211	00030	NE  	2002	12	11	2002FA0001376    	3	20021206	G	6114	54507	NUT             			AIRTRC	AT400 	AT401       	0390204	SW  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	PROP HUB	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	1008Q	280  	280  			4010702		U23037		A NEWLY OVERHAULED "0" TIME PROPELLER WAS INSTALLED 05/31/01.  DURING MAINTENANCE JULY 5, 2002 THE PROPELLER HAD TO BE R	EMOVED TO FACILITATE OTHER WORK.  DURING THE REMOVAL IT WAS DISCOVERED THAT THE PROPELLER RETAINING NUT WAS CRACKED THE 	FULL HEIGHT OF THE NUT AND IT HAD EXPANDER TO THE EXTENT THE SPECIAL SPLINE WRENCH WOULD NOT FIT OVER THE NUT.  THIS CON	DITION COULD LEAD TO THE LOSS OF THE PROPELLER AND WOULD NOT HAVE BEEN DETECTED UNTILL COMPLETE FAILURE OF THE RETAINING	 NUT.  THE NUT WAS NEW AT THE TIME OF INSTALLATION. PICTURES OF THE NUT ARE AVAILABLE.		1	L	7	1 	3R	3	R	 	A17SW   	5E2	6	C	P719	 
2002121100031	20021211	00031	CE  	2002	12	11	2002FA0001377    	1	20021209	G	5711		SPAR            			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320E2A    	41508	EA  	SNSNCH	74D	74DM        	EA  	WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	11687					31372	L482655A	K33815		WHILE COMPLYING WITH AD 2000-25-02 R1 (WING SPAR INSPECTION) FOUND BOTH FORWARD SPARS CRACKED AT SPAR ROOT. EACH SPAR HA	D TWO CRACKS RUNNING THE LENGTH OF THE WOOD GRAIN AND ADJACENT TO UPPER AND LOWER ATTACH BOLT HOLES. PAINT FROM THE AREA	 HAD TO BE REMOVED PRIOR TO EXPOSING CRACKS. UPPER CRACKS WERE UNDETECTABLE UNTIL WING REMOVAL.				1	H	7	1 	3O	3	O	 	A759    	1E12	5	N	P88614	 
2002121200002	20021212	00002	SO  	2002	12	12	2002FA0001378    	1	20021104	G	2434		BEARING         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					ALTERNATOR	DAMAGED         	B			PNRG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	56887		346  		A116232	287425059				THE FRONT BEARING ON THE ALTERNATOR HOUSING FAILED CAUSING THE HOUSING THERE TO BE DAMAGED, THE BELT TENSIONING STRAP TO	 THE ENGINE CASE TO CRACK AND THE ROTOR TO FALL LOOSE ENOUGH INSIDE THE HOUSING TO DESTROY THE ELECTRICAL GENERATING CAP	ABILITIES OF THE ALTERNATOR.  THE CAUSE OF FAILURE WAS NOT CLEAR, ENGINE/PROPELLER VIBRATION WAS DETERMINED TO NOT BE A 	SIGNIFICANT FACTOR.			1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002121200003	20021212	00003	SO  	2002	12	12	2002FA0001379    	1	20021120	G	1430	680660	COLLAR          			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520*    	17040	SO  					FASTENER	LOOSE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	9130N					4608075				LEFT WING REAR ATTACH FITTING COLLAR FOUND IN RECESS BELOW FITTING.  RIVET LOOSE IN HOLE.  REPLACED WITH OVERSIZE FASTEN	ER AND TORQUED COLLAR.  DISCOVERED DURING ALTERATION FOR ENGINE INSTALLATION.					1	L	7	1 	3O	3	O	RT	A25SO   	E8CE				 
2002121200004	20021212	00004		2002	12	12	2002FA0001380    	4	20021125	G	2562	1104	BATTERY         			CESSNA	525   	525         	2076601	CE  										ELT	CORRODED        	B			FCPR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	523BT					5250311				ELT BATTERY, BATTERY CASE CORRODED AND CRACKED.  ELECTROLYTE LEAK.						1	L	7	2 	4F			RT	A1WI    					 
2002121200005	20021212	00005	GL  	2002	12	12	2002FA0001381    	3	20021127	G	6111	FC76634	BLADE           			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O320  	IO320E1A    	41508	EA  	HARTZL	HCC2Y	HCC2YL1     	GL  	PROPELLER	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	76KF	2934 				15374	L514555A			DURING INSPECTION, MAINTENANCE WAS UNABLE TO DETERMINE COMPLIANCE WITH AD.  DUE TO INADEQUATE RECORDS, PROPELLER WAS SUB	MITTED FOR OVERHAUL AND ALSO TO REPLACE THE HUB IAW AD.  AT DISASSEMBLY, PROP WAS FOUND TO HAVE COLD COMPRESSION ROLLED 	SHANKS.  HOWEVER, DURING PENETRANT INSPECTION OF THE BLADES AS REQUIRED BY O/H MANUAL, BLADE WAS FOUND CRACKED IN THE CO	MPRESSION ROLLED RADIUS.  BLADE WAS SUBMITTED TO MFG FOR EVALUATION.  BLADE IS CRACKED.			1	H	7	1 	3O	3	O	 	A21CE   	1E12	5	C	P920	 
2002121200006	20021212	00006	CE  	2002	12	12	2002FA0001382    	1	20021121	G	2613	115611	OVERHEAT SENSOR 			CESSNA	525   	525         	2076601	CE  										MAIN BATTERY	DEFECTIVE       	B				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	19	525RA					5250167				PILOT REPORTED MAIN BATTERY OVER HEAT LIGHT CAME ON IN FLIGHT.  BATTERY WAS CHECKED AFTER LANDING AND WAS NOT WARM.  BAT	TERY CELLS CHECKED GOOD ND WERE ALL EVEN VOLTAGE.  THE BATTERY OVERHEATED SENSOR WAS FOUND TO BE DEFECTIVE.  PURCHASED N	EW BATTERY AND SENSOR.				1	L	7	2 	4F			RT	A1WI    					 
2002121700001	20021217	00001	SO  	2002	12	17	2002FA0001383    	1	20021203	G	3110		SWITCH          			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6*        	52043	EA  					DISPLAY DIMMER	FAILED          	B			LF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	17LH					4697007				PILOT EXPERIENCED FAILURE OF ALL DISPLAYS IN AIRCRAFT.  AUTOPILOT AND RADIOS APPEARED TO BE OPERATING, BUT NO DISPLAY AV	AILABLE.  COULD NOT DUPLICATE ON GROUND.  CHECKED WIRING AND DIMMING UNIT.  FOUND EVIDENCE OF ARCING ON RING TERMINAL AT	 LOAD CONNECTION.  REPLACED DIMMER UNIT AND RING TERMINAL ON WIRE.  OPS CHECK GOOD.  IT APPEARS THAT RING TERMINAL BECAM	E LOOSE.  THERE WAS NO PLAIN WASHER INSTALLED UNDER THE LOCK WASHER ON SCREW.			1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2002121700019	20021217	00019	EA  	2002	12	17	2002FA0001384    	2	20021212	G	7230		BEARING         			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A6       	52043	EA  					NR 1	FAILED          	G				O				OTHER                   				Y	G	J	ENGINE STOPPAGE           	MULTIPLE FAILURE          	WARNING INDICATION        	DE	DESCENT        	1			GL	19	12WY	1979 				112	PCE111098			A/C EXPERIENCED SUDDEN POWER LOSS & ENG STOPPAGE, AND A EMERGENCY LANDING FROM FL245.  NO EXTERNAL OIL LEAKS, AND OIL LE	VEL WAS DOWN 3 QUARTS FROM FULL.  INSPECT OF THE POWER TURBINE SHOWED FOD AND A SMALL AMOUNT OF MELTED METAL IN THE DUCT	.  PROP SHAFT COULD NOT BE ROTATED.  OIL SCREEN PULLED, FERROUS METAL AND BRONZE LIKE FILINGS WERE NOTED. ENG WAS SPLIT.	  COMPRESSOR HAD DAMAGED BLADES AND ONE MISSING.  COMPRESSOR HAD FORE/AFT AND SIDE TO SIDE PLAY, AND RUBBED WHEN TURNED.	  INSPECT OF THE POWER TURBINE INLET DUCT SHOWED FOD AND SEVERAL TEMP PROBES BROKEN AND MISSING.  INDICATIONS WERE THAT 	THE ENG EXPERIENCED A NR 1 BEARING FAILURE, RESULTING IN FAILURE OF THE COMPRESSOR AND POWER TURBINE WHEELS.	1	L	7	1 	3T	3	T	RT	A60EU   	E4EA				 
2002121700020	20021217	00020	CE  	2002	12	17	2002FA0001385    	1	20020814	G	3230	08421022	BELLCRANK       			CESSNA	310   	310Q        	2074242	CE  										NLG	BROKEN          	B				L				ABORTED APPROACH        				J			WARNING INDICATION        			LD	LANDING        	1			SO	11	120SA	4298 				310Q1041				UPON GEAR EXTENSION, BELLCRANK FAILED. ALL ATTEMPTS TO EXTEND NOSE GEAR FAILED. AIRCRAFT LANDED WITH NOSE GEAR AT 45 DEG	REE ANGLE. DAMAGE TO NOSE GEAR AREA.					1	L	7	2 	3O			 	3A10    					 
2003010600011	20030106	00011	GL  	2003	1	6	2002FA0001386    	1	20021215	G	2821		FUEL TANK       			AMTR  	NUWACO	T10         	       	GL  	JACOBS	R755  	R7559       	35003	EA  					MAIN	BLOCKED         	P				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			SW	99		163  	20   							ENGINE FAILURE DURING CRUISE FLIGHT.  FAILURE DUE TO RIVETS FROM MAIN FUEL TANK CONSTRUCTION BLOCKING FUEL LINE DOWNSTRE	AM OF TANK.  NO FINGER SCREEN INSTALLED AT TANK OUTLET.  RECOMMEND CHECKING OTHER TANKS FOR FINGER SCREENS AND DEBRIS IN	 TANK.				1	B	7	1 	3R	3	R	NC	EXPA1B71	TC121				 
2003010600013	20030106	00013	CE  	2003	1	6	2002FA0001388    	1	20020922	G	3233	R3582517213	ACTUATOR        			BEECH 	36    	A36         	1151604	CE  	LYC   	O540  	TIO540J2B   	 	NE  					NLG	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	17	711AM	3150 				E1487				NLG ACTUATOR ARM FAILED DURING GEAR EXTENSION.  NOSE LANDING GEAR WOULD NOT EXTEND.  AIRCRAFT LANDED.  CAUSING DAMAGE TO	 PROP, GEAR DOORS, SKIN.					1	L	7	1 	3O	3	O	 	3A15    	E14EA				 
2003010600014	20030106	00014		2003	1	6	2002FA0001389    	4	20021204	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  						MCAULY	1A170	1A170E      	GL  	PROPELLER	CRACKED         	B			FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	35339	445  				172S8891				DURING PREFLIGHT INSPECTION, THE PILOT NOTED THE PROPELLER SPINNER WAS CRACKED.						1	H	7	1 	3O			NT	3A12    		5	N	P857	 
2003010600015	20030106	00015	GL  	2003	1	6	2002FA0001390    	3	20021107	G	6114	747621	HUB             													MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	B			L2PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13								747621		CLEANED HUB, PLASTIC MEDIA BLASTED THREADED AREAS, AND EDDY CURRENT INSPECTED.  EDDY CURRENT REVEALED CRACK INDICATION I	N THREADED AREA NR 2 BLADE SOCKET 3RD THREAD INBOARD AFT SECTION, NO FURTHER ACTION TAKEN.															5	C	P3EA	 
2003010600016	20030106	00016	SO  	2003	1	6	2002FA0001391    	2	20021211	G	8530	643766	VALVE GUIDE     								CONT  	O200  	O200A       	17020	SO  					CYLINDER HEAD	MISINSTALLED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11										EXHAUST VALVE GUIDE IS A REPLACEMENT GUIDE FOR EXHAUST VALVE GUIDE.  IN THE ENGINE CYLINDER ASSEMBLY.  WHEN THE EXHAUST 	VALVE GUIDE IS INSTALLED, THE EXHAUST VALVE SPRING RETAINER WILL NOT SEAT PROPERLY OVER THE INSTALLED VALVE GUIDE.  THER	E IS NO IDENTIFIED EXHAUST VALVE SPRING RETAINER THAT WILL CORRECT THIS PROBLEM.   CONTACTED MFG, NO ANSWER OR SOLUTION.									3	O			E252				 
2003010600017	20030106	00017	CE  	2003	1	6	2002FA0001392    	1	20021204	G	3397	M227591618	WIRE            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	IO520*      	17032	SO  					LIGHT SOCKET	BROKEN          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			WP	13	5403M					402B0003				ON TAKEOFF PILOT OBSERVED SMOKE AND SPARK FROM BEHIND INSTRUMENT PANEL.  BROKEN WIRE WAS FOUND FROM POST LIGHT SOCKET CO	NNECTOR.  REPLACED CONNECTOR.  OPS CHECK OF DASHBOARD LIGHTING FOUND, OK.					1	L	7	2 	3O	3	O	 	A7CE    	E5CE				 
2003010600018	20030106	00018	SO  	2003	1	6	2002FA0001393    	1	20021023	G	7160	554294	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					LT ALT AIR DOOR	BROKEN          	D			DF2S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	9290P	2874 				4496019				DURING 100 HOUR INSPECTION FOUND THAT THE FOLLOWING CONTROL CABLE WHERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF SH	ROUD OF SWAGED TOGETHER.  PROBABLE CAUSE MAY BE DUE TO THE WAY THE CABLES ARE ROUTED.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003010600019	20030106	00019	SO  	2003	1	6	2002FA0001394    	1	20021023	G	7160	554545	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					ALT AIR DOOR	BROKEN          	D			DF2S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	9290P	2874 				4496019				DURING 100 HOUR INSPECTION, FOUND THAT THE FOLLOWING CONTROL CABLES WERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF S	HROUD OF SWAGED TOGETHER.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003010600020	20030106	00020	SO  	2003	1	6	2002FA0001395    	1	20021023	G	7602	554544	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					ENG MIXTURE	BROKEN          	D			DF2S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	9290P	2874 				4496019				DURING 100 HOUR INSPECTION FOUND THAT THE FOLLOWING CONTROL CABLES WERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF SH	ROUD OF SWAGED TOGETHER.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003010600021	20030106	00021	SO  	2003	1	6	2002FA0001396    	1	20021023	G	7602		CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					MIXTURE CONTROL	BROKEN          	D			DF2S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	9290P					4496019				DURING 100 HOUR INSPECTION, FOUND THAT THE FOLLOWING CONTROL CABLES WHERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF 	SHROUD OF SWAGED TOGETHER.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003010600022	20030106	00022	SO  	2003	1	6	2002FA0001397    	1	20021023	G	7603	554546	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					THROTTLE CONTROL	BROKEN          	D			DF2S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	9290P	2874 				4496019				DURING 100 HOUR INSPECTION, FOUND THAT THE FOLLOWING CONTROL CABLE  WHERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF 	SHROUD OF SWAGED TOGETHER.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003010600023	20030106	00023	EA  	2003	1	6	2002FA0001398    	2	20020112	G	8530		PUSHROD         								LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	DESTROYED       	B			O3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		5927 	1395 				L2078848A			ENGINE DISMANTLED DUE TO ENGINE FAILURE, FOUND NR 6 PUSHROD FAILED OR BEARING FAILED.  PUSHROD COME OFF NR 6 CRANK JOURN	AL AND DESTROYED ENGINE.										3	O			1E4				 
2003010600024	20030106	00024	SO  	2003	1	6	2002FA0001399    	2	20021204	G	8550		NUT             			CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520A      	17032	SO  					OIL FILTER ADAPT	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	95PY					21058514	1120787AR			LARGE LOCKNUT ON OIL FILTER ADAPTER CAME LOOSE AND OIL WENT OVERBOARD AND THE ENGINE SEIZED.  THE AIRCRAFT LANDED IN A F	IELD.  THE SAFETY WIRE WAS STILL ATTACHED.					1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2002012800050	20020128	00050	CE  	2002	1	28	2002TU65         	1	20020107	G	2722	556545071	ACTUATOR        			CESSNA	500   	550         	2076604	CE  										RUDDER	DAMAGED         	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1200N					5500681				ON PREINSTALLATION INSPECTION, THE MECHANIC NOTICED DAMAGE IN THE ATTACH THREADS ON THE ACTUATOR.  THE BOLT WOULD NOT TH	READ IN EVEN ONE TURN WITH OUT BINDING.  AFTER FURTHER INVESTIGATING IT WAS FOUND TO HAVE PART OF A BROKEN BOLT STILL IN	SIDE THE HOUSING.THIS ACTUATOR WAS JUST OVERHAULED BY THE AVIATION GROUP INC. 231 TIGER WAY PEACHTREE CITY GA 30269 CERT	IFICAT NO. VGOR728L W/O 13614.			1	L	7	2 	4F			 	A22CE   					 
2003032000071	20030320	00071	CE  	2003	3	20	2003F00143       	1	20021030	G	3710		LINE            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312B    	 	WP  					EJECTOR PUMP	CLOGGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	10R					042				DEBRIS WAS DISCOVERED IN THE PRESSURE LINE TO THE EJECTOR PUMP.  THIS CAUSED A LACK OF VACUUM TO THE OUTFLOW VALVES AND 	ALLOWED THE CABIN TO PRESSURIZE ON THE GROUND.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2003032600016	20030326	00016	CE  	2003	3	26	2003F00144       	1	20021111	G	2750	26111441	BRACKET         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					FLAP MOTOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	21	90HL	4291 				208B0693				PRIMARY FLAP MOTOR CB POPPED WHEN SELECTING FULL FLAPS IN FLT.  ON  GROUND PROBLEM COULD NOT BE DUPLICATED, RIGGING CHEC	KED.  FURTHER MAINT INSP REVEALED FORE AND AFT SUPPORT BRACKET, OF FLAP MOTOR, BUCKLING AND COMPLETE TRANSVERSE CRACKS O	F THE AFT SUPPORT BRACKET, WAS CRACKED OUTBOARD AT ATTACHMENT POINT.  ASSY HAD ACCUMULATED 9559 LDGS.  MATERIAL OF FWD A	ND AFT SUPPORT BRACKETS, ARE MADE OF .032 T2024.  THIS MATERIAL WAS SHOWN TO HAD GIVE WHEN HAND PRESSURE WAS APPLIED AFT	ER NEW PART WAS INSTALLED.  DEPLOYMENT OF FLAPS TO FULL AT HIGH AIRSPEEDS, IAW AFM, SHOWED SIGNIFICANT SLOW MOVEMENT OF 	FLAPS TO FULL DOWN IN FLT.  THESE HIGH AERODYNAMIC LOADS PUT UNUSUAL STRESS ON  LIGHTER MATERIAL.	1	H	7	1 	3T	3	T	 	A37CE   	E2NE				 
2003010600027	20030106	00027	CE  	2003	1	6	2003FA0000000    	1	20021126	G	2421	99105921	ALTERNATOR      			CESSNA	210   	T210L       	2073449	CE  										ENGINE	SEIZED          	B			SL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	2317G	3389 				21061485				PILOT REPORTED THAT THE LOW VOLTAGE LIGHT ILLUMINATED ON TAXI.  MECHANIC FOUND THAT THE ALTERNATOR HAD SEIZED AND THE BE	LT HAD BROKEN.  WHEN THE ALTERNATOR WAS REMOVED, THE MECHANIC NOTED THAT THERE WAS A NOTICEABLE CATCH WHILE ROTATION THE	 PULLEY.  ADDITIONALLY ONE OF THE CASE HALF THROUGH BOLTS HAD BACKED OUT SLIGHTLY AND WAS LOOSE.				1	H	7	1 	3O			 	3A21    					 
2003010600028	20030106	00028	CE  	2003	1	6	2003FA0000001    	1	20021126	G	2421	MDW100211	THRU BOLT       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ALTERNATOR	UNDERTORQUED    	B			SL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	9815Z					U20606678	245523			THE ALTERNATOR THROUGH BOLTS SECURING THE FRONT CASE HALF TO THE REAR  CASE HALF WERE FOUND TO HAVE BACKED OUT, ALLOWING	 THE CASE HALVES TO SEPARATE APPROXIMATELY .1250 INCH.  THE THROUGH BOLT RETAINERS AND SAFETY WIRE WERE STILL IN PLACE. 	 THE ALTERNATOR HAD A MANUFACTURING DATE OF 02/00.  THIS IS ONE OF TWO CONDITION REPORTS FILED FROM THIS REPAIR STATION 	WITH THE SAME DEFICIENCY AND MANUFACTURING DATE.  IT IS SUSPECTED THAT THE CASE HALF THROUGH BOLTS WERE NOT TORQUED TO T	HE PROPER SPECIFICATION.		1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003010600029	20030106	00029	CE  	2003	1	6	2003FA0000002    	1	20021126	G	2421	MDW100211	THRU BOLT       			CESSNA	206   	TU206F      	2073353	CE  	CONT  	O520  	TSIO520C    	17040	SO  					ALTERNATOR	UNDERTORQUED    	B			SL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	3160L					U20602815				THE ALTERNATOR THROUGH BOLTS SECURING THE FRONT CASE HALF TO THE REAR CASE HALF WERE FOUND TO HAVE BACKED OUT ALLOWING T	HE CASE HALVES TO SEPARATE APPROXIMATELY .1250 INCH.  THE THROUGH BOLT RETAINERS AND SAFETY WIRE WERE STILL IN PLACE.  T	HE ALTERNATOR HAD MFG DATE OF 02/00.  THIS IS ONE OF TWO CONDITION REPORTS FILED FROM THIS REPAIR STATION WITH THE DEFIC	IENCY AND MFG DATE.  THE CASE HALF THROUGH BOLTS WERE NOT TORQUED TO THE PROPER SPECIFICATIONS.			1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2003010600030	20030106	00030	CE  	2003	1	6	2003FA0000003    	1	20021126	G	2421	99105921	ALTERNATOR      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	SEIZED          	B			SL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	9815Z	98   				U20606678				PILOT REPORTED THAT THE AMMETER WAS SHOWING A DISCHARGE UPON ENGINE STARTUP.  IT WAS DISCOVERED THAT THE ALTERNATOR HAD 	SEIZED AND THE BELT HAD BROKEN.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003010600001	20030106	00001	SO  	2003	1	6	2003FA0000004    	2	20021220	G	8550	CH48109	OIL FILTER      			BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  					ENGINE	BURST           	D				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			SO	13	4575D	21   				D4727	36300D98			AFTER STARTING ENGINE AND PERFORMING A ROUTINE WARM UP. PILOT NOTICED OIL PRESSURE DROPPING. AFTER SHUTDOWN, THE OIL FIL	TER WAS SHOWN TO HAVE PARTIALITY BLOWN OPEN AT THE BASE WHERE IT IS CRIMPED. ALSO THE PRESSURE RELIEF VALVE WAS FOUND TO	 HAVE 14 WASHERS UNDER THE SPRING. THIS ENGINE IS NOT ALLOWED TO HAVE ANY WASHERS. THE OIL FILTER HAD 21 HRS SINCE INSTA	LLATION AND WAS NOT OVER TORQUED. THE ENGINE HAS 1044 HRS. SMOH.			1	L	7	1 	3O	3	O	 	A777    	E267				 
2003010600003	20030106	00003	CE  	2003	1	6	2003FA0000007    	1	20021112	G	3220	C1630050201	WHEEL           			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	471KP	6473 				172RG0798				DISCOVERED CRACK IN THE SEAT FOR THE WHEEL BEARING RACE IN THE NOSE WHEEL HALF DURING ANNUAL INSPECTION.  DEFECT APPEARS	 TO HAVE BEEN CAUSED BY REPEATED INSTALLATION OF THE RACE OVER THE LIFE OF THE WHEEL					1	H	7	1 	3O			 	3A17    					 
2003010600004	20030106	00004	SO  	2003	1	6	2003FA0000008    	1	20021231	G	6321	16420	DISK            			MAULE 	M5    	M5210C      	5460134	SO  										BRAKE ASSY	MISINSTALLED    	D				C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			GL	27	901SP					6180C				PILOT GROUND LOOPED A/C FOR THE SECOND TIME,  FIRST FLIGHT AFTER REPAIRS FROM 1ST GROUND LOOP. PILOT REPORTED IT FELT LI	KE BRAKE WAS LOCKING UP. DISASSEMBLED BOTH WHEEL AND BRAKE ASSY AND FOUND INCORRECT DISCS NR 164020 HAD BEEN INSTALLED B	Y PERSONS UNKNOWN.THIS DISC THICKNESS IS .187 INCH. INSTALLED CORRECT DISC 164-02601 WHICH HAS A THICKNESS OF .250 INCH.	 THE DIFFERENCE IN DIMENSION WAS ALLOWING THE PISTON TO EXTEND TO FAR OUT AND BINDING THE CALIPER.  VISUAL INSPECTION AL	SO SHOWED FLUID SEEPAGE AROUND BOTH PISTONS.  NEW SEALS HAD BEEN INSTALLED AT LAST ANNUAL/15 HOURS PRIOR.		1	H	7	1 	3O			 	3A23    					 
2003011000047	20030110	00047	SO  	2003	1	10	2003FA0000009    	1	20021209	G	3232	1159L41000145	ACTUATOR        			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					MLG	LEAKING         	D				K				NONE                    				K	L		FLUID LOSS                	NO TEST                   		IN	INSP/MAINT     	1			EA	25	464QS	7264 				1264				CREW REPORTED COMBINED HYDRAULIC QUANTITY LOW,  LIGHT ILLUMINATED.  JACKED AIRCRAFT AND PERFORMED GEAR SWING.  FOUND RT 	MLG SIDEBRACE ACTUATOR LEAKING.  REMOVED LEAKING ACTUATOR, INSTALLED OVERHAULED ACTUATOR OF SAME P/N, PERFORMED GEAR SWI	NGS, OPERATIONAL AND LEAK CHECKS GOOD.  SERVICED AND BLED HYDRAULIC RESERVOIRS.  ALL WORK PERFECTLY IAW GAC G IV MSG-3 M	M.  OLD ACTUATOR SENT TO MFG FOR EVALUATION.  AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003011000048	20030110	00048	EA  	2003	1	10	2003FA0000010    	2	20021209	G	8520	LW13884	BEARING         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FWD MAIN	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	914MA	1241 				172S8257	L2843351A			BEARING DELAMINATED PART DEFECT REQUEST PART BE ANALYSED BY MANUFACTURER OR FAA.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003011000049	20030110	00049	CE  	2003	1	10	2003FA0000011    	1	20021203	G	3710		PUMP            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					VACUUM SYS	LEAKING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	356D					340A0745				LOSS OF OIL AND OIL PRESSURE ON RT ENGINE.  TROUBLESHOT FOUND LEAKING FROM VACUUM PUMP BASE.  REMOVED VACUUM PUMP.  FOUN	D PIECES OF OLD GASKET STILL ATTACHED TO MOUNTING PAD WITH A NEW GASKET INSTALLED.  CLEANED MOUNTING BASE, INSTALLED NEW	 VACUUM PUMP GASKET AND REINSTALLED VACUUM PUMP.  INSPECTED OIL FILTER, NO METAL NOTED.  INSTALLED NEW OIL FILTER, SERVI	CED ENGINE WITH OIL.  RAN ENGINE.  OPS AND LEAK CHECKED, OK.  PILOT SAID VACUUM PUMP WAS CHANGED THAT DAY.			1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2003011000050	20030110	00050	CE  	2003	1	10	2003FA0000013    	1	20021218	G	2910	228000113	LINE            			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					HYD POWERPACK	LEAKING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	757PD					R18201251	L21618			THE POWERPACK CONTROL LINE WAS LEAKING HYDRAULIC FLUID, CAUSED BY AN IMPROPER SECURITY AND/OR ROUTING OF THE HYDRAULIC P	OWERPACK CONTROL LINE IN PROXIMITY TO THE MIXTURE CONTROL CABLE.  AREA AROUND THE HYDRAULIC POWERPACK CONTROL LINE SHOUL	D BE INSPECTED UNDER THE PANEL DURING ROUTINE AND ANNUAL INSPECTIONS.				1	H	7	1 	3O	3	O	 	3A13    	E295				 
2003011000053	20030110	00053	CE  	2003	1	10	2003FA0000015    	1	20020930	G	1430		BOLT            			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520*      	17032	SO  					VERTICAL STAB	LOOSE           	B			WWKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4994F					U2060694				INSPECTION IAW AD AND FOUND LOOSE BOLT HOLES FOR VERTICAL STABILIZER ATTACH.  INSTALLED OVERSIZE BOLTS AND DYE CHECK, NO	 CRACKS FOUND, RETORQUED BOLTS DYE PENETRANT INSPECTION ITEMS.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003011000054	20030110	00054	EA  	2003	1	10	2003FA0000018    	2	20021219	G	8520	SL13885M03	MAIN BEARING    								LYC   	O720  	IO720A1B    	41546	EA  					ENGINE	FAILED          	B			BG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17		3    					L25254			AFTER TEST CELL RUN, ENGINE OIL WAS DRAINED AND THE SUCTION SCREEN AND FILTER WAS CHECKED.  A ABNORMAL AMOUNT OF ALUMINU	M WAS FOUND.  UPON DISASSEMBLY, IT WAS FOUND THAT THE FRONT BEARING  HAD FAILED AT THE NR 2 JOURNAL.  THE METAL APPEARED	 TO HAVE DELAMINATED AND TRANSFERRED TO THE CRANKSHAFT THRUST AREA AND CRANKCASE THRUST FACE.									3	O			1E15				 
2003020400231	20030204	00231	SO  	2003	2	4	2003FA0000024    	1	20021130	G	5740		ATTACH FITTING  			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY50614   	54519	EU  					WING	MISINSTALLED    	B			N3DR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	200AB					71				DURING ROUTINE 24-MONTH ULTRASONIC EXAMINATION NOTED ASC-426 (3 PIECE WING ATTACH FITTING) MODIFICATION WAS IMPROPERLY I	NSTALLED.  NOTED THAT DOUBLER WAS TRIMMED TO FIT WING PLANK CUT OUT INSTEAD OF WING PIN DIAMETER.  RECOMMEND ALL OPERATO	RS VISUALLY INSPECT FOR PROPER INSTALLATION AND CONTACT MFG.				2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2003020400237	20030204	00237	EU  	2003	2	4	2003FA0000026    	1	20021209	G	7931	30723742	LINE            			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					2 ENGINE	CRACKED         	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	25	833AV	1237 				181	P101345			DURING CRUISE FLIGHT, NR 2 OIL LIGHT ON MASTER WARNING PANEL CAME ON.  POWER LEVER WAS REDUCED TO IDLE, OIL PRESSURE IND	ICATION CONTINUED TO FALL TO LESS THAN 25 PSI, THIS TOOK APPROXIMATELY 15-20 SECONDS. CHECKLIST WAS CALLED, NR 2 ENGINE 	WAS SHUT DOWN. CREW DEIVERTED FOR LONGER RUNWAY AND MAINTENANCE SERVICES. NO OTHER ABNOMALIES WERE ENCOUNTERED AND EMERG	ENCY WAS NOT DECLARED.  UNEVENTFUL LANDING WAS MADE.  AIRCRAFT WAS TAXIED TO MAINTENANCE BASE. OIL WAS FOUND DRIPPING OU	T OF NR 2 ENGINE COWLING. FURTHER EXAMINATIONS OF ENGINE DISCOVERED CRACK ON OIL PRESSURE SUPPLY LINE TO THE AFT BEARING	 AREA. THE PART WAS REPLACED AND RUN AND LEAK CHECKS COMPLIED WITH. NO LEAKS NOTED AND AIRCRAFT WAS RETURNED TO SERVICE.	2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2003011000055	20030110	00055	CE  	2003	1	10	2003FA0000027    	1	20021219	G	2820		LINE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					FUEL SYSTEM	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	06	739LC	3930 				17270619				FUEL LEAK NOTED CENTER TOP EDGE OF LT DOOR FROM HEADLINER.  FOUND OUTSIDE AIR DUCT CHAFING ON FUEL VENT LINE, CORRODED H	OLE IN LINE.  BOTH LINE AND DUCT REPLACED.  SPIRAL PLASTIC WRAP ADDED TO NEW LINE DUE TO TIGHT AREA ON LT SIDE.  RT SIDE	 INSPECTED, NO PROBLEMS, AS CLEARANCE IS ADEQUATE.  INSPECTION AT LEAST DURING ANNUAL INSPECTIONS SHOULD BE ACCOMPLISHED	.  REQUIRES OPENING HEADLINER TO VIEW DUCT, LINES AND RUBBER HOSE CONNECTIONS.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003011000056	20030110	00056	CE  	2003	1	10	2003FA0000028    	1	20021025	G	3260	363800501	SWITCH          			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					CAM	LOOSE           	D				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			SO	15	2324A	528  				E3124				LANDING GEAR WARNING HORN WAS SOUNDING IN COCKPIT AS A/C WAS TAXIED.  DURING TAKEOFF, LANDING GEAR RETRACTED AS SOON AS 	A/C BROKE GROUND, EVEN THOUGH LANDING GEAR CONTROL SWITCH WAS IN LANDING GEAR (DOWN).  ELECTRICAL T/S ESTABLISHED THAT L	ANDING GEAR CONTROL SWITCH COMMANDING GEAR RETRACTION EVEN THOUGH SWITCH WAS IN DOWN POSITION.  SWITCH WAS REMOVED FROM 	PANEL AND INSPECTED.  CAM, WHICH ACTUATES SWITCH TO RAISE AND LWR LANDING GEAR, INSIDE OF LANDING GEAR CONTROL SWITCH WA	S LOOSE.  CAM IS HELD IN PLACE WITH TWO SET SCREWS WHICH LOCK CAM TO GEAR SELECTOR HANDLE SHAFT.  ONE OF SET SCREWS WAS 	NOT MAKING CONTACT WITH THE GEAR HANDLE SHAFT.  THE OTHER SET SCREW WAS MAKING LIGHT CONTACT.  RIGGED CAM IAW MM.	1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2003020300094	20030203	00094	CE  	2003	2	3	2003FA0000032    	1	20021231	G	5414	1213401	COWLING         			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	11KR					21061249				IT IS POSSIBLE THAT DUE TO NORMAL WEAR OF THE ENGINE COWL CAUSED CONTACT WITH THE NLG DOOR EDGE PREVENTING THE NLG FROM 	FULLY EXTENDING.  IN ADDITION IT IS POSSIBLE THAT DUE TO THE INCORPORATION OF STC SA 5934SW, REMOVING HYDRAULIC POWER FR	OM THE NLG, ACTUATION PREVENTED FORCING THE DOOR ALL THE WAY OPEN WHICH WOULD ALLOW THE GEAR TO FULLY EXTEND.				1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003020300095	20030203	00095	CE  	2003	2	3	2003FA0000037    	1	20021209	G	2913	105932E	COMMUTATOR      			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1A    	41514	EA  					HYD PUMP MOTOR	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	8971M	2321 				177RG0371				PUMP OPERATED SLOWLY.  SENT FOR OVERHAUL WHICH SHOWED THAT MOTOR BRUSHES WERE WORN AND THE COMMUTATOR WAS WORN IRREGULAR	LY.  LED TO SLOW OPERATION OF THE LANDING GEAR.					1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2003020300096	20030203	00096	CE  	2003	2	3	2003FA0000038    	1	20021209	G	3260	20700174	DOWNLOCK SWITCH 			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	8971M	2321 				177RG0371				FOUND THAT RT MLG DOWNLOCK SWITCH TO BE STUCK IN THE CLOSED POSITION WHICH, WHEN COMBINED WITH THE LT MLG DOWNLOCK SWITC	H OPERATING IMPROPERLY, LED TO A LANDING WHERE THE MAIN GEAR COLLAPSED WITH A GREEN DOWN AND LOCKED LIGHT.					1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2003020300103	20030203	00103	EU  	2003	2	3	2003FA0000063    	1	20021209	G	2910	120A9491105AV	RELAY           			GROB  	120   	G120A       	1660208	EU  										HYD SYSTEM	SHORTED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										DURING PROGRESSIVE INSPECTION AND CYCLE OF THE LANDING GEAR WE HAD A FAILURE OCCURED.  FOUND A BAD HYDRAULIC CONTROL REL	AY THAT SHORTED.  BECAUSE OF THAT SHORT, IT ALLOW TO MUCH CURRENT TO FLOW TO PC BOARD AND SHORT OUT BOARD BETWEEN RELAY 	K13 PIN 13 AND 16 TO BOARD PIN 6, RECOMMEND THAT SOME TYPE OF CIRCUIT PROTECTION BE PLACED BEFORE BOARD TO PROTECT FROM 	POWER SPIKES.  PART NEW OUT OF STOCK.			1	L	7	1 	3O			RT	A49CE   					 
2003020300114	20030203	00114	SW  	2003	2	3	2003FA0000072    	1	20021212	G	6410	471201353	GRIP            			BELL  	47    	47G3B1      	1181028	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R BLADE	CRACKED         	B			E5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	8548F					6507				CRACK LIKE INDICATION ON 9TH THREAD INBOARD WHICH EXCEEDS 15 PERCENT.  IAW AD.  PART REJECTED AND RED TAGGED BY REPAIR S	TATION.  OPERATOR STATED PART WAS PURCHASED AS SPARE PRIOR TO AD.  PART DESTROYED BY OPERATOR.					1	G	7	1 	3O	3	U	 	2H3     	E4CE				 
2003020300121	20030203	00121	CE  	2003	2	3	2003FA0000076    	1	20021216	G	3710	442CW	PUMP            			BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720*      	41546	EA  					LT ENGINE VACUUM	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	46MA	283  				LD413				PUMP FAILED UNDER NORMAL OPERATING CONDITIONS.						1	L	7	2 	3O	3	O	 	3A20    	1E15				 
2003020300123	20030203	00123	SO  	2003	2	3	2003FA0000078    	1	20021227	G	3230	16667000	LINK            			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O360  	O360A1D     	41514	EA  					NLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	4188P	4298 				231676	L3041736A			PILOT REPORTED HEARING A BANG WHEN GEAR RETRACTED.  NO NOSE GEAR INDICATION ON GEAR EXTENSION.  UPON LANDING, NOSE GEAR 	DOWN AND LOCKED WITH GREEN LIGHT.  LANDED WITHOUT INCIDENT.  ON INSPECTION, FOUND HYDRAULIC ACTUATOR CONNECTOR LINKS BRO	KEN IN HALF WHICH ALSO RIPPED OPEN BOLT HOLES FOR LOCKING LINK.  REPLACED PART, OPS CHECK GOOD.  SUSPECT FATIGUE FAILURE	.			1	L	7	2 	3O	3	O	 	1A10    	E286				 
2003020300130	20030203	00130	EU  	2003	2	3	2003FA0000083    	1	20021201	G	2121	M3348A1	MOTOR           			SAAB  	SF340 	SF340A      	7850100	EU  										FAN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	ZKNLP									FAN RETURNED TO MFG FOR OVERHAUL.  WHEN FAN WAS TESTED, IT FAILED THE MINIMUM RPM REQUIREMENTS, WHEN IT WAS DISASSEMBLED	, IT WAS DISCOVERED THAT THIS OVERHAULED UNIT HAS NOT BEEN OVERHAULED IAW THE MM.  THE ARMATURE IS NOT OF DAE DESIGN.  O	VERHAUL MANUAL DOES NOT ALLOW FOR THE REWINDING OF THE ARMATURE OR THE REPLACEMENT OF PARTS OTHER THAN LISTED.				2	L	7	2 	4T			RT	A52EU   					 
2003020300136	20030203	00136	SO  	2003	2	3	2003FA0000087    	1	20020806	G	2910	3153601	LINE            			PIPER 	PA23  	PA23250     	7102308	SO  										HYD SYSTEM	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	508UU	2774 				277954001				LANDING GEAR HYDRAULIC FLUID HARD LINE FAILED DUE TO CRACKED FLARE UNDER (B) NUT CAUSING HYDRAULIC FLUID TO BE PUMPED OV	ERBOARD.  RIGHT MLG AND NLG FAILED TO DOWN AND LOCK WITH EMERGENCY CO2 BOTTLE DEPLOYMENT.  AIRCRAFT LANDED WITH THE RT M	LG AND NLG UNLOCKED.  VERY HARD TO INSPECT THIS LINE DURING A ANNUAL INSPECTION DUE TO ITS LOCATION.  SHOULD HAVE A HIGH	 PRESSURE HYDRAULIC HOSE INSTALLED IN THIS POSITION AND MANDATORY REPLACEMENT EVERY TEN YEARS.			1	L	7	2 	3O			 	1A10    					 
2003020300141	20030203	00141	NM  	2003	2	3	2003FA0000092    	1	20021204	G	2822	568126713005	PUMP            			BOEING	737   	737*        	       	NM  										FUEL BOOST	INOPERATIVE     	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01			666  							BOOST PUMP IS INOPERATIVE.  STATOR HAS THREE BLOWN FUSES.  INTERNALLY CORRODED ROTOR CAUSED UNIT TO OVERHEAT AND BLOW FU	SES.  ADDRESS ROTOR CORROSION PROBLEMS WITH MFG.  (JOB NR 172794)					2	L	7	2 	4F			RT	A16WE   					 
2003021800074	20030218	00074		2003	2	18	2003FA0000116    	4	20020103	G	2561	GA1ZP0201101	LIFE VEST       																	CABIN	FAILED          	B			KO1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOAT DEVICE FAILED.  MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-13.  DOM NOV 1984.																			 
2003021800075	20030218	00075		2003	2	18	2003FA0000118    	4	20020412	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	3537B	241  				172S8827				SPINNER BULKHEAD CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800076	20030218	00076		2003	2	18	2003FA0000119    	4	20020524	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  										PROPELLER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	3537B	55   				172S8827				PROPELLER SPINNER CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800077	20030218	00077		2003	2	18	2003FA0000120    	4	20020524	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	3537B	55   				172S8827				SPINNER BULKHEAD CRACKED						1	H	7	1 	3O			NT	3A12    					 
2003021800080	20030218	00080		2003	2	18	2003FA0000123    	4	20020206	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  										PROPELLER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	393SP	950  				172S8290				PROPELLER SPINNER CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800108	20030218	00108		2003	2	18	2003FA0000126    	4	20020307	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  										PROPELLER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	740SP	466  				172S8671				PROPELLER SPINNER CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800110	20030218	00110		2003	2	18	2003FA0000127    	4	20020307	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	740SP					172S8671				SPINNER BULKHEAD, CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800112	20030218	00112		2003	2	18	2003FA0000128    	4	20020411	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  										PROPELLER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	740SP					172S8671				PROPELLER SPINNER, CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800113	20030218	00113		2003	2	18	2003FA0000129    	4	20020411	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	740SP	43   				172S8671				SPINNER BULKHEAD, CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800114	20030218	00114		2003	2	18	2003FA0000130    	4	20020820	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  										PROPELLER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	740SP	187  				172S8671				PROPELLER SPINNER, CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800121	20030218	00121	CE  	2003	2	18	2003FA0000133    	1	20021227	G	3220	HSBG5S	BEARING         			CESSNA	310   	310D        	2074212	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG	SEIZED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	6738T					39038				FORWARD ROD END BEARING (ON INTERMEDIATE ROD FROM LANDING GEAR GEARBOX TO NOSE GEAR) SEIZED, CAUSING ROD END TO SHEAR IT	`S ATTACH RIVETS, ALLOWING ROD END TO PARTIALLY SEPARATE FROM ROD, EFFECTIVELY JAMMING NOSE GEAR.  THIS RESULTED IN A NO	SE GEAR-UP LANDING.  ROD END APPARENTLY SNAPPED DURING LANDING.				1	L	7	2 	3O	3	O	 	3A10    	E1CE				 
2003021400016	20030214	00016	SO  	2003	2	14	2003FA0000139    	2	20020927	G	8520	3979	GEAR            								CONT  	R670  	W6706A      	17016	SO  					CAMSHAFT	WRONG PART      	B			RAQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15							14090			ENGINE STOPPED RUNNING DUE TO A FAILED INTERMEDIATE CAM DRIVE GEAR.  UPON DISASSEMBLY IT WAS FOUND THAT A PN 3979 GEAR F	ROM A TANK ENGINE HAD BEEN SUBSTITUTED FOR THE PN A3062.  AIRCRAFT ENGINE GEAR WHICH SHOULD HAVE BEEN USED.  TANK IGNITI	ON DRIVE GEARS HAD BEEN USED AS WELL IN PLACE OF THEIR AIRCRAFT COUNTERPARTS.  THE TEETH HAD SHEARED FROM THE INTERMEDIA	TE CAM DRIVE GEAR CAUSING THE CAM TO STOP TURNING AND ENGINE QUIT RUNNING.								3	R			E162				 
2003022000002	20030220	00002	EA  	2003	2	20	2003FA0000166    	1	20021108	G	3210	C6UM111010	STRUCTURE       			DHAV  	DHC6  	DHC6        	2802606	EA  										MLG	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										MAIN LANDING GEAR, CRACKED AT TAC OF WELD.  UNKNOWN.  NO OTER APPARENT DAMAGE.						1	H	7	2 	3T			RT	A9EA    					 
2003022000005	20030220	00005	SO  	2003	2	20	2003FA0000170    	1	20021230	G	3010	14565200402	PICCOLO TUBE    			EMB   	145   	EMB145      	3260210	SO  										WING	BENT            	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										PICCOLO TUBE BENT AND CRUSHED.						2	L	7	2 	4F			RT	T00011AT					 
2003031100074	20030311	00074	SO  	2003	3	11	2003FA0000171    	1	20021121	G	3230	AN313A	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NLG DOWNLOCK	MISSING         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	205ER					447995320				THE NOSE LANDING GEAR DOWNLOCK BOLT WAS MISSING,  FOUND BROKEN OFF AT NUTPLATE.  THIS CONTRIBUTED TO AN INADVERTENT NOSE	 GEAR RETRACTION.  BOLT COULD POSSIBLY HAVE BEEN BENT PREVIOUSLY OR LOOSE.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003031100079	20030311	00079	EA  	2003	3	11	2003FA0000179    	1	20020926	G	5230	C6FSM373027	LATCH           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A11      	52043	NE  					CARGO DOOR	UNSECURE        	C				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			EA	17	204SA					402				CARGO DOOR DEPARTED AIRCRAFT.  AFTER INSPECTION OF THE REAR CARGO DOOR UPON ITS RECOVERY, IT WAS NOTED THAT AN ATTEMPT M	AY HAVE BEEN TRIED TO OPEN THE DOOR ON THE AIRCRAFT AND THE DOOR WAS NOT FULLY SECURED WHEN THE AIRCRAFT DEPARTED.  TEST	ING ON THE GROUND SHOWED THAT THE DOOR COULD ONLY BE PARTIALLY SECURED, THE LATCHING PINS WERE PARTIALLY ENGAGED IN THE 	DOOR FRAME.  IT WAS FOUND THAT PRIOR TO THE COMPLETE LATCHING OF THE DOOR, THE LATCHING MECHANISM BECAME HARDER TO TURN,	 GIVING THE IMPRESSION THAT THE DOOR WAS FULLY LATCHED AND SECURED.		1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2003031300009	20030313	00009	CE  	2003	3	13	2003FA0000215    	1	20020514	G	2422	MD2628	INVERTER        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					DIRECTIONAL GYRO	FAILED          	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SO	21	2222C	200  			47416	208B0921				DIRECTIONAL GYRO FAILED DUE TO UNACCEPTABLE INSTALLATION OF A MD26-28 INVERTER WITH ITS 26V AC OUTPUT IN PARALLEL WITH T	HE KG102A 26V AC OUTPUT.  THIS WAS DONE IN ERRO TO BOOST THE CURRENT CAPACITY ON THE 26V AC LINE.  CANNOT PARALLED INVER	TER OUTPUT UNLESS THE CAN BE SYNCHRONIZED, WHICH IS NOT POSSIBLE ON THESE TWO UNITS.  IN THIS INSTALLATION, THE ADDITION	AL CURRENT WAS NOT REQUIRED SINCE THE TWO UNITS DRIVEN BY THE BOOTSTRAP ARE NOT MECHANICAL SYNCHROS BUT HIGH IMP ELECTRO	NIC CIRCUITS.  THE GYRO WAS REPLACED AND THE MD26-28 ELIMINATED.		1	H	7	1 	3T	3	T	 	A37CE   	E2NE				 
2003031300013	20030313	00013	CE  	2003	3	13	2003FA0000219    	1	20020314	G	7810	20179110	EXHAUST PIPE    			ZINAIR	CH2000	CH2000      	9950100	CE  	LYC   	O235  	O235*       	41505	EA  					ENGINE	CRACKED         	B			QE5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	8500Z					201003				ASSEMBLIES ARE CRACKING WITH LESS THAN 100 HOURS IN SERVICE SINCE NEW.  THE CRACKS ARE UNDER THE CABIN HEAT SHROUD AND C	AN NOT BE SEEN UNLESS THE SHROUD IS REMOVED.  NUMEROUS CRACKS HAVE ALSO BEEN FOUND IN OTHER AREAS OF THESE ASSEMBLIES.  	IT IS SUGGESTED THAT THE MANUFACTURER BE CONTACTED IMMEDIATELY WITH THE ABOVE INFORMATION AND RECOMMEND CORRECTIVE ACTIO	N.  UNTIL THE ABOVE IS CORRECTED BY THE MANUFACTURER, IT IS SUGGESTED BY THIS REPAIR STATION THAT THE EXHAUST SYSTEM BE 	PRESSURE CHECKED EVERY TWENTY FIVE (25) HOURS.		1	L	7	1 	3O	3	O	NT	TA5CH   	E223				 
2003040900061	20030409	00061	CE  	2003	4	9	2003FA0000322    	1	20020125	G	7810	12509921	SLIP JOINT      			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					EXHAUST STACK	WORN            	D			JZYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	25AK	445  				T20608010	L10106HA			THERE IS AN EXHAUST ELBOW THAT COMES OFF THE WASTEGATE AND RETURNS TO THE TAILPIPE.  THIS PIPE HAD WORN NEARLY THROUGH A	T THE SLIP JOINT BETWEEN IT AND THE TAIL PIPE.  THE TAIL PIPE WAS WORN TO A SHARP EDGE WHERE THE ELBOW ENTERS THE SLIP J	OINT.  THIS CONDITION WAS NOT VISIBLE UNTIL THE TAILPIPE WAS REMOVED.  PROBABLE CAUSE IT THE VIBRATION BETWEEN THE TWO P	IPES.  THE TAILPIPE NEEDS TO BE REMOVED EVERY 200 HOURS TO INSPECT THIS JOINT FOR DAMAGE.  UNDETECTED, THIS EXHAUST PIPE	 WOULD HAVE FAILED IN A FEW MORE HOURS.  THIS FAILURE COULD HAVE CAUSED AN INFLIGHT FIRE AND POSSIBLE LOSS OF LIFE.		1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2003040900062	20030409	00062	SO  	2003	4	9	2003FA0000323    	2	20020315	G	8520	A50446	CRANKSHAFT      								CONT  	A75   	A75*        	17005	SO  					ENGINE	BROKEN          	B			JZYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09							5641703			OWNER COMPLAINED ABOUT THE ENGINE KNOCKING.  BROUGHT ENGINE TO US FOR INSPECTION.  UPON DISASSEMBLY WE FOUND THE CRANKSH	AFT IN TWO PIECES.  THE CRANKSHAFT WAS BROKEN BETWEEN THE FRONT MAIN JOURNAL AND THE NR 4 ROD BEARING JOURNAL.  ENGINE W	AS OPERATING ON AUTO FUEL.  ENGINE HAD BEEN DISASSEMBLED FOR REPAIR WORK APPROXIMATELY 20 HOURS BEFORE.									3	O			E213				 
2003040900010	20030409	00010	SW  	2003	4	9	2003FA0000325    	1	20020305	G	7400	6891969	CONTROL UNIT    			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					AUTO RELIGHT	INTERMITTENT    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	9984K					45054	CAE832197R			AUTO-RELIGHT SYSTEM ACTIVATES INTERMEDIATELY DURING NORMAL ENGINE OPERATION.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003040900074	20030409	00074	SW  	2003	4	9	2003FA0000338    	1	20020621	G	5320	206033110239	STIFFENER       			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30      	03013	GL  					FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	2064S	2587 				52002				FOUND SUBJECT STIFFENER AND WEB CRACKED DURING MAINTENANCE EVENT.  GAINED ACCESS AND FOUND RIGHT HAND BEAM ALSO CRACKED.	  BEAM AREA WAS HIDDEN UNTIL DISASSEMBLY SHOWED FURTHER DAMAGE.  SUGGEST THAT BETTER ATTENTION IS PAID TO THIS AREA ON I	NSPECTIONS, ESPECIALLY IF HELICOPTER IS SUBJECTED TO A HARD LANDING OR IS USED FOR EXTERNAL LOAD OPERATIONS.  MANUFACTUR	ER COULD MODIFY STIFFENER IN THE CURVED AREA TO STRENGTHEN THE ASSEMBLY.			1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2003041000005	20030410	00005	GL  	2003	4	10	2003FA0000350    	1	20020104	G	2820	281210081	LINE            			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					FUEL SYSTEM	BROKEN          	D			PNRG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	646H					1099				THE TUBE FAILED INSIDE THE FERRULE ON THE ENGINE DRIVEN FUEL PUMP FITTING DUE TO RUBBING AND VIBRATION.  FAILURE WAS FOU	ND AFTER PILOT COMPLAINED OF LOW M.A.P., ABOUT 2 IN HG, AT MAXIMUM OPERATING PERIMETERS, AND FUEL CONSUMPTION LOW.					1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2003041000006	20030410	00006	GL  	2003	4	10	2003FA0000351    	1	20020104	G	2820	281210081	LINE            			ENSTRM	F28   	F28F        	3300412	GL  	LYC   	O360  	HIO360F1AD  	41514	EA  					FUEL PUMP	BROKEN          	D			PNRG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	8626A	1650 				783				THE TUBE FAILED ADJACENT TO FERRULE ON THE ENGINE DRIVEN FUEL PUMP FITTING.  FAILURE WAS FOUND UPON REMOVAL OF THE PART 	FROM THE AIRCRAFT TO PERFORM OTHER MAINTENANCE.  RECOMMEND CHANGING THIS RIDGED LINE TO A FLEXIBLE LINE;					1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2003041000009	20030410	00009	EA  	2003	4	10	2003FA0000355    	2	20021024	G	8530	LW19001	EXHAUST VALVE   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					NR 3 CYL INDER	FAILED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	15	95118					2825812	L2470327A			A/C EXPERIENCED SUDDEN LOSS OF POWER, LANDED SAFELY ON COUNTRY ROAD.  INVESTIGATION FOUND NR 3 CYLINDER LOST 75 PERCENT 	OF EXHAUST VALVE FACE THAT SUBSEQUENTLY TRAVELED THROUGH THE INDUCTION SYSTEM TO REMAINING CYLINDERS.  BROKEN VALVE PART	S FORCED SPARK PLUG TIPS TO CRUSH TO A NO GAP CONDITION.  NR 1 CYLINDER HAD BOTH PLUGS CRUSHED, NR 2 HAD ONE PLUG CRUSHE	D, ENGINE BASICALLY RAN ON 2 CYLINDERS.  PN OF VALVE LW OR SL19001.  ENGINE REPLACED, TEST RUN OPS REVEALED INADEQUATE C	OOLING TO THE NR 3 CYL WITH SAME BAFFLING AS FAILED ENG.  CHT IND REVEALED TEMPS TO BE ABOVE 420 DEGREE TEMPERATURE DROP	 IN OPERATION.  SUSPECT HIGH CHT TEMP CAUSED SHORT LIFE SPAN OF VALVE.	1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003041000010	20030410	00010	CE  	2003	4	10	2003FA0000356    	1	20020917	G	2820	51001101	VENT LINE       			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LT WING	CHAFED          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	09	414ST					414A0614				FUEL RUNNING OUT OF LT VENT WHEN TOPPED OFF.  INSP REVEALED LEFT VENT TUBE HAD A HOLE CHAFED IN IT BY FUEL FILLER PORT S	CREEN.  THIS AIRCRAFT HAD RAM WINGLETS INSTALLED SEVERAL HOURS BEFORE THIS OCCURRED.  LINE MAY HAVE BEEN BENT DURING THI	S INSTALLATION, CAUSING LINE TO CHAFF ON FILLER PORT SCREEN.  INSPECTED RIGHT SIDE WITH NO CHAFING FOUND.  RECOMMEND THI	S LINE TO BE INSPECTED WHEN FUEL TANKS ARE OPENED, OR VISUAL INSPECTION THRU FILLER PORT.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003041000011	20030410	00011	CE  	2003	4	10	2003FA0000357    	1	20021031	G	5610	10138402517	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	B			CGOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	363CA	2067 				BB1250				LEFT WINDSHIELD INNER PLY FAILED INFLIGHT, SPIDER WEB, CRACKED OVER ENTIRE INNER PLY.  FLIGHT CONDITIONS AT TIME, NOT RE	PORTED.  NO OBVIOUS EXTERIOR DEFECTS OR FOD OBSERVED.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003042300052	20030423	00052	SW  	2003	4	23	2003FA0000394    	1	20021122	G	3233	1057005G	ACTUATOR        			MOONEY	M20   	M20J        	5870219	SW  										MLG	FAILED          	D			FR8S	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	23	747CF	4284 	349  			240196				AIRCRAFT LANDING GEAR WOULD NOT FULLY EXTEND WITH MOTOR OR HAND CRANK.  AIRCRAFT LANDED FOLLOWED BY GEAR COLLAPSE, CAUSI	NG DAMAGE TO BELLY, STEP, PROP AND GEAR DOORS.  EXAMINATION REVEALED SEVERAL TEETH GROUND FLAT.  ALL LIMIT SWITCHES APPE	ARS TO FUNCTION NORMAL.				1	L	7	1 	3O			 	2A3     					 
2003050700157	20030507	00157	CE  	2003	5	7	2003FA0000397    	1	20021126	G	3230	12416307	BUMPER BLOCK    			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	DEBONDED        	B			SMTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	5555S	183  				P21000417				LT AND RT MAIN LANDING GEAR SHELL BUMPER DEBONDS, THE BUMPER EDGES CURL OVER PREVENTING MAIN GEAR STRUT FROM MAKING FULL	 DOWN TRAVEL.  THIS CONDITION PREVENTS MAIN GEAR STRUT FROM CONTACTING DOWNLOCKS AND PROPER DOWNLOCK SWITCH ACTUATION, T	HEREFORE AN UNSAFE CONDITION.  IT APPEARS THAT MFG MAY HAVE CHANGED THE COMPOSITION OF THE SHELL BUMPER MATERIAL WHICH D	OES NOT HAVE GOOD BONDING QUALITIES.  (PHOTO)			1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003050900090	20030509	00090	SO  	2003	5	9	2003FA0000434    	2	20021011	G	8530	SA631475	PISTON          								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CONTAMINATED    	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		941  					901094H			ENGINE DISMANTELED DUE TO METAL CONTAMINATION, FOUND NR 2 PISTON BROKEN AT RING LAND ON LOWER SIDE OF ENGINE.											3	O			E5CE				 
2003050800060	20030508	00060	SO  	2003	5	8	2003FA0000435    	2	20021010	G	8520	SA631475	PISTON          								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CONTAMINATED    	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		700  					1684688F			ENGINE DISMANTLED DUE TO METAL CONTAMINATION.  FOUND NR 2 PISTON BROKEN AT TOP SCRAPER RING LAND.											3	O			E5CE				 
2003051400230	20030514	00230	SW  	2003	5	14	2003FA0000467    	1	20021207	G	3897	304316	HEAT TAPE       			GULSTM	111   	111RKWELL   	0144601	SW  										GALLEY	MELTED          	C			RO3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03						460				DURING INSPECTION, TECHNICIANS DISCOVERED MELTED GALLEY DRAIN HEAT TAPE.  WHEN THE TAPE OVERHEATED, IT APPEARS TO HAVE C	AUSED THE INSULATION TO HAVE MELTED.  THIS TAPE WAS INSTALLED IN 1996.					1	L	7	1 	3O			 	A11SO   					 
2003060600037	20030606	00037	CE  	2003	6	6	2003FA0000513    	1	20021202	G	5312	07126151	BULKHEAD        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	7446Q					18261086				WHEN PERFORMING A FULL STALL LANDING THE TAIL TIE DOWN STRUCK THE GROUND (RATHER HARD).  INSPECTION FOUND NO DAMAGE OTHE	R THAN SCUFFING OF THE TIE DOWN RING.  FOUND ALL FIVE NUTS AND BOLTS TO BE TIGHT TO BOTH FINGER PRESSURE AND WRENCH, COM	PLIENCE WITH AD.  WHILE CLEANING AREA AROUND RT RUDDER CABLE HOLE, A POSSIBLE CRACK WAS NOTED AND CONFIRMED.  CRACK ORIG	INATED AT APPROX 11 OCLOCK ON THE HOLE, RADIATING OUTWARD AND UPWARD APPROX .3125 INCH, TO A POINT APPROX .1875 INCH FRO	M UPPER CURVE AT BULKHEAD FLANGE.  STRIKE ON TIE DOWN RING WAS A DIRECT CONTRIBUTOR TO THE DAMAGE FOUND.		1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2003060600053	20030606	00053	SW  	2003	6	6	2003FA0000516    	1	20021101	G	5542	420030507	CAP             			GULSTM	690TP 	690B        	7630516	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					RUDDER	SEPARATED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	77UA	10450	635  			11422				SHORTLY AFTER LEVELING OFF AT A CRUISE ALTITUDE OF 16,000 FT, THE AIRCRAFT MADE A HARD UNCOMMANDED TURN TO THE LEFT AND 	LOST APPROX 1000 FT ALTITUDE BEFORE THE PILOT WAS ABLE TO REGAIN CONTROL.  POST FLIGHT INSPECTION REVEALED THAT THE TOP 	PORTION OF THE RUDDER, RED BEACON, LEAD BALANCE WEIGHT, AND APPROXIMATELY SIX INCHES OF THE RUDDER SKIN WERE MISSING.  M	AINTENANCE RECORDS REVEALED PREVIOUS DAMAGE HISTORY IN THIS AREA WHICH MAY HAVE CONTRIBUTED TO THE SEPARATION.			1	H	7	2 	3T	3	T	 	2A4     	E2WE				 
2003062500030	20030625	00030	EA  	2003	6	25	2003FA0000566    	1	20021218	G	2823	TC173007	SELECTOR VALVE  			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985*       	52008	NE  					FUEL SYSTEM	LEAKING         	C				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	01	233N		269  			976				WITH FUEL SELECTOR VALVE IN OFF POSITION FUEL LEAKS BY VALVE, SLIGHT PRESSURE ON CABLE DRUM ON VALVE MAKES IT WORSE. (SI	DE LOAD)  THIS VALVE MUST BE CHECKED DURING AND ANNUAL, IN THE OFF POSITION AND PUTTING PRESSURE ON DRUM TO SEE IF FUEL 	FLOWS THROUGH VALVE IN THE OFF POSITION.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003091800069	20030918	00069	SO  	2003	9	18	2003FA0000764    	1	20021031	G	3230	487312	SPRING          			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG DOWNLOCK	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	13878					274513				THERE ARE 4 DOWNLOCK HOOK SPRINGS ON EACH GEAR 2 WERE FOUND BROKEN AFTER A RIGHT GEAR COLLAPSED ON ROLLOUT, IT IS UNKNOW	N IF A HARD LANDING WAS MADE PRIOR TO COLLAPSE THERE ARE NO REPLACEMENT TIMES FOR THESE SPRINGS, BUT PROBABLY 1000 HOURS	, WHOULD BE A GOOD IDEA.				1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2003092200004	20030922	00004	EU  	2003	9	22	2003FA0000833    	1	20021210	G	5302		SKIN            			AGUSTA	A109  	A109A2      	0260120	EU  										TAIL BOOM	CORRODED        	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	500WK	3485 				7341				EXTENSIVE CORROSION IN SEVERAL AREAS OF THE TAIL BOOM.  CORROSION UNDER THE LT AND RIGHT SIDES OF THE HORIZONTAL STABILI	ZER THROUTH THE SHEET ALUMINUM.  CORROSION UNDER THE AIRCRAFT, BELOW THE BAGGAGE AREA THROUGH THE SHEET ALUMINUM AND COR	ROSION ON THE ANGLED FITTING IN THE FORWARD VERTICAL STABILIZER.  THE CORROSION WAS FOUND DURING AN ANNUAL INSPECTION OF	 THE AIRCRAFT.			1	G	7	2 	3U			 	H7EU    					 
2003091500025	20030915	00025		2003	9	15	2003FA0000889    	4	20021120	G	6122	4508042	GOVERNOR        			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	MALFUNCTIONED   	F				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			GL	03										PN 4508-042 WAS OF A LOWER THAN SPECIFIED HARDNESS WHEN INSPECTED.  THIS LOWER HARDNESS ALLOWED THE PART TO WEAR AT A FA	STER RATE THAN EXPECTED.  THIS WEAR ALLOWED THE DRIVE SPRING TO DISENGAGE FROM THE DRIVER IN THE PROPELLER GOVERNOR AND 	PERMITTED THE PROPELLER TO OPERATE AT A SPEED FASTER THAN SPECIFIED.  THE PART HAS BEEN IN SERVICE SINCE 1977.				1	L	7	2 	3O	3	O	 	A12SW   	E14EA	5	C	P33EA	 
2003102700043	20031027	00043	EA  	2003	10	27	2003FA0000980    	2	20020502	G	7230	311211703	BEARING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  					COMPRESSOR	DELAMINATED     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	283KA	806  				BB83				BEARING RACE SILVER PLATING DELAMINATED. FOUND SILVER IN MAIN OIL FILTER CHECK AT ROUTINE MFG INSPECTION.  BEARING WAS R	EMOVED FROM SERVICE BY STANDARD AERO AND WARRANTED BY MFG.   ALSO COPPER FLASHING FOR SILVER PLATING WAS ALSO PEELING FR	OM RACE.  MFG SIL ADDRESSED THIS PROBLEM ON THE NR 2 AND NR 3 BEARINGS IN A CERTAIN BATCH THAT THE COPPER FLASHING WAS O	MITTED IN MANUFACTURING. THIS WAS A NR 1 BEARING AND THE COPPER FLASHING WAS PRESENT BUT DELAMINATING.			1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003103000097	20031030	00097	EA  	2003	10	30	2003FA0000996    	2	20021007	G	8520	LW13884M10	MAIN BEARING    			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	CRANKSHAFT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	3450W	503  				32317	L1002040	CH6746E		NEW FRONT MAIN BEARING PN LW13884M010 (6-99 ML-KS) INSTALLED AT ENGINE MAJOR OVERHAUL ON 5/15/00.  ENGINE REMOVED THIS D	ATE FOR METAL CONTAMINATION DV SCREEN AND FILTER.  METAL SOURCE IS FROM MAIN BEARING DELAMINATION.  THIS IS A MANUFACTUR	ING PROBLEM.  FURTHER INVESTIGATION IS NEEDED TO DETERMINE MANUFACTURING ERROR.  ENGINE WAS MOMENTS AWAY FROM A CATASTRO	PHIC FAILURE.   (WP01200304903)			1	L	7	1 	3O	3	O	 	A3SO    	E295	5	C	P920	 
2003111300063	20031113	00063	NE  	2003	11	13	2003FA0001141    	2	20020731	G	8530		ROCKER BOSS     			WSK   	M18   	PZLM18      	9180102	EU  	WSK   	ASZ62 	ASZ62IRM18  	 	NE  					NR 9 CYLINDER	CRACKED         	G				O				OTHER                   				R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			SW	11	6236M					IZ012308	KAD848870			AIRCRAFT COLLIDED WITH THE GROUND WHILE MANEUVERING FOR AERIAL APPLICATION. (FAR 137) EYE WITNESS OBSERVED WHITE SMOKE C	OMING FROM AIRCRAFT BEFORE ACCIDENT.  NR 9 CYLINDER(JNG) EXHAUST ROCKER BOX HAD DEVELOPED A CRACK AND EXHAUST AND OIL BU	RNING FURTHERED BURNED OUT THE CRACK TO APPROX. 1 INCH IN WIDTH.  POLISH PRODUCED ENGINE.  FAA TC-EIONE.(K)				1	L	7	1 	3R	3	R		        	E10NE				 
2003123000073	20031230	00073	NE  	2003	12	30	2003FA0001212    	1	20020717	G	6120	26305	CONTROL HANDLE  			CONAER	LA4   	LA4         	5110302	NE  	LYC   	O360  	O360*       	41514	EA  					COCKPIT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7604L					377				PILOT REPORTED THAT ON APPROACH TO LANDING THAT HE ADVANCED PROP TO FULL RPM AND THE PROP CONTROL LEVER BROKE OFF IN HIS	 HAND,  INSTALLED A NEW PROP CONTROL LEVER.  OLD PART SHOWS EVIDENCE THAT IT WAS CRACKED FOR SOME TIME PRIOR TO THIS, BU	T WENT  UNDETECTED DUE TO A PLASTIC COATING ON THE LEVER.  RECOMMEND A CLOSER INSPECTION THAT WOULD INCLUDE THE REMOVAL 	OF THIS PLASTIC COATING IF A CRACK IS SUSPECTED.			1	H	7	1 	3O	3	O	 	1A13    	E286				 
2003123000058	20031230	00058		2003	12	30	2003FA0001213    	4	20020322	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170*      	GL  	PROP SPINNER	CRACKED         	B			FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	792SP	60   				172S8717				DURING A PREFLIGHT INSPECTION THE PILOT NOTED AN .7500 INCH CRACK IN THE CORNER OF SPINNER BULKHEAD.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2004030400045	20040304	00045		2004	3	4	2004FA0000228    	4	20021217	G	2562	AK450	ELT             			CESSNA	310   	310N        	2074234	CE  										CABIN	FAILED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CE	53	310VD	60   			50035	310N0123				EMERGENCY LOCATOR BEACON FAILED PRIOR TO FIRST ANNUAL CHECK. BATTERIES WERE FINE, BUT UNIT FAILED TO FUNCTION- IT WAS DE	AD ONLY ONE YEAR AFTER INITIAL INSTALLATION.					1	L	7	2 	3O			 	3A10    					 
2004090800170	20040908	00170	SO  	2004	9	8	2004FA0000609    	1	20021115	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA39        	7103902	SO  	LYC   	O320  	IO320*      	41508	EA  					STABILATOR	CORRODED        	D			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	8943Y	3004 				39104				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA 30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C3	3A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERLY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS: AN24-46A (400-932), AN174-22A (402-321).  AND THE TORQUE TUBE. TT3004.			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2004090800168	20040908	00168	SO  	2004	9	8	2004FA0000610    	1	20021025	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360*       	41514	EA  					STABILATOR	CORRODED        	D			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	6613P					241734				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILIATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWI	NG BOLTS:  AN24-46A (400-932), AN174-22A (402-321). THE TORQUE TUBE.			1	L	7	1 	3O	3	O	 	1A15    	E286				 
2004090800171	20040908	00171	SO  	2004	9	8	2004FA0000615    	1	20020919	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					STABILATOR	CORRODED        	D			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	7672Y	3342 				30750				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321). AND THE TORQUE TUBE.  TT 3342.			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2004090800165	20040908	00165	CE  	2004	9	8	2004FA0000618    	1	20021025	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24180     	7102402	CE  	LYC   	O360  	O360*       	41514	EA  					STABILATOR	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	487NM					24835				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321).  AND THE TORQUE TUBE.			1	L	7	1 	3O	3	O	NT	1A15    	E286				 
2004090800178	20040908	00178	SO  	2004	9	8	2004FA0000620    	1	20021010	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					STABILATOR	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	9073P	6132 				244542				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321).  AND THE TORQUE TUBE. TT 6132.			1	L	7	1 	3O	3	O	 	1A15    	E14EA				 
2004090800179	20040908	00179	SO  	2004	9	8	2004FA0000622    	1	20020707	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					STABILATOR	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	8700P	3842 				244146				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321) AND THE TORQUE TUBE.  TT 3842.			1	L	7	1 	3O	3	O	 	1A15    	E14EA				 
2004083100041	20040831	00041	SO  	2004	8	31	2004FA0000625    	1	20020220	G	2740	2020302	TORQUE TUBE     			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					STABILATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5947P					241037				PRIOR TO ANNUAL INSPECTION.  THE RT STABILATOR TIP WAS OBSERVED TO OSCILLATE SEVERAL INCHES.  DURING THE ANNUAL INSPECTI	NG THE RT STABILATOR BEARING, PN 4250383 WAS FOUND TO BE LOOSE.  THIS PROCESS TOOK THREE PEOPLE SEVERAL HOURS TO COMPLET	E.  TO ASSIST IN THE REMOVAL, MAKE-SHIFT LEVER WAS CONSTRUCTED TO HELP IN THE TWISTING OF THE STABILATOR ON THE TORQUE T	UBE.  CORROSION WAS FOUND ON THE STABILATOR TORQUE TUBE AND THE BOLTS, AN175-33A, THAT ATTACH THE STABILATOR TORQUE TUBE	 TO THE HORN ASSY, 20397.  AFTER CORROSION WAS REMOVED FROM BOLTS, OVER .45 MATERIAL WAS REMOVED.  NO RECORD WAS FOUND T	O SUGGEST THAT THE STABILATOR WAS REMOVED PRIOR TO THIS DATE.	1	L	7	1 	3O	3	O	 	1A15    	E295				 
2004083100025	20040831	00025	SO  	2004	8	31	2004FA0000626    	2	20020116	G	8520		CRANKCASE       			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					RIGHT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	35597	519  				348070063	807616R			THE TURBOCHARGER ATTACHES TO THE ENGINE RT CRANKCASE, THROUGH A 21 INCH MOUNTING BRACKET, WHICH ATTACHES TO THE RT AFT E	NGINE MOUNT.  DURING A ROUTINE 100 HR INSPECTION, A 1.75 INCH CRACK WAS FOUND ON THE RT CRANKCASE HALF, RT AFT ENGINE MO	UNT ATTACH.  IT APPEARS THAT OVER TIME, THE FLEXING OF THE TURBOCHARGER INSTALLATION PRODUCES A STRESS CRACK ON THE CASE	 HALF AROUND THE FWD STUD.  IT IS POSSIBLE THAT THIS PROBLEM IS DUE TO HIGH TIME CRANKCASE HALVES AND THE DESIGN OF THE 	TURBOCHARGER MOUNTING.  ENGINE HAS 519.2 HRS SINCE FACTORY REMAN.		1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2004092300091	20040923	00091	SO  	2004	9	23	2004FA0000627    	2	20020116	G	8520		CRANKCASE       			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					ENGINE	CRACKED         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	05	35597	146  				348070063	818407R			THE TURBOCHARGER ATTACHES TO THE ENGINE RT CRANKCASE, THROUGH A 21 INCH MOUNTING BRACKET, WHICH ATTACHES TO THE RT AFT E	NGINE MOUNT.  DURING A ROUTINE 100 HR INSPECTION, A .75 INCH CRACK WAS FOUND ON THE RT CRANKCASE HALF, RT AFT ENGINE MOU	NT ATTACH.  IT APPEARS THAT OVER TIME, THE FLEXING OF THE TURBOCHARGER INSTALLATION PRODUCES A STRESS CRACK ON THE CASE 	HALF AROUND THE FWD STUD.  IT IS POSSIBLE THAT THIS PROBLEM IS DUE TO HIGH TIME CRANKCASE HALVES AND THE DESIGN OF THE T	URBOCHARGER MOUNTING.  IT APPEARS AS THOUGH THIS CRACK HAS BEEN PREVIOUSLY WELDED.  ENGINE HAS 146.6 HRS SINCE FACTORY R	EMAN.	1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2005122800074	20051228	00074	EA  	2005	12	28	2005FA0001607    	1	20021218	G	2823	TC173007	SELECTOR VALVE  			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985*       	52008	NE  					FUEL SYSTEM	LEAKING         	C				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	01	233N		269  			976				WITH FUEL SELECTOR VALVE IN OFF POSITION FUEL LEAKS BY VALVE, SLIGHT PRESSURE ON CABLE DRUM ON VALVE MAKES IT WORSE. (SI	DE LOAD) THIS VALVE MUST BE CHECKED DURING AN ANNUAL IN THE OFF POSITION AND PUTTING PRESSURE ON DRUM TO SEE IF FUEL FLO	WS THROUGH VALVE IN THE OFF POSITION.  (K)				1	H	7	1 	3R	3	R		A806    	5E1				 
2002101100127	20021011	00127	CE  	2002	10	11	3399             	2	20021008	G	7310	6544453	LINE            	CONT        	TSIO360RB1B 	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					ENGINE FUEL	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	6TZ	553  			322262	3449125	322262			FUEL INJECTION LINE TO NR 3 CYLINDER CHAFED BY CLAMP SECURING RUBBER INDUCTION COUPLING FROM INDUCTION SPIDER TO NR 5 CY	LINDER INTAKE TUBE.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002112000030	20021120	00030	CE  	2002	11	20	3739             	1	20021118	G	2701	102933D5ZM2452	SPACER          			BEECH 	36    	A36TC       	1151603	CE  										CONTROL COLUMN	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	09	66885					EA48				THESE BUSHINGS ARE LOCATED BETWEEN THE CONTROL COLUMN TORQUE KNEES, LOCATED BEHIND THE INSTRUMENT PANEL. THE SPACERS WER	E FOUND MISSING WHILE INVESTIGATING EXCESSIVE PLAY IN THE TORQUE KNEES.					1	L	7	1 	3O			 	3A15    					 
2002031300122	20020313	00122	CE  	2002	3	13	441M             	1	20020313	G	2822		WIRE HARNESS    			CESSNA	441   	441         	2076020	CE  										BOOST PUMP	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	441M	6735 				4410032				FOUND CHAFED WIRE THAT HAD BEEN ARCING ON THE BOX THAT SURROUNDS THE BOOST PUMPS TO KEEP THE FUEL IN THE FUEL HOPPER. AB	OUT SIX INCHES FROM WHERE THE BOOST PUMP, CONNECTOR PLUG ENTERS THE INBOARD RIB OF THE WET WING AREA, A WIRE (THE RED WI	RE) HAD BEEN CHAFING ON THE BOX AND CHAFED THROUGH THE INSULATION. A PIN HOLE WAS CREATED IN THE CAN FROM THE ELECTRICAL	 ARCING.			1	L	7	2 	3T			RT	A28CE   					 
2002032700151	20020327	00151	CE  	2002	3	27	441M032002       	1	20020320	G	2897		WIRE            			CESSNA	441   	441         	2076020	CE  										BOOST PUMP	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	441M	6735 				4410032				WIRING FOR FUEL BOOST PUMPS IN EACH WING WERE CHAFED THROUGH TO CONDUCTOR. WIRING HARNESS HAS TWO CONNECTOR PLUGS, ONE T	O EACH BOOST PUMP.  CONNECTOR PLUGS ARE WIRED TO A THIRD, LARGER PLUG THAT CONNECTS TO BULKHEAD PLUG THAT FEEDS THROUGH 	INBOARD MOST RIB IN WET WING AREA.  BOOST PUMPS ARE MOUNTED TO PLATE AND SURROUNDED BY METAL BOX SHAPED CAN WHICH WHEN I	NSTALLED, GETS INSERTED THROUGH HORIZONTAL PANEL WITH NEOPRENE SEALS, TO CREATE THE FUEL HOPPER. BOX LIKE ENCLOSURE FOR 	BOOST PUMPS IS VERY CLOSE TO WHERE THE WIRES EXIT LARGER OF THREE CONNECTOR PLUGS, SO WIRES ARE PUSHING FIRMLY AGAINST T	HE BOOST PUMP BOX LIKE COVER AND ARE CHAFING ON IT.  FOUND AT LEAST ONE WIRE IN EACH WING THAT WAS CHAFED THROUGH.	1	L	7	2 	3T			RT	A28CE   					 
2002042500097	20020425	00097	SW  	2002	4	25	474              	1	20020424	G	5711	5146	SPAR            			BBAVIA	7     	7EC         	2110120	SW  	CONT  	C90   	C9012F      	17009	SO  	MCAULY	1A90	1A90*       	GL  	RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	4351C	5500 	500  			7EC370	46334812	53617		C/W AD 00-25-02R1 FOUND CRACK AT BUTT OF MAIN SPAR JUST UNDER ATTACH FITTING TO FUSELAGE ON R/H WING TRAVELING SEVERAL I	NCHES LONGITUDINALLY AND PARALLEL- SEVERAL RIB NAILS LOOSE ON BOTH WINGS- AIRCRAFT HANGARED FOR SEVERAL YEARS (20)VERY L	OW USEAGE- CAUSE UNKOWN- REPAIR OF WINGS REQUIRED.				1	H	7	1 	3O	3	O	 	A759    	E252	5	N	P842	 
2002040200026	20020402	00026	SO  	2002	4	2	5124             	1	20020401	G	5522	83515002	PLATE           			PIPER 	PA46  	PA46350P    	7104602	SO  										RT ELEVATOR	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	775RD	990  				4622174				ELEVATOR CONTROL PLATE ASSEMBLY HAD 4 OUT OF 7 AN4 RIVETS SHEARED.  NO PREVIOUS DAMAGE HISTORY WAS NOTED IN THE LOGBOOK.						1	L	7	1 	3O			RT	A25SO   					 
2002090400071	20020904	00071	EU  	2002	9	4	5211             	1	20020826	G	3233		SETSCREW        			AMD   	FALC20	FALCON200   	2730150	EU  										MLG STRUT	LOOSE           	B			GQRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	VH-EC					493				A SMALL SET SCREW BACKED OUT OF THE THREADED RING CAUSING THE THREADED RING TO BACK OFF AND LEAVE A SPACE BETWEEN THE TH	READED RING AND THE PISTON. THIS CONDITION CAN BE NOTED WITH THE AIRCRAFT ON JACKS AND PULLING BACK AND FORTH ON THE COM	BO STRUT. A SLUNKING SOUND WILL BE HEARD AND FELT IF A LOOSE CONDITION IS PRESENT. THE SET SCREW HAD NOT BEEN INSTALLED 	PROPERLY NOR STACKED ENOUGH TO PREVENT BACKING OUT. IF THE THREADED RING CONTINUES TO BACK OFF OR UNSCREW FROM THE PISTO	N THE LANDIN GEAR COULD COLLAPSE.		2	L	7	2 	4F			RT	A7EU    					 
2002050600150	20020506	00150	CE  	2002	5	6	53550            	1	20020305	G	3210		STIFFENER       			CESSNA	650   	650         	2076802	CE  										NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	397CW					6500107				LT AND RT OUTBOARD NOSE GEAR TRUNNION SUPPORT STIFFENERS ARE CRACKED 4 INCHES AFT OF FS 94.0  REPAIRED BY REPLACING DOUB	LERS 6213011-139 AND 6213011-140.  POSSIBLY CAUSED BY INCORRECT TOWING PROCEDURES.					2	L	7	2 	4F			 	A9NM    					 
2003010600031	20030106	00031	SO  	2003	1	6	56724            	1	20021219	G	5740	ASC426	FITTING         			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY50614   	54519	EU  					WING	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	200AB					71				WHILE PERFORMING AND NDT INSPECTION IT WAS BROUGHT TO OUR ATTENTION THAT THERE APPEARED TO BE MORE THAN NORMAL SPACING B	ETWEEN THE WING CLOTHESPIN FITTING AND THE DOUBLER PLATE THAT WERE MODIFIED IAW ASC.   UPON INSPECTION WE DETERMINED THA	T THERE WAS A GAP BETWEEN THE PARTS THAT SHOULD NOT BE THERE. WE HAVE CONTACTED THE MANUFACTURER AND HAVE RECEIVED AN EN	GINEERING ORDER ADVISING THAT THE INSTALLATION OF THE ASC 426 WAS IN FACT, NOT DONE CORRECTLY. WE ARE IN THE PROCESS OF 	DISASSEMBLING THE AREA IAW THE MANUFACTURERS INSTRUCTIONS FOR THE PURPOSE OF  REQUESTED NDT TESTING AND INSPECTION AND I	NTEND TO CORRECT THE DEFECTS AS ADVISED BY THE AIRCRAFT MANUFACTURER.	2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2002050600113	20020506	00113	CE  	2002	5	6	609170           	1	20020501	G	7910	M832481117	O-RING          			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					OIL CAP	SPLIT           	B				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SO	15	717JH					0138	87397			LEFT ENGINE WAS SHUTDOWN IN FLIGHT AFTER LOW OIL PRESSURE ANNUNCIATION ILLUMINATED.  FOUND O-RING ON OIL FILLER CAP SPLI	T.					2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2002112000089	20021120	00089	WP  	2002	11	20	778              	2	20021117	G	7320	7221493	CONTROL CABLE   			LKHEED	1329  	132925      	5263125	SO  	ALIDSG	TFE731	TFE7313AR   	 	WP  					FUEL CONTROL	BROKEN          	C				O				OTHER                   				P			NO WARNING INDICATION     			DE	DESCENT        	1			WP	07	95BD	7963 	7963 			5208	78121			NR 1 ENGINE TELEFLEX CABLE BROKE INSIDE ITS HOUSING MAKING IT IMPOSSIBLE FOR THE PILOTS TO HAVE CONTROL OF THE ENGINE AS	 FAR AS MAKING CHANGES TO THE SPEED AND FOR SHUTTING THE ENGINE DOWN IN THE NORMAL MANNER. THE PILOTS SHUT THE ENGINE DO	WN USING THE FIREWALL SHUTOFF AND LANDED WITHOUT INCIDENT.				2	L	7	4 	4F	4	F	 	2A1SO   	E6WE				 
2002091100091	20020911	00091	CE  	2002	9	11	A152             	1	20020909	G	2897		WIRE            			BEECH 	90    	E90         	1152914	CE  										FUEL PANEL	CORRODED        	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	15	5462G					LW69				DURING INSPECTION OF FUEL PANEL DIODES: FOUND FUEL PANEL DIODES AND WIRING CONNECTION CORRODED: CLEANED , TREATED AND RE	INSTALLED PANEL.					1	L	7	2 	3T			 	3A20    					 
2002012300047	20020123	00047	SW  	2002	1	23	AC2A077546       	1	20020107	G	6410	206310105101	BEARING         		206016201131	BELL  	206   	206B3       	1181506	SW  										T/R BLADES	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	71319	788  			CS7008	4112				TAIL ROTOR BLADE BEARINGS WERE WORN BEYOND LIMIT. REPLACED WITH NEW BEARINGS.						1	G	7	1 	3U			 	H2SW    					 
2002012300048	20020123	00048	SW  	2002	1	23	AC2A077548       	1	20020107	G	6410	206010733003	SLEEVE          		206016201131	BELL  	206   	206B3       	1181506	SW  										TAIL ROTOR BLADE	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	71319	788  			CS7008	4112				SLEEVES WERE WORN IN TAIL ROTOR ASSY. REPLACED WITH NEW SLEEVES.						1	G	7	1 	3U			 	H2SW    					 
2002101100130	20021011	00130		2002	10	11	AC2A081089       	4	20020401	G	3140	430375002107	DISPLAY         			BELL  	430   	430         	1182150	SW  										COCKPIT	FAILED          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	46   				49037				EHSI SCREEN FAILED TO ILLUMINATE REPLACED WITH SERVICEABLE EFIS TUBE.						1	G	7	2 	3U			RT	H9SW    					 
2002101100135	20021011	00135	NE  	2002	10	11	AC2A081090       	2	20020401	G	7320	430360055101	SOLENOID        			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					NR 1 ENGINE	DEFECTIVE       	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CM	26   				49090				SOLENOID IS DEFECTIVE.  SNAP RING ON SHAFT UNDER THE SPRING DOES NOT STAY IN GROOVE. REPLACED SOLENOID.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2002101100137	20021011	00137	SW  	2002	10	11	AC2A081107       	1	20021001	G	3211	601025015	CLAMP           			BELL  	206   	206L3       	1182108	SW  										MLG	BROKEN          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159J					51408				DURING RETORQUE OF LANDING GEAR SADDLE CLAMP, THE "T" BOLT BROKE IN TWO. UPON EXAMINATION IT WAS EVIDENT THAT THE CLAMP 	WAS CRACKED PRIOR TO BREAKING. REPLACED CLAMP WITH NEW PART.					1	G	7	1 	3U			 	H2SW    					 
2002102300068	20021023	00068	NE  	2002	10	23	AC2A081172       	2	20021013	G	7261	23063372	SEAL            			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	LEAKING         	H			AC2A	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	5447C					760180				ENGINE STARTED LEAKING OIL AFTER OIL FLOW CHECK. REPLACED SEAL						1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2002121100039	20021211	00039	SW  	2002	12	11	AC2A081580       	1	20021130	G	3340	729144501283	CONTROLLER      			BELL  	430   	430         	1182150	SW  										SEARCH LIGHT	FAILED          	H			AC2A	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	430CV	211  				49072				SEARCH LIGHT WILL NOT STOW. REPLACED WITH SERVICEABLE SEARCH LIGHT ASSEMBLY.						1	G	7	2 	3U			RT	H9SW    					 
2003010300003	20030103	00003	SW  	2003	1	3	AC2A082140       	1	20021210	G	3350	214175140101	POWER SUPPLY    			BELL  	430   	430         	1182150	SW  										CABIN	MALFUNCTIONED   	H			AC2A	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	430CT	866  				49089				POWER SUPPLY WILL NOT CHARGE BATTERIES. REPLACED POWER SUPPLY.						1	G	7	2 	3U			RT	H9SW    					 
2002062100013	20020621	00013	EA  	2002	6	21	AG2R04230201     	2	20020423	G	8520	SL738190	BUSHING         								LYC   	O720  	IO720D1C    	41546	EA  					COUNTER WEIGHT	FAILED          	B			AG2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		250  								COUNTER WEIGHT BUSHINGS (PN LS73810) HAVE FAILED AT 2 TO 250 HOURS.  IT APPEARS THAT THE MATERIAL MAY BE TOO SOFT.  BUSH	INGS WERE REMOVED BY OPERATOR AND SENT BACK FOR EVALUATION.										3	O			1E15				 
2002062500004	20020625	00004	GL  	2002	6	25	ALGA079296       	2	20020528	G	7210	6895007	BEARING         		23063393    	BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	GALLED          	H			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	577AL	683  			CAG47062	53247				T/M JOURNAL AND INNER RACE FOUND EXCESSIVE GALLING, CAUSING METAL CONTAMINATION.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002072200166	20020722	00166	SW  	2002	7	22	ALGA080392       	1	20020718	G	2840	206063656001	TRANSMITTER     			BELL  	206   	206L1       	1182107	SW  										FUEL INDICATOR	DEFECTIVE       	H			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	3185P					45775				FUEL GAUGE FLUCTUATING DUE TO TRANSMITTER BEING DEFECTIVE.						1	G	7	1 	3U			 	H2SW    					 
2002121700021	20021217	00021	GL  	2002	12	17	ALGA081610       	2	20021210	G	7250	23066744	WHEEL           			CLARK 	1000  	1000CLARK   	2230102	SW  	ALLSN 	250C  	250C30      	03013	GL  					TURBINE SECTION	MISMANUFACTURED 	H			ALGA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	PARTO									THIS IS A NEW PART. PART CAN NOT BE DYNAMIC BALANCED, DUE TO BEING TOO HIGH OUT OF BALANCE AND OFF SCALE ON THE X10 SCAL	E AND ON UPPER SCALE.					1	Q	7	1 	3R	3	U	 	2A6     	E1GL				 
2002121700026	20021217	00026	SW  	2002	12	17	ALGA081621       	1	20021211	G	6230	204010904001	SLEEVE          		412010402109	BELL  	412   	412         	1182202	SW  										SWASHPLATE	WORN            	H			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	XAAAR	1753 			RE741	36255				SLEEVE BORE INNER DIAMETER MEASURES 0.011 INCH OVER MAXIMUM ALLOWED WITH ONLY 1753.2 HRS. (ORIGINAL EQUIPMENT) THIS PART	 HAS A 9000 HR. RETIREMENT LIFE.					1	G	7	2 	4U			 	H4SW    					 
2002121700029	20021217	00029	SW  	2002	12	17	ALGA081624       	1	20021211	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	H			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	409AL	1175 				53494				FOUND BEARINGS WORN. BEARING HAS A 5000 HR. RETIREMENT LIFE.						1	G	7	1 	3U			O	H2SW    					 
2002121700034	20021217	00034	SW  	2002	12	17	ALGA081630       	1	20021211	G	6320	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	WORN            	H			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	577AL	825  				53247				COOLER BLOWER BEARING IS ROUGH IN ROTATION.						1	G	7	1 	3U			O	H2SW    					 
2002020500192	20020205	00192	CE  	2002	2	5	AUS20020002      	1	20020102	G	5711	05230142	SPAR            	            	            	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FORWARD SPAR ASSEMBLY CONTAINED SEVERE EXFOLIATION CORROSIONBETWEEN THE SPAR PNO 0523014-2 AND THE ATTACHMENT PLAT	E PNO 0523016-1. THE THICKNESS OF THE ASSEMBLY WAS REDUCED BY APPROXIMATELY 50% DUE TO THE CORROSION. THE RIVETS HOLDING	 THEASSEMBLY TOGETHER WERE ALSO CORRODED (18OF22). CORROSION WAS ALSO FOUND AT RIB TO SKIN INTERFACES. INVESTIGATION OF 	OTHER SIMILAR WINGS HELD IN STORAGE FOUND THEM TO BE IN A SIMILAR CONDITION.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002020600060	20020206	00060	CE  	2002	2	6	AUS20020003      	1	20020102	G	5220		DOOR            			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	EMERGENCY EXIT	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EMERGENCY EXIT INCORRECTLY INSTALLED. ONLY TWO OF THREE LATCHING PINS ENGAGED. EMERGENCY RELEASE CABLE LOOPED AND 	THE TWO LATCHING PINS WERE FITTED BACKWARDS. IT WOULD HAVE BEEN IMPOSSIBLE FOR THE EMERGENCY EXIT TO BE RELEASED.					1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P5EA	 
2002020500196	20020205	00196	EA  	2002	2	5	AUS20020008      	2	20020103	G	8520	AS13884M03	BEARING         	LYC         	IO540E1B5   	GULSTM	500   	500U        	0141108	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3X	HCA3XK2     	GL  	RECIPROCATING EN	DELAMINATED     	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE NO1 MAIN BEARING DELAMINATED. METAL CONTAMINATION OF OIL FILTERS.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P913	 
2002020600084	20020206	00084	SO  	2002	2	6	AUS20020012      	1	20020102	G	5510	9735500	BOLT            	PIPER       	LIFTSTRUT   	PIPER 	PA36  	PA36285     	7103610	SO  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAILPLANE LIFT STRUT CLEVIS BOLT CRACKED IN AREA OF FIRST THREAD ON THE HEAD END OF THE BOLT.						1	L	7	1 	3O	3	T	 	A10SO   	E4EA	6	C	P15EA	 
2002020600086	20020206	00086	SO  	2002	2	6	AUS20020015      	2	20020109	G	7414	10349367	IMPULSE COUPLING	BENDIX      	10349505    	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L039021F					(AUS) MAGNETO IMPULSE COUPLING FLYWEIGHTS WORN BEYOND LIMITS.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002020500198	20020205	00198	GL  	2002	2	5	AUS20020017      	3	20020107	G	6110	1949	PROPELLER       	HARTZL      	HCE2YK2RB   	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSEMB	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		267  		1949					(AUS) PROPELLER BLADE CLAMP BOLTS NOT IN SAFETY. NO SPACERS BETWEEN SPINNER BACKPLATE AND PROPELLER HUB. PROPELLER BLADE	S CONTACTINGBACKPLATE WHEN BLADE IS IN THE FEATHER POSITION.PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2002020600096	20020206	00096	EA  	2002	2	6	AUS20020018      	2	20020107	G	8530	LW12425	CYLINDER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	ENGINE	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE NR 2 CYLINDER OUT OF ROUND. NR 5 CYLINDER BORE STEPPED AND BLUE MARKING ON FINS. NR 1 CYLINDER IS MARKED	 AS NITRIDED BUT IS ACTUALLY A CHROMED CYLINDER. RT ENGINE NR 4 CYLINDER NOT ENTERED ON RELEASE NOTE. NR 2 CYLINDER IS N	OT MARKED ORANGE FOR CHROMED. CYLINDER SN A3104 DOES NOT EXIST IN THE PAPERWORK.				1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2002021400004	20020214	00004	NE  	2002	2	14	AUS20020019      	2	20020111	G	7310	30J228501	LINE            			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					FUEL SYS	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE HEAT EXCHANGER FUEL TUBE LEAKING. FUEL SPRAYING INSIDE COWLS AND ENTERING ENGINE THROUGH INTAKE.						1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2002020500199	20020205	00199	NE  	2002	2	5	AUS20020020      	1	20020107	G	2560		FLOAT           	            	            	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  	 		            		EMERGENCY EQUIPM	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 	 									(AUS) AIRCRAFT SUFFERED AN UNCOMMANDED INFLATION OF THE REAR CELLS OF THE NOSE FLOATATION BAGS. THE FLOAT SYSTEM WAS NOT	 ARMED AT THE TIME.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002020500200	20020205	00200	NE  	2002	2	5	AUS20020022      	2	20020111	G	7320	3031829	PIPE            	PWA         	PT6A65AG    	AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	FUEL CONTROLLING	CRACKED         	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 	 				PCE32620					(AUS) P3 PIPE TO FUEL CONTROL UNIT CRACKED.						1	L	7	1 	3T	4	T	NC	A19SW   	E4EA	6	C	P44GL	 
2002020500201	20020205	00201	EU  	2002	2	5	AUS20020023      	1	20020107	G	5743		FITTING         	            	            	MUDRY 	10    	CAP10B      	0950102	EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	WING, LANDING GE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		990  							(AUS) LH AND RH FORWARD LANDING GEAR ATTACHMENT BLOCKS CRACKED. FOUND DURING INSPECTION IAW AD/CAP10/3.						1	L	7	1 	3O	3	O	 	A36EU   	1E10	5	N	P3EU	 
2002020600099	20020206	00099	SO  	2002	2	6	AUS20020024      	2	20020107	G	7310	630626	BALANCE TUBE    			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  					FUEL DIST	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			940  							(AUS) ENGINE BALANCE TUBE FRACTURED AT WELD JOINT. NR 3 CYLINDER INOPERATIVE AND PROPELLER BLADE LOOSE.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002020500202	20020205	00202	SO  	2002	2	5	AUS20020025      	2	20020103	G	7414	1051675	CONDENSER       	BENDIX      	S6RN25      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MAGNETO/DISTRIBU	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 									(AUS) MAGNETO CONDENSER FAULTY. A TOTAL OF FIVE CONDENSERS FAILED INAPPROXIMATELY 500 HOURS OF OPERATION. INVESTIGATION 	FOUND THATTHE FAILURE OCCURRED IN THE SMALL ATTACHMENT BRACKET HOLDING THECONDENSER IN THE POINTS CAVITY.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002020600100	20020206	00100	CE  	2002	2	6	AUS20020026      	1	20020110	G	2430		LIMITER         			CESSNA	441   	441         	2076020	CE  										ELECTRICAL	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 										(AUS) DURING ENGINE EMERGENCY SHUTDOWN THE NR 2 ELECTRICAL SYSTEM BUS LIMITERS (225A) FAILED.						1	L	7	2 	3T			RT	A28CE   					 
2002020600101	20020206	00101	CE  	2002	2	6	AUS20020027      	1	20020110	G	7920	124F0018CR0194	HOSE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT ENGINE OIL	RESTRICTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE OIL COOLER SCAVENGE HOSE INTERNALLY RESTRICTED. SUSPECT HOSE COULD HAVE BEEN KINKED DURING ENGINE INSTAL	LATION.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2002020600102	20020206	00102	CE  	2002	2	6	AUS20020028      	1	20020114	G	5280	9981003034	DOOR            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					MLG	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOOR SEPARATED FROM AIRCRAFT DUE TO FAILURE OF THE HINGE PIN.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002020600122	20020206	00122	SO  	2002	2	6	AUS20020033      	1	20020116	G	5341	97101301	FITTING         			PIPER 	PA36  	PA36375     	7103620	SO  	LYC   	O720  	IO720D1C    	41546	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FRONT SPAR ATTACHMENT FITTING ON FUSELAGE LOCATED AT RT STN 124.250 CRACKED IN REAR LAMINATE. CRACK LENGTH 10MM	 (0.39IN).					1	L	7	1 	3O	3	O	 	A10SO   	1E15				 
2002030600007	20020306	00007	SO  	2002	3	6	AUS20020037      	2	20020117	G	8500	810533R	BEARING         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			449  							(AUS) ENGINE MAKING METAL. SUSPECT DEFECTIVE BEARINGS.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002030400126	20020304	00126	EU  	2002	3	4	AUS20020041      	1	20020118	G	2150	2676C010	DUCT            	            	            	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		CABIN COOLING SY	CRACKED         	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 	 									(AUS) NO2 AIR CYCLE MACHINE INLET PIPE CRACKED.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2002030400127	20020304	00127	EU  	2002	3	4	AUS20020044      	1	20020121	G	8000	S1991A1	RELAY           	LYC         	AEIO360B2F  	MUDRY 	10    	CAP10B      	0950102	EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	ENGINE STARTING	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 									(AUS) STARTER RELAY FAULTY.						1	L	7	1 	3O	3	O	 	A36EU   	1E10	5	N	P3EU	 
2002030400128	20020304	00128	SO  	2002	3	4	AUS20020046      	1	20020118	G	2731	6270142	CABLE           	            	            	PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ELEVATOR TAB CON	FAILED          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 	 									(AUS) STABILATOR TRIM CABLE SEPARATED AT ELECTRIC TRIM SERVO ACTUATOR.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2002030600031	20020306	00031	SO  	2002	3	6	AUS20020047      	1	20020122	G	3260		BRACKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR MICROSWITCH MOUNT BRACKET MOVED. MICROSWITCH OUT OF ADJUSTMENT.  BRACKET HAD BEEN REMOVED DUR	ING DRAG BRACE REPLACEMENT.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002030400129	20020304	00129	SO  	2002	3	4	AUS20020048      	2	20020116	G	8520		CONNECTING ROD  	CONT        	TSIO520E    	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		DE	DESCENT        	1			AU	S 	 									(AUS) RH ENGINE INTERNAL FAILURE. INSPECTION FOUND HOLES IN THE FORWARD END OF THE CRANKCASE IN THE AREA OF NO5 AND NO6 	CYLINDERS. ON DISASSEMBLY MASSIVE INTERNAL DAMAGE FOUND. CONNECTING ROD FOUND IN SUMP. CAMSHAFT BROKEN. SUSPECT CONNECTI	NG ROD OR CONNECTINGROD BOLT FAILURE.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002030400130	20020304	00130	CE  	2002	3	4	AUS20020049      	1	20020118	G	3233	JRA4582	ACTUATOR        	            	            	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	LANDING GEAR ACT	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				BATCH2					(AUS) MAIN LANDING GEAR ACTUATOR HAS NO PROVISION FOR SEPARATION WASHER AND FELT.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2002030400131	20020304	00131	NM  	2002	3	4	AUS20020050      	1	20020123	G	2824	BACC63CE14S5S	PLUG            	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUEL TRANSFER VA	FAULTY          	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 	 									(AUS) FUEL CROSSFEED VALVE CONNECTOR PLUG AND WIRING FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030400132	20020304	00132	CE  	2002	3	4	AUS20020051      	1	20020122	G	2430	S19432	CABLE           	            	            	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	DC GENERATING SY	WORN            	W			    	K	 	 	 	NONE                    				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 	 									(AUS) ALTERNATOR OUTPUT CABLE ARCING ON ALTERNATOR GROUND CABLE. CABLEHAD BEEN REMANUFACTURED FROM MIL-W-22759/16-4 MATE	RIAL.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002030600033	20020306	00033	WP  	2002	3	6	AUS20020052      	2	20020116	G	7321	8977801A	FUEL CONTROL    			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	FAULTY          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			3673 							(AUS) FUEL CONTROL UNIT FAULTY.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2002030600036	20020306	00036	NE  	2002	3	6	AUS20020054      	2	20020126	G	7200	12680	ENGINE          			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NR 2	VIBRATES        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 			7039 							(AUS) NR 2 ENGINE VIBRATION EXCESSIVE.						2	L	7	2 	4F	4	F	RT	A20WE   	E30NE				 
2002030600045	20020306	00045	NM  	2002	3	6	AUS20020059      	1	20020119	G	2434	9110813	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					DC ALTERNATOR	LACK OF LUBE    	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			340  							(AUS) ALTERNATOR BEARING SEIZED. SUSPECT CAUSED BY LACK OF LUBRICATION.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002030400133	20020304	00133	EU  	2002	3	4	AUS20020060      	1	20020125	G	6320	350A32106321	GASKET          	            	            	AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  	 		            		MAIN ROTOR GEARB	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN ROTOR TRANSMISSION EPICYCLIC RING GEAR GASKET FAULTY. GASKET WAS EXTRUDING FROM BETWEEN THE UPPER AND LOWER C	ASES AND BREAKING INTO PIECES AND CAUSING AN OIL LEAK WHICH WAS PROGRESSIVELY WORSENING. ON DISASSEMBLY THE MATING CASE 	FLANGES SHOWEDSIGNS OF FRETTING.				1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2002030400134	20020304	00134	CE  	2002	3	4	AUS20020061      	1	20020121	G	3233	99101363	ACTUATOR        	            	            	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	LANDING GEAR ACT	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR RETRACTION RAM INTERNAL FAULT CAUSING RAM TO BE UNLOCKED. RH MLG COLLAPSED ON LANDING.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002030600047	20020306	00047	CE  	2002	3	6	AUS20020062      	1	20020109	G	5511	123262224	SPAR            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER MAIN SPAR CRACKED. CRACKS WENT THROUGH SPAR, SPLICE AND CHANNEL. CRACKS RADIATED FROM THE TO	P AND BOTTOM OF THE CENTRAL LIGHTENING HOLE.  REAR ATTACHMENT FITTING ALSO CRACKED AT THE TAILPLANE TO FUSELAGE ATTACHME	NT POINT.				1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002030600069	20020306	00069	NM  	2002	3	6	AUS20020064      	1	20020129	G	2781	189929	SENSOR          			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					SLATS	FAULTY          	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 2 LEADING EDGE FLAP EXTEND SENSOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030400135	20020304	00135	NM  	2002	3	4	AUS20020065      	1	20020117	G	5270	A42006992302	SOLENOID        	            	            	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		DOOR WARNING SYS	FAULTY          	W			    	K	 	 	 	NONE                    				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 	 									(AUS) RH OVERWING EXIT FLIGHT LOCK RELAY AND SOLENOID FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030600071	20020306	00071	NM  	2002	3	6	AUS20020066      	1	20020128	G	4920	737M49503011	APU             			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					APU BAY	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) APU LEAKING FUEL FROM DRAIN MAST.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030600075	20020306	00075	SW  	2002	3	6	AUS20020070      	1	20020124	G	3243	76C76612501	ROD END         		76C76612501 	SWRNGN	SA227 	SA227*      	       	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	MASTER CYLINDER	SHEARED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 			14749		RH0112					(AUS) PILOTS LT BRAKE MASTER CYLINDER ROD END SHEARED.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
2002030600076	20020306	00076	CE  	2002	3	6	AUS20020071      	1	20020131	G	5711		SPAR CAP        			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7560 							(AUS) WING SPAR CAP CONTAINED EXFOLIATION CORROSION.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2002030400136	20020304	00136		2002	3	4	AUS20020075      	4	20020115	G	2564	733M2537011	LIFE RAFT       	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		LIFERAFT	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				11208487					(AUS) LIFERAFT FAULTY. LH BOTTLE PRESSURE READING ZERO.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030700002	20020307	00002	CE  	2002	3	7	AUS20020076      	1	20020116	G	2842		SENSOR          			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	IO360A1G6   	41514	EA  					FUEL QUANTITY	STUCK           	W				O				OTHER                   				E	R	N	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FALSE WARNING             	CL	CLIMB          	1			AU	S 										(AUS) RT FUEL SENSOR JAMMED IN HALF FULL POSITION.  ERRONEOUS FUEL INDICATIONS ALLOWED RT FUEL TANK TO BE LOW ON FUEL RE	SULTING IN RT ENGINE POWER LOSS.					1	L	7	2 	3O	3	O	 	A29CE   	1E10				 
2002030400137	20020304	00137	NM  	2002	3	4	AUS20020079      	1	20020204	G	2150	65771	COOLING FAN     	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		CABIN COOLING SY	FAILED          	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 	 				10430					(AUS) NORMAL EXHAUST FAN FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030700006	20020307	00006	NE  	2002	3	7	AUS20020081      	2	20020125	G	8500	R183092	ENGINE          			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	LEFT	MAKING METAL    	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		DE	DESCENT        	1			AU	S 			974  							(AUS) LT ENGINE OIL FILTER CONTAMINATED WITH METAL.						2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2002030700007	20020307	00007	GL  	2002	3	7	AUS20020083      	3	20020201	G	6111	BU9606	BLADE           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2932 							(AUS) LT PROPELLER NR 2 BLADE CRACKED. CRACK LENGTH APPROXIMATELY 40MM (1.57IN) RUNNING CHORDWISE ACROSS THE BLADE FROM 	THE TRAILING EDGE. CRACK IS LOCATED APPROXIMATELY 150MM (5.9IN) FROM THE BLADE TIP.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2002030400138	20020304	00138	CE  	2002	3	4	AUS20020084      	1	20020125	G	2460	S123230	CIRCUIT BREAKER 	            	            	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	DC POWER DISTRIB	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			AU	S 	 									(AUS) CIRCUIT BREAKER FAILED.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002030700008	20020307	00008	CE  	2002	3	7	AUS20020085      	1	20020204	G	5751	512400021	BALANCE WEIGHT  			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH AILERON INTERNAL BALANCE WEIGHT LOOSE. INVESTIGATION FOUND THE MIDDLE SECTION OF THE BALANCE WEIGHT WAS BROKEN 	OFF.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002030400139	20020304	00139	SO  	2002	3	4	AUS20020086      	2	20020130	G	7414	36066AA	GEAR            	BENDIX      	105005147   	EAGLE 	XTS   	EAGLEXTS150 	05607BZ	GL  	CONT  	O240  	IO240A      	 	SO  	MCAULY	1A135	1A135BRM    	GL  	MAGNETO/DISTRIBU	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		498  		LHE3194060RH					(AUS) LH AND RH MAGNETO GEARS WORN.						1	H	7	1 	3I	3	O	NC	A00005LA	E7SO	5	N	P842	 
2002030700009	20020307	00009	GL  	2002	3	7	AUS20020087      	3	20020121	G	6111	90A8	BLADE           			CESSNA	182   	182B        	2072706	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	PROPELLER	MISREPAIRED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INSPECTION OF PROPELLER WHEN RECEIVED FOR REPAIR FOUND THAT THE BLADE THREADS HAD BEEN TRUNCATED TO COMPLY WITH AD	/PMC/24/3 BUT HAD NOT BEEN SHOT PEENED. THE RETENTION NUTS DID NOT HAVE THE O-RING GROOVE WIDENED AS LISTED IN SL 1990-2	. AD/PMC/41HAD NOT BEEN INCORPORATED AT THE LAST OVERHAUL. THE SERIAL NUMBER OF ONEBLADE WAS INCORRECT IN THE LOGBOOK. P	ERSONNEL/MAINTENANCE ERROR.			1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002030700010	20020307	00010	EA  	2002	3	7	AUS20020088      	2	20020125	G	7414	AO9815	SCREW           			GIPPLD	GA200 	GA200       	       	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	MAGNETO	LOOSE           	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 										(AUS) LT MAGNETO SEPARATED FROM ENGINE. INVESTIGATION FOUND THAT THE MAGNETO BASE FLANGE RETAINING SCREWS (3OFF) FELL OU	T AND WERE FOUND INSIDE THE ENGINE. SUSPECT CAUSED BY LACK OF TORQUE ON THESCREWS. PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	NC	A00001LA	1E4	5	C	P920	 
2002030400140	20020304	00140	CE  	2002	3	4	AUS20020090      	1	20020206	G	2820	0800400261	PIPE            	            	            	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH INBOARD FUEL TRANSFER PIPE CORRODED AND LEAKING.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002030700059	20020307	00059	CE  	2002	3	7	AUS20020091      	1	20020203	G	5313		STRINGER        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRINGER NR 9 LT LOCATED BEHIND FRONT PRESSURE BULKHEAD CRACKED AT THE END OF THE ATTACHMENT GUSSETT.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002030700064	20020307	00064	CE  	2002	3	7	AUS20020095      	1	20020208	G	6120		CABLE           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	PROP CONTROL	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT PROPELLER CONTROL CABLE DIAMETER WAS FOUND TO BE LESS THAN THE DIAMETER OF THE RH SIDE CABLE. LT CABLE WAS4.762	MM (0.1875IN) INDIAMETER AND THE RT CABLE WAS 6.350MM (0.25IN). UNAPPROVED PART.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002030400141	20020304	00141	EU  	2002	3	4	AUS20020096      	1	20020209	G	3230	HP848430621	VALVE           	            	            	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 		18217							(AUS) LANDING GEAR CONTROL VALVE FAULTY. INVESTIGATION FOUND THAT THE DOWN SOLENOID HAD A RESISTANCE PROBLEM.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL	 
2002030700068	20020307	00068	NE  	2002	3	7	AUS20020098      	2	20020122	G	7420	311983301	IGNITION LEAD   			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					IGNITION SYSTEM	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE IGNITER LEADS CAUSING IGNITER PIN EROSION.  LEADS ARE A NEW ITEM WITH SHORTER INSULATORS.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002030400142	20020304	00142	EU  	2002	3	4	AUS20020100      	2	20020131	G	7321	8063215	MEC             	GE          	CFM563C1    	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 				857543					(AUS) NO2 ENGINE MAIN ENGINE CONTROL (MEC) FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030400143	20020304	00143	NM  	2002	3	4	AUS20020104      	1	20020212	G	3230	A42000028305	SOLENOID        	            	            	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) LANDING GEAR LOCK SOLENOID FAULTY. AIR/GROUND SWITCH S106 OUT OFADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030700092	20020307	00092	EU  	2002	3	7	AUS20020106      	1	20020214	G	2520	MS220441P00501	HOOK            			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					CABIN	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SAFETY HARNESS USED BY CAMERAMAN FAULTY.  SNAP HOOK ON HARNESS MAY UNDER SOME CIRCUMSTANCES HAVE THE SPRING LOADED	 SAFETY CATCH FORCED OPEN ALLOWING THE SNAP HOOK TO SEPARATE FROM THE AIRCRAFT ATTACHMENT POINT.					1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2002030400144	20020304	00144	NM  	2002	3	4	AUS20020110      	1	20020105	G	5101		STRUCTURE       	            	            	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		AIRCRAFT STRUCTU	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) EXFOLIATION CORROSION FOUND AT NO3 CARGO DOOR UPPER FORWARD SIDEAT STN 1090, STRINGER 20R. FOUND DURING CPCP INSPE	CTION.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002030700096	20020307	00096	CE  	2002	3	7	AUS20020111      	1	20020207	G	7160	12507043	FILTER          			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	AIR INTAKE	BURNED          	W				O				OTHER                   				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE AIR FILTER BURNT.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002030400145	20020304	00145	NM  	2002	3	4	AUS20020117      	1	20020218	G	7921	28E997	OIL COOLER      	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE OIL COOLE	LEAKING         	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 		428  		REF75980					(AUS) NO2 ENGINE OIL COOLER LEAKING. LOSS OF ENGINE OIL.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002030700102	20020307	00102	CE  	2002	3	7	AUS20020120      	1	20020211	G	2823	HE7805	SELECTOR SWITCH 			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	AMTR	C8289	C8289       	GL  	FUEL SYSTEM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			197  							(AUS) LT FUEL SELECTOR VALVE EXCESSIVELY CORRODED DUE TO CONTAMINATION.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	N	EXPP5N	 
2002030700103	20020307	00103	CE  	2002	3	7	AUS20020121      	1	20020211	G	2823	HE7803	SELECTOR SWITCH 			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	AMTR	C8289	C8289       	GL  	FUEL SYSTEM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			197  							(AUS) RT FUEL SELECTOR VALVE EXCESSIVELY CORRODED DUE TO CONTAMINATION.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	N	EXPP5N	 
2002030400146	20020304	00146	NM  	2002	3	4	AUS20020122      	1	20020218	G	7712	311694201	SENSOR          	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE BMEP/TORQ	FAULTY          	W			    	K	E	 	 	NONE                    	ENGINE SHUTDOWN         			E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 	 		6362 		120683					(AUS) ENGINE TORQUE SENSOR FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002030700104	20020307	00104	EU  	2002	3	7	AUS20020123      	1	20020211	G	2434	ALV2045BS	BRUSH BLOCK     			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	DC ALTERNATOR	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR BRUSHES SHORTING BETWEEN THE SLIP RINGS AND ALTERNATOR SLIP RING END BEARING.						1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920	 
2002030700105	20020307	00105	SO  	2002	3	7	AUS20020124      	1	20020220	G	2140	461731	REGULATOR VALVE 			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	FAULTY          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT HEATER FUEL PRESSURE REGULATOR FAULTY. REGULATOR LEAKING FUELFROM DRAIN.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002030400147	20020304	00147	CE  	2002	3	4	AUS20020125      	1	20020126	G	7810		EXHAUST PIPE    	CONT        	GTSIO520H   	CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	ENGINE COLLECTOR	LEAKING         	W			    	K	 	 	 	NONE                    				E	B	 	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			AU	S 	 									(AUS) RH ENGINE FIRE. ENGINE COMPARTMENT DAMAGED. FIRE WAS EXTINGUISHED USING CABIN FIRE EXTINGUISHER. INVESTIGATION FOU	ND THE FIRE WAS CAUSED BY MISALIGNMENT OF THE EXHAUST SWIVEL JOINT WHICH ALLOWEDEXHAUST GAS TO LEAK INTO THE ENGINE BAY.	 A LIST OF DAMAGE IS AS FOLLOWS:- 1.OUTBOARD ENGINE MOUNT BEAM HEAT DAMAGED 2.STARTER HEAT DAMAGED3.OUTBOARD REAR ENGINE	 MOUNT HEAT AFFECTED4.INTERCOOLER INDUCTION TUBE HEAT DAMAGED 5.VARIOUS FUEL, OIL AND DRAIN HOSES HEAT DAMAGED6.TURBOCHA	RGER SEIZED 7.TACHO GENERATOR HEAT AFFECTED 8.INTERCOOLER HEAT AFFECTED 9.VACUUM PUMP HEAT AFFECTED 10. OIL PUMP HEAT AF	FECTED	1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2002030400148	20020304	00148	SO  	2002	3	4	AUS20020127      	1	20020215	G	3232	455946	ACTUATOR        	            	            	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR DOO	FAULTY          	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		CL	CLIMB          	1			AU	S 	 				3552					(AUS) RH MAIN LANDING GEAR INBOARD DOOR ACTUATOR FAULTY. SUSPECTINTERNAL LOCK FAILURE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002030400149	20020304	00149	SO  	2002	3	4	AUS20020128      	1	20020215	G	3710	215CC	PUMP            	AIRBORNE    	215CC       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	VACUUM DISTRIBUT	INOPERATIVE     	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		CR	CRUISE         	1			AU	S 	 				3AU1603					(AUS) LH VACUUM PUMP DRIVE SHEARED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002030400150	20020304	00150	NM  	2002	3	4	AUS20020130      	1	20020206	G	2913	66087	PUMP            	            	            	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		HYDRAULIC PUMP,	SEIZED          	W			    	K	 	 	 	NONE                    				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 	 				K0169					(AUS) NO1 ENGINE DRIVEN HYDRAULIC PUMP SEIZED AND LEAKING. RH MAINLANDING GEAR RETRACTION ACTUATOR HOSES ALSO LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002030700110	20020307	00110	CE  	2002	3	7	AUS20020132      	1	20020122	G	3230	504501025	TORQUE TUBE     			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR TORQUE TUBE DAMAGED. SUSPECT DAMAGE ORIGINATED FROM CRACKING AROUND THE FORK BOLT AREA.						1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2002030400151	20020304	00151	NE  	2002	3	4	AUS20020133      	3	20020219	G	6114	54547AB	SPIDER          	HAMSTD      	22D40505    	AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	22D	22D40       	NE  	PROPELLER HUB SE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		570  		82087					(AUS) PROPELLER SPIDER CRACKED. CRACK LENGTH 50.8MM (2IN).						1	L	7	1 	3R	3	R	 	A9SW    	5E2	5	C	P736	 
2002030400152	20020304	00152	CE  	2002	3	4	AUS20020136      	1	20020221	G	3710	215CC	PUMP            	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	VACUUM DISTRIBUT	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) VACUUM PUMP FAILED.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002030400153	20020304	00153	CE  	2002	3	4	AUS20020137      	1	20020221	G	3710	215CC	PUMP            	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	VACUUM DISTRIBUT	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) VACUUM PUMP FAILED.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002030700113	20020307	00113	CE  	2002	3	7	AUS20020138      	1	20020212	G	3230	574122214	HOOK            			CESSNA	441   	441         	2076020	CE  										MLG UPLOCK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR UPLOCK HOOK CRACKED.						1	L	7	2 	3T			RT	A28CE   					 
2002030700115	20020307	00115	CE  	2002	3	7	AUS20020139      	1	20020225	G	3230	MS935302	CLAMP           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	MLG BLOWDOWN	UNAPPROVED PART 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR EMERGENCY BLOWDOWN SYSTEM CONTROL CABLE CLAMP INCORRECT ITEM.  THE INCORRECT ITEM WAS A RUBBER CUSHIO	NED CLAMP WHICH ALLOWED THE CONTROL CABLE TO SLIP AND JAM THE FIRINGSYSTEM. WHEN THE CORRECT CLAMP WAS FITTED THE SYSTEM	 OPERATED NORMALLY. UNAPPROVED PART.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002030400154	20020304	00154	SO  	2002	3	4	AUS20020141      	1	20020225	G	5411	8617903	WEB             	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	NACELLE/PYLON, F	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ENGINE NACELLE TOP OUTBOARD WEB CRACKED IN AREA OF TOP REARENGINE MOUNT ATTACHMENT POINT.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002030700124	20020307	00124	EA  	2002	3	7	AUS20020142      	2	20020223	G	8530	SL19034	EXHAUST VALVE   			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	BURNED          	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 										(AUS) EXHAUST VALVE BURNED. VALVE NOT SEATING CORRECTLY.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002030400155	20020304	00155	CE  	2002	3	4	AUS20020144      	1	20020212	G	5610	10138402515	WINDSHIELD      	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLIGHT COMPARTME	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 				94055H2855					(AUS) WINDSHIELD CRACKED WHEN HEAT TURNED ON.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2002030400156	20020304	00156	EA  	2002	3	4	AUS20020145      	2	20020225	G	8520	LW18840	CAMSHAFT        	LYC         	O360A4M     	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	AMTR	C8289	C8289       	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 									(AUS) CAMSHAFT LOBE FAILED. METAL CONTAMINATION OF OIL SYSTEM. OILPRESSURE RELIEF VALVE OFF SEAT. LOW OIL PRESSURE LED T	O BEARING FAILURE AND SUBSEQUENT ENGINE SEIZURE.					1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	EXPP5N	 
2002030400157	20020304	00157	NM  	2002	3	4	AUS20020146      	1	20020223	G	2913	165W01020	PUMP            	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		HYDRAULIC PUMP,	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) STANDBY HYDRAULIC PUMP FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002040800046	20020408	00046	NE  	2002	4	8	AUS20020147      	2	20020220	G	7420	5336761	CABLE           	PWA         	HEIU        	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	IGNITION HARNESS	SPLIT           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		24034		97180405					(AUS) LH ENGINE IGNITION CABLE FROM HIGH ENERGY IGNITION UNIT (HEIU) TO IGNITER PLUG CHAFED THROUGH REINFORCED OUTER LAY	ER THROUGH TO THE INNER LAYER DUE TO RUBBING AGAINST THE FIREWALL AND OTHER ENGINEMOUNTED COMPONENTS.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2002040800047	20020408	00047	SO  	2002	4	8	AUS20020148      	1	20020221	G	5521	4007514	SPAR            	PIPER       	SPAR        	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	ELEVATOR, SPAR/R	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH ELEVATOR SPARS CRACKED AT OUTBOARD ENDS. LH ELEVATORSPAR PNO 40075-14. RH ELEVATOR SPAR PNO 40075-16.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002040800122	20020408	00122	EU  	2002	4	8	AUS20020149      	1	20020228	G	2910	SA7670006127	HOSE            			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NLG	BURST           	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR RETRACTION HOSE BURST. LOSS OF GREEN HYDRAULIC SYSTEM FLUID.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2002040800048	20020408	00048	NM  	2002	4	8	AUS20020150      	1	20020228	G	2823		SHUTOFF VALVE   	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUEL SELECTOR/SH	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CENTRE TANK FUELLING SHUTOFF VALVE FAILED IN THE OPEN POSITION. VALVE COULD BE OPERATED MANUALLY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002040800123	20020408	00123	EA  	2002	4	8	AUS20020151      	2	20020226	G	7322	DC0156	PIN             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL CONTROL	MISSING         	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			AU	S 										(AUS) CARBURETOR THROTTLE LEVER LOCKNUT SPLIT PIN MISSING AND LOCKNUT LOOSE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002040800124	20020408	00124	CE  	2002	4	8	AUS20020152      	1	20020226	G	3244		TIRE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	NLG	DEFLATED        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE WHEEL TIRE DEFLATED. FENDER DAMAGED BY TIRE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002040800126	20020408	00126	NM  	2002	4	8	AUS20020153      	1	20020301	G	3040		CONNECTOR       			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					WINDOW HEAT	LOOSE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) CAPTAINS NR 1  WINDOW HEAT CONNECTION LOCATED IN THE LOWER LT CORNER LOOSE AND ARCING.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2002040800128	20020408	00128	NE  	2002	4	8	AUS20020154      	2	20020301	G	7230		FAN BLADE       			BOEING	747   	747400      	       	NM  	PWA   	4056  	PW4056      	 	NE  					TURBINE ENGINE	SEPARATED       	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 3 ENGINE FAN BLADE SEPARATED. ASSOCIATED DAMAGE TO ENGINE. AIRCRAFT IS BRITISH REGISTERED.						2	L	7	4 	4F	4	F	RT	A20WE   	E24NE				 
2002040800049	20020408	00049	SO  	2002	4	8	AUS20020155      	2	20020301	G	7414	10357281	CAPACITOR       	BENDIX      	S6LN25      	PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	MAGNETO/DISTRIBU	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				A175117					(AUS) LH MAGNETO CAPACITOR WIRE INTERMITTENT CONTACT.						1	L	7	1 	3O	3	O	 	2A13    	E9CE	5	C	P920	 
2002040800050	20020408	00050	SO  	2002	4	8	AUS20020156      	2	20020205	G	7414	10357281	CAPACITOR       	BENDIX      	S6LN25      	PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	MAGNETO/DISTRIBU	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				A223385					(AUS) RH MAGNETO CAPACITOR WIRE INTERMITTENT CONTACT.						1	L	7	1 	3O	3	O	 	2A13    	E9CE	5	C	P920	 
2002040800051	20020408	00051	SW  	2002	4	8	AUS20020157      	1	20020223	G	2844	7G1075	PRESSURE SWITCH 	            	            	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  	 		            		FUEL PRESSURE IN	FAILED          	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 				1097					(AUS) FUEL PRESSURE SWITCH INTERNAL FAILURE. FUEL LEAKING FROM BODY.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002040800129	20020408	00129	SW  	2002	4	8	AUS20020158      	1	20020307	G	5711		SPAR            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR SPAR WEB CRACKED ON RT SIDE AT WS 27.063. FOUND DURING INSPECTION IAW AD/SWSA226/86.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2002040800131	20020408	00131	NM  	2002	4	8	AUS20020159      	1	20020305	G	2722	654486112	ACTUATOR        			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					YAW DAMPER	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			4210 							(AUS) RUDDER YAW DAMPER ACTUATOR SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002040800052	20020408	00052	NM  	2002	4	8	AUS20020160      	1	20020301	G	2912	AN81510D	FITTING         	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC FILTER	FAILED          	W			    	K	 	 	 	NONE                    				K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 	 									(AUS) NO2 HYDRAULIC SYSTEM MAIN FILTER PRESSURE MANIFOLD BULKHEAD FITTING FRACTURED. LOSS OF HYDRAULIC FLUID. INVESTIGAT	ION FOUND THE FRACTURE SURFACE WAS COARSE TEXTURED WITH CHEVRON MARKINGSINDICATING OVERLOAD FRACTURE DUE TO ROTATION IN 	A CLOCKWISE MANNER. THE FITTING FAILED BY OVERLOAD FRACTURE CONSISTENT WITH OVERTIGHTENING.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002040800053	20020408	00053	NE  	2002	4	8	AUS20020161      	2	20020304	G	7321		BEARING         	PWA         	PW123D      	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) NO1 ENGINE POWER LEVER JAMMED. INVESTIGATION FOUND THEHYDROMECHANICAL UNIT (HMU) POWER LEVER INPUT BEARING FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002040800054	20020408	00054	EU  	2002	4	8	AUS20020162      	2	20020305	G	7260		BEARING         	GE          	CFM563C     	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TURBINE ENGINE A	GALLED          	W			    	K	 	 	 	NONE                    				E	F	 	VIBRATION/BUFFET          	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			AU	S 	 									(AUS) NO2 ENGINE TRANSFER GEARBOX INPUT ROLLER BEARING GALLED. METALCONTAMINATION OF OIL SYSTEM.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002040800134	20020408	00134	NE  	2002	4	8	AUS20020163      	2	20020307	G	7320		LINE            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					P3 AIR	BLOCKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 			372  							(AUS) NR 2 ENGINE RPM REDUCED TO IDLE DURING FLIGHT. EXTENSIVE INVESTIGATION COULD FIND NO FAULT AND THE AIRCRAFT WAS RE	TURNED TO SERVICE. SUSPECT PROBLEM CAUSED BY TEMPORARY BLOCKAGE OF P3 AIR SUPPLY LINE.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002040800055	20020408	00055	CE  	2002	4	8	AUS20020164      	1	20020131	G	3260	951F04	LIGHT           	            	            	BEECH 	1900  	1900        	1154160	CE  	      		            			 		            		LANDING GEAR POS	FAILED          	W			    	K	 	 	 	NONE                    				O	P	 	OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR POSITION LIGHT FAILED.						2	L	7	2 	4T			RT	A24CE   					 
2002040800056	20020408	00056	GL  	2002	4	8	AUS20020165      	2	20020121	G	7321	23070613	FCU             	ALLSN       	250C30P     	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  	 		            		FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				E	M	 	VIBRATION/BUFFET          	OVER TEMP                 		NR	NOT REPORTED   	1			AU	S 	 		10   		72412					(AUS) FUEL CONTROL UNIT FAULTY. FCU HAD JUST BEEN FITTED BUT GAVE CONTINUAL HOT STARTS.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002040800151	20020408	00151	EA  	2002	4	8	AUS20020166      	1	20020221	G	3250	711709	LEVER           			DHAV  	DHC6  	DHC6300     	2802606	EA  										NLG STEERING SYS	BROKEN          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NOSE WHEEL STEERING LEVER ASSEMBLY LOCATED BETWEEN THE NOSE STEERING ACTUATOR AND THE NOSE STEERING COLLAR BROKEN 	IN TWO.					1	H	7	2 	3T			RT	A9EA    					 
2002040800152	20020408	00152	CE  	2002	4	8	AUS20020167      	1	20020301	G	5711		SPAR            			CESSNA	441   	441         	2076020	CE  										WING	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT AFT SPAR WEBS DELAMINATED.						1	L	7	2 	3T			RT	A28CE   					 
2002040800153	20020408	00153	CE  	2002	4	8	AUS20020168      	1	20020302	G	5711		SPAR            			CESSNA	441   	441         	2076020	CE  										WING	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT AFT SPAR WEBS DELAMINATED.						1	L	7	2 	3T			RT	A28CE   					 
2002040800057	20020408	00057	SO  	2002	4	8	AUS20020169      	2	20020222	G	8540	653882	SHAFT           			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	BROKEN          	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		DE	DESCENT        	1			AU	S 										(AUS) STARTER SHAFT AND CRANKSHAFT GEAR HAD SEVERAL MISSING TEETH.						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
2002040800058	20020408	00058	SO  	2002	4	8	AUS20020170      	2	20020218	G	8540	537721	BEARING         	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) STARTER SHAFT BEARING BROKEN UP. BEARING DEBRIS LOCATED IN SUMP.CRANKCASE DAMAGED IN AREA OF BEARING SUPPORT. STAR	TER SHAFT AND CRANK GEARS EXHIBITED DEFORMATION OF PROFILE. THE ENGINE WASFITTED WITH PNO EQ6642 ADAPTER KIT AS PER AD/C	ON/71.				1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002040800059	20020408	00059	EA  	2002	4	8	AUS20020171      	2	20020106	G	7313		INJECTOR        	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL INJECTOR NO	BLOCKED         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 									(AUS) RH ENGINE NO1 CYLINDER FUEL INJECTOR NOZZLE CLOGGED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002040800060	20020408	00060	CE  	2002	4	8	AUS20020172      	1	20020206	G	3222	MS28775329	SEAL            	            	            	CESSNA	206   	TU206F      	2073353	CE  	      		            			 		            		NOSE/TAIL LANDIN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) NOSE LANDING GEAR OLEO LEG MAIN SEAL PNO MS28775-329 ROLLED AND SPLIT IN THREE PLACES.						1	H	7	1 	3O			 	A4CE    					 
2002040800155	20020408	00155	EU  	2002	4	8	AUS20020173      	1	20020218	G	7603		THROTTLE        			BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					LT ENGINE	BROKEN          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LT ENGINE THROTTLE SLIDING END ASSEMBLY BROKEN.						1	H	7	2 	3O	3	O	 	A17EU   	1E4				 
2002040800061	20020408	00061	EU  	2002	4	8	AUS20020175      	1	20020127	G	3230	A78730421	UPLOCK          	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 		21782		BE3585					(AUS) RH MAIN LANDING GEAR UPLOCK LATCH FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002040800157	20020408	00157		2002	4	8	AUS20020176      	4	20020126	G	2350	X00011413	ACCESSORY UNIT  			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					AUDIO SYSTEM	FAULTY          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 			370  		67059					(AUS) AUDIO ACCESSORY UNIT FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002040800062	20020408	00062	EU  	2002	4	8	AUS20020177      	1	20020122	G	2432	23531	BATTERY         	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		BATTERY/CHARGER	OVERHEATED      	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 	 		45   		F1537					(AUS) AFT BATTERY OVERHEATED. AFT BATTERY OVERHEAT MILLIAMPMETER NOTOPERATING DUE TO A PART OF THE BROKEN PERSPEX COVER 	WEDGED INSIDE THE INDICATOR.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002040800160	20020408	00160	EU  	2002	4	8	AUS20020179      	1	20020107	G	3260		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					MLG	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOOR FORWARD UPLOCK SWITCH OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002040800063	20020408	00063	EU  	2002	4	8	AUS20020180      	1	20020116	G	2432	23531	BATTERY         	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		BATTERY/CHARGER	OVERHEATED      	W			    	K	 	 	 	NONE                    				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 	 		73   		C02676C02677					(AUS) AFT BATTERY OVERTEMPERATURE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002040800064	20020408	00064	NM  	2002	4	8	AUS20020182      	1	20020308	G	3240	82970009151	HOSE            	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR BRA	LOOSE           	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH BRAKE PRESSURE INPUT LINE TO THE TOP OF THE SWIVEL PNO AE82556E LOOSE. LOSS OF HYDRAULIC FLUID. PERSONNEL/MAINT	ENANCEERROR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002040800065	20020408	00065	EU  	2002	4	8	AUS20020184      	1	20020115	G	2410		SENSOR          	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		ALTERNATOR-GENER	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 									(AUS) NO2 CONSTANT SPEED DRIVE TEMPERATURE SENSOR FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002040800066	20020408	00066	EU  	2002	4	8	AUS20020185      	1	20020115	G	3610		TUBE            	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		PNEUMATIC DISTRI	LEAKING         	W			    	K	 	 	 	NONE                    				M	J	 	OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			AU	S 	 									(AUS) PNEUMATIC TUBE LEAKING FROM DOWNSTREAM PRESSURE TAPPING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002040800187	20020408	00187	EU  	2002	4	8	AUS20020186      	1	20020101	G	2432	23521	BATTERY         			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					BATTERY BAY	OVERHEATED      	W				O				OTHER                   				H	M		ELECT. POWER LOSS-50 PC   	OVER TEMP                 		LD	LANDING        	1			AU	S 			10   							(AUS) FORWARD BATTERY OVERHEATED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002040800188	20020408	00188	NM  	2002	4	8	AUS20020187      	1	20020309	G	7830	S315A1026	SEGMENT         			BOEING	737   	73733A      	1384673	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					THRUST REVERSER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THRUST REVERSER NR 12 CASCADE SEGMENT MISSING. FORWARD ANDAFT FLANGES CRACKED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002040800067	20020408	00067	NM  	2002	4	8	AUS20020188      	1	20020307	G	2620	32422D121212G	FITTING         	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		EXTINGUISHING SY	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO1 ENGINE FIRE EXTINGUISHING SYSTEM T' FITTING CRACKED BIN TWO  PLACES ON THE SEALING SURFACES AND THREADS OF THE	 FITTING.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002040800189	20020408	00189	NE  	2002	4	8	AUS20020189      	2	20020312	G	7250	30723112	TURBINE BLADES  								GARRTT	TFE731	TFE73131G   	29003	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			522  							(AUS) TWO FIRST STAGE LOW PRESSURE TURBINE BLADES FRACTURED CAUSING DAMAGE TO TURBINE BLADES AND NOZZLE ASSEMBLIES. ONE 	RIVET HAD BROKEN OFF THE LP TURBINE NOZZLE SEAL ASSEMBLY AND IMPINGED ONTHE FORWARD FACE OF THE TURBINE DISC BEFORE FINA	LLY WEDGING ONTHE SHAFT SEAL BOLT.									4	F			E6WE				 
2002040800190	20020408	00190	CE  	2002	4	8	AUS20020190      	1	20020311	G	2810	60170010604	FUEL TANK       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	AMTR	C8289	C8289       	GL  	RT WING	CONTAMINATED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING TIP TANK CONTAMINATED. SUSPECT NON-APPROVED SEALANT USED. POSSIBLE FILTER BLOCKAGE.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	N	EXPP5N	 
2002040800068	20020408	00068	EA  	2002	4	8	AUS20020191      	2	20020311	G	8520	72877	TAPPET          	LYC         	IO540K1B5   	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1390 							(AUS) RH ENGINE NO6 CYLINDER INLET TAPPET AND NO4 CYLINDER EXHAUSTTAPPET BODIES CRACKED.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002040800191	20020408	00191	CE  	2002	4	8	AUS20020192      	1	20020313	G	7810	99102962	SLIP JOINT      			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE COLLECTOR	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			189  							(AUS) LT ENGINE EXHAUST SYSTEM SLIP JOINT HARDWARE UNAPPROVED PARTS AND NOT INSTALLED IAW RELEVANT DATA.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002040800192	20020408	00192	CE  	2002	4	8	AUS20020193      	1	20020313	G	7810	99102962	SLIP JOINT      			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE COLLECTOR	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE EXHAUST SYSTEM SLIP JOINT HARDWARE UNAPPROVED PARTS AND NOT INSTALLED IAW RELEVANT DATA. PERSONNEL/MAINT	ENANCE ERROR. UNAPPROVED PART.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002040800069	20020408	00069	SO  	2002	4	8	AUS20020194      	1	20020213	G	2721	6666100	ARM             	            	            	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	RUDDER TAB CONTR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RUDDER TRIM ARM ASSEMBLY CRACKED AROUND WELD.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002040800193	20020408	00193	CE  	2002	4	8	AUS20020195      	1	20020301	G	5711		SPAR            			CESSNA	441   	441         	2076020	CE  										LT WING	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING REAR SPAR WEB DELAMINATED IN THREE AREAS.						1	L	7	2 	3T			RT	A28CE   					 
2002040800194	20020408	00194	CE  	2002	4	8	AUS20020196      	1	20020223	G	2751		SWITCH          			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	TE FLAPS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS)  SWITCH ON FLAP PRESELECT ARM MISSING. ALL ATTACHING HARDWARE ALSO MISSING AND CONNECTING WIRES STOWED.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800070	20020408	00070		2002	4	8	AUS20020197      	4	20020223	G	3432		CONNECTOR       	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	GLIDE SLOPE SYST	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) GLIDESLOPE RECEIVER CONNECTOR INPUT VOLTAGE PIN BENT.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800071	20020408	00071		2002	4	8	AUS20020198      	4	20020223	G	3454		CONVERTER       	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	VOR SYSTEM	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) VOR CONVERTER FAULTY.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800195	20020408	00195		2002	4	8	AUS20020199      	4	20020223	G	2310		TRANSCEIVER     			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	HF COMMUNICATION	UNSECURE        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) HF TRANSCEIVER NOT SECURED IN RACK. FURTHER INVESTIGATION FOUND THE TRANSCEIVER UNSERVICEABLE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800197	20020408	00197		2002	4	8	AUS20020200      	4	20020223	G	2310		RADIO           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	COMMUNICATIONS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LIMITED RECEIVE RANGE ON BOTH COM1 AND COM2.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800198	20020408	00198		2002	4	8	AUS20020201      	4	20020223	G	2310		RADIO           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	HF COMMUNICATION	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HF SYSTEM FAULTY.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800199	20020408	00199	CE  	2002	4	8	AUS20020202      	1	20020223	G	3411		VENT            			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	PITOT/STATIC SYS	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) STATIC VENT INCORRECTLY MARKED.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800072	20020408	00072		2002	4	8	AUS20020203      	4	20020223	G	3451		ANTENNA         	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	DME/TACAN SYSTEM	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) DME ANTENNA PAINTED OVER. SIGNS OF CORROSION AROUND EDGES OFANTENNA.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800073	20020408	00073		2002	4	8	AUS20020204      	4	20020223	G	3434		MOUNT           	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	MARKER BEACON SY	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MARKER BEACON ANTENNA MOUNT CONTAINED SURFACE CORROSION.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800074	20020408	00074	CE  	2002	4	8	AUS20020205      	1	20020223	G	1400		STATIC WICK     	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	MISCELLANEOUS HA	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ALL STATIC WICKS (10OFF) UNSERVICEABLE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800200	20020408	00200	EA  	2002	4	8	AUS20020206      	2	20020223	G	7297		WIRE HARNESS    			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ENGINE BAY	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE BAY WIRING LOOMS WORN THROUGH IN NUMEROUS PLACES.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800201	20020408	00201	CE  	2002	4	8	AUS20020207      	1	20020223	G	2434		FILTER          			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	DC GENERATOR-ALT	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR FILTER TOUCHING AUX' TERMINAL OF ALTERNATOR.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800075	20020408	00075	CE  	2002	4	8	AUS20020208      	1	20020223	G	2497		WIRE            	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ELECTRICAL POWER	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) EXTERNAL POWER SWITCH LEAD WORN THROUGH ON AIRCRAFT RIB.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800076	20020408	00076	CE  	2002	4	8	AUS20020209      	1	20020223	G	3310		LIGHT           	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	FLIGHT COMPARTME	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) OVERHEAD FLOOD LIGHT AND TRIM POST LIGHTS UNSERVICEABLE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800077	20020408	00077	CE  	2002	4	8	AUS20020210      	1	20020223	G	3310		LIGHT           	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	FLIGHT COMPARTME	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH POST LIGHTS AND PEDESTAL POST LIGHTS UNSERVICEABLE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800202	20020408	00202		2002	4	8	AUS20020211      	4	20020223	G	3455		LIGHT           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ADF SYSTEM	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ADF INTERNAL LIGHTS UNSERVICEABLE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800203	20020408	00203	CE  	2002	4	8	AUS20020212      	1	20020223	G	1100		PLACARD         			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	COCKPIT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MULTIPLE LABELS MISSING FROM EQUIPMENT IDENTIFIERS IN COCKPIT.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800078	20020408	00078		2002	4	8	AUS20020213      	4	20020223	G	2210		SWITCH          	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	AUTOPILOT SYSTEM	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AUTO-PILOT CONTROLLER BACK COURSE SWITCH INOPERATIVE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800079	20020408	00079	CE  	2002	4	8	AUS20020214      	1	20020223	G	2437		AMMETER         	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	DC INDICATING SY	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AMMETER FAULTY.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800204	20020408	00204		2002	4	8	AUS20020215      	4	20020223	G	2210		SELECTOR SWITCH 			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	AUTOPILOT SYSTEM	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AUTOPILOT NAV2 EXTERNAL SWITCH SELECTOR HAD NO MARKINGS.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800080	20020408	00080	CE  	2002	4	8	AUS20020216      	1	20020223	G	3310		LIGHT           	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	FLIGHT COMPARTME	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CONTROL COLUMN MAP LIGHT FAULTY. LAMP AND LAMP HOLDER MISSING.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800081	20020408	00081	CE  	2002	4	8	AUS20020217      	1	20020223	G	7931		PIPE            	LYC         	O540J3C5    	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ENGINE OIL PRESS	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PIPE BETWEEN OIL PRESSURE INDICATOR AND HOUR-METER BLOCK CORRODED AND FLARE SPLIT. HOUR-METER BLOCK FIREWALL FITTI	NG LOOSE AND REAR FITTING HAD INCORRECT THREAD TYPE. OIL LEAKING FROM BEHIND DASH.					1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800205	20020408	00205	CE  	2002	4	8	AUS20020218      	1	20020223	G	2437		LIGHT           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	DC INDICATING	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR LOW VOLTAGE WARNING LIGHT SECURED TO RT DASH WITH PVC ELECTRICAL TAPE. UNAPPROVED PART.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800206	20020408	00206	CE  	2002	4	8	AUS20020219      	1	20020223	G	3310		LIGHT           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  		MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT INSTRUMENT PANEL COVER POST LIGHT CONNECTION WIRES FITTED WITH INCORRECT TERMINALS.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800208	20020408	00208		2002	4	8	AUS20020220      	4	20020223	G	3497		WIRE            			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	NAVIGATION	CUT             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRING TO RT SIDE OF ADF RACK CUT THROUGH BY RACK.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800082	20020408	00082		2002	4	8	AUS20020221      	4	20020223	G	3197		LIGHT           	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	INSTRUMENT WIRIN	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ARTIFICIAL HORIZON HAD NO INTERNAL OR EXTERNAL LIGHTING. INTERNAL LIGHTS WIRING CONNECTED TO AN UNKNOWN SOURCE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800209	20020408	00209	CE  	2002	4	8	AUS20020222      	1	20020223	G	3340		LIGHT           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	STROBE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BOTH STROBE LIGHT FLASH TUBES BLACKENED.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800210	20020408	00210	CE  	2002	4	8	AUS20020223      	1	20020223	G	3340		LENS            			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	NAV LIGHT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RT NAVIGATION LIGHT LENS GLUED IN WITH SILASTIC. UNAPPROVED PART.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800083	20020408	00083	CE  	2002	4	8	AUS20020224      	1	20020223	G	3340		LENS            	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	EXTERIOR LIGHTIN	LOOSE           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TAIL LIGHT LENS LOOSE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800084	20020408	00084	CE  	2002	4	8	AUS20020225      	1	20020223	G	3310		LIGHT           	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	FLIGHT COMPARTME	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH CLOCK/MICROPHONE JACK POST LIGHT UNSERVICEABLE. THE CENTRE CONTACTOR ASSEMBLY WAS MISSING FROM THE LIGHT HOLDER	.					1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800085	20020408	00085		2002	4	8	AUS20020228      	4	20020223	G	2210		INDICATOR       	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	AUTOPILOT SYSTEM	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AUTOPILOT TURN AND BANK UNIT FAULTY.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800086	20020408	00086	CE  	2002	4	8	AUS20020229      	1	20020223	G	3340		BALLAST         	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	EXTERIOR LIGHTIN	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TAIL BEACON BALLAST RESISTOR BROKEN IN THREE PLACES.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800212	20020408	00212		2002	4	8	AUS20020230      	4	20020223	G	3425		SCREW           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	HSI	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HSI TOP RT SCREW MISSING.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800087	20020408	00087	CE  	2002	4	8	AUS20020231      	1	20020223	G	7933		INDICATOR       	LYC         	O540J3C5    	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ENGINE OIL TEMPE	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE OIL TEMPERATURE INDICATOR FAULTY.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800088	20020408	00088		2002	4	8	AUS20020232      	4	20020223	G	3452		MOUNT           	            	            	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ATC TRANSPONDER	LOOSE           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TRANSPONDER MOUNT LOOSE. MOUNT MADE OF THIN METAL.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040900004	20020409	00004		2002	4	9	AUS20020233      	4	20020223	G	3452		RESISTOR        			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ATC TRANSPONDER	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TRANSPONDER VOLTAGE DROPPING RESISTOR INCORRECTLY MOUNTED. THE RESISTOR IS MOUNTED ON THE REAR OF THE TRANSPONDER 	MOUNTING RACK. THE INSTALLATION MANUAL STATES THAT IT MUST BE MOUNTED AWAY FROM THE AVIONICS STACK TO AVOID OVERHEATING 	OF THE POWER SUPPLY.				1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002040800089	20020408	00089	SO  	2002	4	8	AUS20020236      	1	20020314	G	7810	3031988	DUCT            	PWA         	PT6A34      	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE COLLECTOR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1172 		PCE57045					(AUS) EXHAUST DUCT CONTAINED HAIRLINE CRACKS.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2002040800090	20020408	00090	NM  	2002	4	8	AUS20020237      	1	20020313	G	3231	XD4N	RELAY           	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR DOO	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR DOOR RELAY SUSPECT FAULTY. INVESTIGATION COULD NOT DUPLICATE FAULT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002040800091	20020408	00091	EA  	2002	4	8	AUS20020238      	2	20020315	G	7314	RJ9080J4A	PUMP            	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE FUEL PUMP	FAILED          	W			    	K	 	 	 	NONE                    				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		LD	LANDING        	1			AU	S 	 		132  		C6223					(AUS) RH ENGINE DRIVEN FUEL PUMP FAILED ON LOW SIDE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002040800092	20020408	00092	NM  	2002	4	8	AUS20020239      	1	20020314	G	2752	65766061	BOLT            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TRAILING EDGE FL	SHEARED         	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 	 									(AUS) NO1 TRAILING EDGE FLAP SCREWJACK TO TRANSMISSION ATTACHMENT BOLTSHEARED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002040800093	20020408	00093	NM  	2002	4	8	AUS20020240      	1	20020215	G	5523		BALANCE WEIGHT  	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		ELEVATOR, TAB ST	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) RH ELEVATOR TAB CENTRE BALANCE WEIGHT SPLIT OPEN DUE TO CORROSION.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800094	20020408	00094	NM  	2002	4	8	AUS20020241      	1	20020214	G	5512		PANEL           	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		HORIZONTAL STABI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) HORIZONTAL STABILISER PANEL LOCATED ABOVE BAY THREE CORRODED IN AREA OF REAR AUXILIARY SPAR LH SIDE.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800095	20020408	00095	NM  	2002	4	8	AUS20020242      	1	20020122	G	5347	BAC1520843	TRACK           	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		SEAT/CARGO ATTAC	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) FORWARD CARGO TIEDOWN TRACK CORRODED.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800096	20020408	00096	NM  	2002	4	8	AUS20020243      	1	20020122	G	5347		TRACK           	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		SEAT/CARGO ATTAC	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) CARGO TRACK CORRODED. TRACK IS LOCATED IN ZONE 1-13 SECTION 43, STN 540 TO STN 600 WL 156, BL16.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800097	20020408	00097	NM  	2002	4	8	AUS20020244      	1	20020123	G	5344	69339561	PLATE           	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		FUSELAGE DOOR HI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) CARGO DOOR HINGE SUPPORT PLATE CORRODED. PLATE IS LOCATED IN ZONE 2-48, STN 520 TO STN 530, STRINGER 55LH.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800098	20020408	00098	NM  	2002	4	8	AUS20020245      	1	20020125	G	5343		FRAME           	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		LANDING GEAR ATT	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) RH MAIN LANDING GEAR WHEEL WELL DOOR SEQUENCING STRIKER FRAME CORRODED. FRAME LOCATED IN ZONE 1-36, STN 880, STRIN	GER 520RH,WL157, BL70RH.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800099	20020408	00099	NM  	2002	4	8	AUS20020246      	1	20020130	G	5343		SUPPORT         	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		LANDING EAR ATTA	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) LH MAIN LANDING GEAR DOOR SEQUENCING STRIKER FRAME CORRODED.LOCATION OF CORROSION ZONE 1-35, STN 880, STRINGER 20L	H, WL 152,BL70LH.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040900005	20020409	00005	NM  	2002	4	9	AUS20020247      	1	20020129	G	5320		STIFFENER       			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG WW	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			58266							(AUS) LT MAIN LANDING GEAR BAY STIFFENER CHORD CORRODED IN SEVERAL AREAS INCLUDING ATTACHMENT TO PRESSURE DECK. CORROSIO	N LOCATED IN ZONE 1-35, STN 870, STRINGER 20 LT TO STRINGER 17, WL 208 TO WL184, BL 67 LT.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040900006	20020409	00006	NM  	2002	4	9	AUS20020248      	1	20020130	G	5710		STRUCTURE       			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			58266							(AUS) UPPER RT WING TOP CHORD CORRODED. CORROSION LOCATED AT ZONE 6-76, WS 351RT TO WS 355 RT.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040900007	20020409	00007	NM  	2002	4	9	AUS20020249      	1	20020130	G	5711		SPAR            			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			58266							(AUS) LT REAR WING SPAR UPPER AND LOWER CHORDS CORRODED IN AREA LOCATED BEHIND THE VERTICAL STIFFENER. CORROSION LOCATED	 AT ZONE 6-72, WS 437 TO WS 438 LT.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800100	20020408	00100	NM  	2002	4	8	AUS20020250      	1	20020206	G	5230		DOOR            	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		CARGO/BAGGAGE DO	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) MAIN CARGO DOOR STRUCTURE CORRODED AT THE LAP JOINT LOCATED ATSTN 620. CORROSION LOCATED AT ZONE 2-48, STN 620 TO 	STN 623,STRINGER 4LH TO STRINGER 5.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800101	20020408	00101	NM  	2002	4	8	AUS20020251      	1	20020206	G	5230		DOOR            	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		CARGO/BAGGAGE DO	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) MAIN CARGO DOOR STRUCTURE LAP JOINT CORRODED AT STN 620.CORROSION IS LOCATED AT ZONE 2-48, STN 620 TO STN 623, STR	INGER 9LH TO STRINGER 11.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800102	20020408	00102	NM  	2002	4	8	AUS20020252      	1	20020206	G	5310		SKIN            	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		FUSELAGE MAIN, S	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) MAIN CARGO DOOR SUPPORT STRUCTURE TOP FORWARD CORNER CORRODED.CORROSION LOCATED AT ZONE 2-24, STN 48D, STRINGER 1L	H TO STRINGER 3.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040800103	20020408	00103	NM  	2002	4	8	AUS20020253      	1	20020127	G	5330		SKIN            	            	            	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		FUSELAGE MAIN, P	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		58266							(AUS) SKIN CORRODED IN AREA BELOW TOILET SERVICE DOOR. CORROSIONLOCATED AT ZONE 2-11, STN 350 TO STN 370, STRINGER 18RH.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002040900008	20020409	00008	EU  	2002	4	9	AUS20020254      	1	20020226	G	3260		SWITCH          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWNLOCK SWITCH FAILED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002040800104	20020408	00104	NM  	2002	4	8	AUS20020256      	1	20020316	G	2740	91238071	RELAY           	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		STABILIZER CONTR	FAULTY          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 	 									(AUS) STABILISER TRIM RELAY FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002040800105	20020408	00105	SO  	2002	4	8	AUS20020257      	1	20020306	G	3230	41963001	HOOK            	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR DOWNLOCK HOOK ASSEMBLY CLIP SECURING RIVETS CORRODED. ONE RIVET HEAD SHEARED AND ONE RIVET HEAD 	CORRODED. THE DEFECTIVE PART IS LOCATED IN THE AREA OF THE ENGINE EXHAUST.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002040800106	20020408	00106	CE  	2002	4	8	AUS20020259      	1	20020222	G	5342		MOUNT           	            	            	BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A1B    	41514	EA  	MCAULY	2D34C	2D34C9      	GL  	FUSELAGE, STABIL	CORRODED        	W			    	K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 	 									(AUS) STABILATOR MOUNTING BLOCK RIVETS SHEARED. INVESTIGATION FOUND THE UNDERSIDE OF THE ATTACHMENT BLOCK BADLY CORRODED	 AND THE RIVETS CORRODED.					1	L	7	1 	3O	3	O	 	A1CE    	1E10	5	C	P7EA	 
2002040900009	20020409	00009		2002	4	9	AUS20020260      	4	20020315	G	3420	6466350	INDICATOR       			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	INACCURATE      	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) STANDBY HORIZON OUT OF LIMITS COMPARED WITH ADI.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2002040800107	20020408	00107	NE  	2002	4	8	AUS20020262      	2	20020318	G	7260	1155550259	SHAFT           	PWA         	PT6A42      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	TURBINE ENGINE A	SHEARED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 	 									(AUS) RH ENGINE AIRCONDITIONING COMPRESSOR PULLEY DRIVE QUILL SHAFT SHEARED. LOSS OF ENGINE OIL.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002040900010	20020409	00010	CE  	2002	4	9	AUS20020263      	1	20020312	G	2711	57152801	PUSHROD         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	AILERON TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AILERON TRIM TAB PUSH ROD AFT ROD END CRACKED ACROSS BEARING RETAINER. RODEND BEARING CORRODED.  CRACK FOUND WH	EN PUSHROD WAS REMOVED FOR REPLACEMENT DUE TO WEAR.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2002040800108	20020408	00108	SW  	2002	4	8	AUS20020264      	1	20020303	G	2910	2781032626	LINE            	            	            	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYSTEM	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HYDRAULIC SUCTION LINE WORN THROUGH BY ELECTRICAL WIRINGASSOCIATED WITH THE LH OUTBOARD GEAR DOOR POSITION SWITCH.	 THELINE IS VISIBLE THROUGH PANEL 513 LOCATED IN THE LH WHEEL WELL.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2002040900011	20020409	00011	CE  	2002	4	9	AUS20020265      	1	20020313	G	3297		WIRE            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					MLG POSITION	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR POSITION SYSTEM WIRE BROKEN.  WIRE WAS LOCATED IN THE WIRING LOOM IN THE UNDERCARRIAGE BAY.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002040800109	20020408	00109	EU  	2002	4	8	AUS20020266      	1	20020315	G	7920	B590065	PIPE            	LYC         	IO540K1B5   	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE OIL DISTR	LOOSE           	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 									(AUS) RH ENGINE CRANKCASE TO OIL COOLER PIPE LOOSE AND LEAKING. ENGINEHAD BEEN RECENTLY REPLACED. PERSONNEL/MAINTENANCE 	ERROR.					1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002040900012	20020409	00012	CE  	2002	4	9	AUS20020267      	1	20020320	G	1430	12NB126	NUT             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					RT WING	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER RT WING REAR ATTACHMENT NUT INCORRECT PART. UNAPPROVED PART.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002040900013	20020409	00013	CE  	2002	4	9	AUS20020268      	1	20020320	G	1430	12NB126	NUT             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					LT WING	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER LT WING REAR ATTACHMENT NUT INCORRECT PART. UNAPPROVED PART.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002040900014	20020409	00014	CE  	2002	4	9	AUS20020269      	1	20020320	G	5741	EB126	NUT             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					LT WING	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER LT WING FORWARD ATTACHMENT NUT INCORRECT PART. UNAPPROVED PART.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002040900015	20020409	00015	SW  	2002	4	9	AUS20020270      	1	20020321	G	2731	DL504DM5	ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ELEVATOR TAB	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			2635 							(AUS) PITCH TRIM ACTUATOR MOTOR FAILED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2002040900016	20020409	00016	NM  	2002	4	9	AUS20020271      	1	20020321	G	7830	LJ34179	BLOCKER DOOR    			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					THRUST REVERSER	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 4 ENGINE THRUST REVERSER NR 5 BLOCKER DOOR SEPARATED IN FLIGHT.  DAMAGE CAUSED TO RT OUTBOARD AILERON.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2002040800110	20020408	00110	SW  	2002	4	8	AUS20020272      	1	20020301	G	2710	730006000	LINK            	            	            	MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	MCAULY	2D34C	2D34C53     	GL  	AILERON CONTROL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AILERON CONTROL LINK CRACKED IN WELD JOIN.						1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P7EA	 
2002040800111	20020408	00111	SW  	2002	4	8	AUS20020273      	1	20020301	G	2710	7300051	LINK            	            	            	MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	MCAULY	2D34C	2D34C53     	GL  	AILERON CONTROL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AILERON CONTROL LINK CRACKED AT WELDED JOIN.						1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P7EA	 
2002040900017	20020409	00017	EU  	2002	4	9	AUS20020274      	1	20020115	G	2424	700122490420	GCU             			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AC REGULATOR	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 			28394							(AUS) NR 1 GENERATOR CONTROL UNIT (GCU) FAULTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2002040900018	20020409	00018	SW  	2002	4	9	AUS20020275      	1	20020321	G	6120		ROD END         			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROP CONTROL	DISCONNECTED    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) PROPELLER GOVERNOR CONTROL ROD RODEND DISCONNECTED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2002040800112	20020408	00112	NM  	2002	4	8	AUS20020276      	1	20020308	G	6310	405H	ACTUATOR        	            	            	ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  	 		            		ENGINE/TRANSMISS	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 	 		6    							(AUS) CLUTCH ACTUATOR UNSERVICEABLE. ACTUATOR UP LIMIT SWITCH STUCK INOPEN CIRCUIT POSITION PREVENTING RETENSIONING OF D	RIVE BELTS.					1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2002040800113	20020408	00113	EA  	2002	4	8	AUS20020277      	2	20020207	G	8520	L714361A	BEARING         	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	MCAULY	3DF36C	B3DF36C526  	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		720  		L714361A					(AUS) CONNECTING ROD BEARINGS AND MAIN BEARINGS LOOSING WHITE-METAL.METAL CONTAMINATION OF OIL FILTER.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	 	 
2002040800114	20020408	00114	SO  	2002	4	8	AUS20020278      	1	20020203	G	5341		FITTING         	            	            	PIPER 	PA36  	PA36285     	7103610	SO  	CONT  	6285  	6285C       	17038	SO  	HARTZL	HCC2Y	HCC2YF1     	GL  	FUSELAGE, WING A	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING ATTACHMENT LUG BROKEN. SUSPECT DAMAGED DURING A PREVIOUSCRASH.						1	L	7	1 	3O	3	O	 	A10SO   	E12CE	5	C	P920	 
2002040800115	20020408	00115	GL  	2002	4	8	AUS20020279      	1	20020319	G	2434	ES4139	HOUSING         	FORD        	DOFF10300D  	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	DC GENERATOR-ALT	CRACKED         	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 	 		160  		9070246					(AUS) ALTERNATOR FRONT HOUSING WEBS CRACKED.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2002040800116	20020408	00116	EU  	2002	4	8	AUS20020280      	1	20020326	G	7922	230379401	VALVE           	LYC         	ALF502R3A   	BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  	 		            		ENGINE OIL TEMPE	FAULTY          	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 									(AUS) NO3 ENGINE OIL COOLER FUEL SYSTEM VERNATHERM VALVE SUSPECTFAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2002040900019	20020409	00019	NM  	2002	4	9	AUS20020281      	1	20020323	G	2910	9741735	HOSE            			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					HYDRAULIC SYSTEM	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 1 ADP PRESSURE HOSE LOCATED BETWEEN THE PUMP AND THE PRESSURE MODULE RUPTURED. LOSS OF HYDRAULIC FLUID.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2002040800117	20020408	00117	NM  	2002	4	8	AUS20020282      	1	20020326	G	2912	271T006810	MODULE          	            	            	BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  	 		            		HYDRAULIC FILTER	FAULTY          	W			    	K	 	 	 	NONE                    				K	J	 	FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 	 				00477					(AUS) HYDRAULIC FILTER MODULE FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2002040900020	20020409	00020	SW  	2002	4	9	AUS20020283      	2	20020311	G	8530	4300C	CYLINDER        			CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A2      	35006	SW  	HAMSTD	2B	2B20        	NE  	ENGINE	SEPARATED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			271  							(AUS) ENGINE CYLINDERS (2OFF) LEAKING PAST EXHAUST VALVE. DURING CYLINDER REMOVAL THE CYLINDER HOLD DOWN NUTS WERE FOUND	 TO BE LOOSE. RED SILICONE SEALANT WAS ALSO FOUNDS AROUND THE BASE OF THE CYLINDERS AND STUCK TO THE CYLINDER BASE O-RIN	GS.				1	H	7	1 	3R	3	R	NC	A790    	TC237	5	C	P255	 
2002040900021	20020409	00021	NE  	2002	4	9	AUS20020284      	1	20020318	G	6320	7635109500043	GEARBOX         			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					MAIN ROTOR	MAKING METAL    	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 			1534 		A08100352					(AUS) MAIN TRANSMISSION CHIP DETECTOR CONTAMINATED WITH METAL. AMOUNT OF METAL ON DETECTORS WAS BEYOND MANUFACTURERS LIM	ITS AND THE TRANSMISSION WAS CHANGED.					1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2002040800118	20020408	00118	SO  	2002	4	8	AUS20020285      	1	20020326	G	3230	95299	STUD            	            	            	PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LANDING GEAR RET	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR SIDE BRACE STUDS (2OFF) CRACKED IN RADIUS.FOUND DURING MPI INSPECTION IAW AD/PA32/79.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2002040900022	20020409	00022	EU  	2002	4	9	AUS20020286      	1	20020315	G	3260	L1336	BULB            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG INDICATOR	BURNED OUT      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT LANDING GEAR DOWN AND LOCKED INDICATOR BULB BLOWN.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2002050900070	20020509	00070	NM  	2002	5	9	AUS20020287      	1	20020329	G	2731		BEARING         			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ELEVATOR TAB	LACK OF LUBE    	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) ELEVATOR TRIM TAB BEARING DRY. MOISTURE AND PAINT STRIPPER FOUND AROUND TRIM TAB BEARINGS AND ACTUATORS.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051000001	20020510	00001	CE  	2002	5	10	AUS20020288      	1	20020328	G	3221	5842000211	TRUNNION        			CESSNA	441   	441         	2076020	CE  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			500  							(AUS) NLG TRUNNION CRACKED. FOUND DURING INSPECTION IAW SBCQB00-3.						1	L	7	2 	3T			RT	A28CE   					 
2002051000002	20020510	00002	SW  	2002	5	10	AUS20020289      	1	20020327	G	3230	KRP5064B	ROLLER          			SWRNGN	SA227 	SA227*      	       	SW  										LANDING GEAR RET	MISSING         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR UPLOCK ROLLER MISSING. SUSPECT ATTACHMENT BOLT SHEARED.						2	L	7	2 	4T			RT	A5SW    					 
2002051000003	20020510	00003	SW  	2002	5	10	AUS20020290      	1	20020125	G	5270	2720039039	SWITCH          			SWRNGN	SA227 	SA227*      	       	SW  										DOOR WARNING SYS	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) CARGO DOOR WARNING SWITCH FAULTY.						2	L	7	2 	4T			RT	A5SW    					 
2002050700069	20020507	00069	GL  	2002	5	7	AUS20020291      	1	20020320	G	5302		SKIN            	ENSTRM      	F28C        	ENSTRM	F28   	F28C        	3300407	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  	 		            		ROTORCRAFT TAIL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		640  							(AUS) TAIL CONE SKIN CRACKED IN AREA UNDER RADIO AERIAL.						1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2002051000004	20020510	00004	GL  	2002	5	10	AUS20020292      	1	20020320	G	5302	VARIOUS	BULKHEAD        			ENSTRM	F28   	F28C        	3300407	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					TAILBOOM	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			640  							(AUS) TAIL BOOM BULKHEAD AND SKINS CRACKED. INCORRECT ANCHOR NUTFITTED.						1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2002051000005	20020510	00005	CE  	2002	5	10	AUS20020293      	1	20020327	G	5312		BULKHEAD        			CESSNA	182   	182P        	2075816	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FORWARD DOORPOST BULKHEAD CRACKED. FOUND DURING INSPECTION IAW AD/C180/75 A2.						1	H	7	1 	3O			NT	TA13    					 
2002050700070	20020507	00070	SO  	2002	5	7	AUS20020294      	1	20020327	G	3233	451826	ACTUATOR        	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR ACT	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) NOSE LANDING GEAR ACTUATOR LEAKING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002050700071	20020507	00071	EA  	2002	5	7	AUS20020295      	2	20020320	G	7310	2540888	DIAPHRAGM       	BENDIX      	25241784    	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ENGINE FUEL DIST	DAMAGED         	W			    	K	 	 	 	NONE                    				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 	 		1817 		UJ6					(AUS) LH ENGINE MANIFOLD VALVE DIAPHRAGM TORN. LENGTH OF TEAR APPROXIMATELY 12.7MM (0.5IN).						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2002051000006	20020510	00006	EU  	2002	5	10	AUS20020296      	1	20020402	G	2910	HTE9531101	ISOLATION VALVE 			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 2 HYDRAULIC SYSTEM ISOLATION VALVE LEAKING INTERNALLY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2002051000007	20020510	00007		2002	5	10	AUS20020297      	4	20020329	G	2565		BOTTLE          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ESCAPE SLIDE	DISCHARGED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					GV207					(AUS) FORWARD RT DOOR SLIDE INFLATION BOTTLE HAD NO PRESSURE.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002051000008	20020510	00008	GL  	2002	5	10	AUS20020298      	3	20020327	G	6114	C471658	HUB             			CESSNA	188   	A188A       	2073008	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB NR 2 SOCKET CRACKED.						1	L	7	1 	3O	3	O	 	A9CE    	E5CE	5	C	P3EA	 
2002051000009	20020510	00009	NM  	2002	5	10	AUS20020299      	1	20020327	G	3320	BV0330211150	SOCKET          			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CABIN	ARCED           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) LT SIDE NR 2 FLUORESCENT TUBE END SOCKET ARCING.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051000010	20020510	00010	WP  	2002	5	10	AUS20020300      	2	20020330	G	7261	8659307	SHAFT           			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	SCAV PUMP	SHEARED         	W				O				OTHER                   				K	E	J	FLUID LOSS                	VIBRATION/BUFFET          	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			2578 							(AUS) RT ENGINE OIL SCAVENGE PUMP SHAFT SHEARED.  SHAFT THEN MIGRATED OUT OF THE SUPPORT HOUSING CAUSING DAMAGE TO ENGIN	E GEAR TRAIN AND SHAFT.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2002050700072	20020507	00072	CE  	2002	5	7	AUS20020301      	1	20020321	G	2822	2B729	PUMP            	AIRBORNE    	2B729       	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	FUEL BOOST PUMP	RUSTED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 				6AC181					(AUS) FUEL BOOST PUMP SOLENOID RUSTY CAUSING THE PUMP TO INTERMITTENTLY SWITCH TO HIGH' WHEN SELECTED TO LOW'.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002050700073	20020507	00073	NM  	2002	5	7	AUS20020302      	1	20020403	G	2841	114001224	INDICATOR       	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUEL QUANTITY IN	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAGNA STICK INNER INDICATOR SCALE AND END FITTING MISSING.DAMAGE CAUSED TO LOWER WING SKIN.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051000011	20020510	00011	CE  	2002	5	10	AUS20020303      	1	20020328	G	2460		CURRENT LIMITER 			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	DC POWER	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) PILOT EXPERIENCED COMPLETE LOSS OF ELECTRICAL POWER WHEN THE UNDERCARRIAGE WAS RETRACTED AFTER TAKE-OFF. INVESTIGA	TION FOUND THE BUS 1 AND 2 CURRENT LIMITERS BLOWN. FURTHER INVESTIGATION FOUND THE ALTERNATOR BLOCKING DIODE HAD AN UNSE	RVICEABLEINSULATOR THAT WAS SHORTING ALTERNATOR OUTPUTS TO EARTH.				1	L	7	2 	3O	3	O	 	A29CE   	E286	5	C	P43GL	 
2002051000012	20020510	00012	NM  	2002	5	10	AUS20020304      	1	20020329	G	3250	257T4120	TILLER          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					MLG STEERING	STIFF           	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 					00231					(AUS) FIRST OFFICERS TILLER GEARBOX STIFF IN OPERATION.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002051000013	20020510	00013	NM  	2002	5	10	AUS20020305      	1	20020403	G	5210		HANDLE          			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					PAX DOOR	OUT OF ADJUST   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) L5 DOOR HANDLE RIGGING OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2002050700074	20020507	00074	NM  	2002	5	7	AUS20020307      	1	20020403	G	5610	8SC0043008	WINDSHIELD      	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FLIGHT COMPARTME	DELAMINATED     	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 									(AUS) FIRST OFFICERS WINDSHIELD DELAMINATED BEYOND LIMITS.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002050700075	20020507	00075	NM  	2002	5	7	AUS20020308      	1	20020403	G	5730	85700001001	SKIN            	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	WING, PLATES/SKI	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LOWER WING SKIN DAMAGED WHEN MAGNA STICK FAILED AND SEPARATED FROM THE AIRCRAFT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002050700076	20020507	00076	EU  	2002	5	7	AUS20020310      	1	20020106	G	5420	7254200016	CHANNEL         	            	            	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	NACELLE/PYLON, M	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		34097							(AUS) RH ENGINE NACELLE CHANNEL CRACKED UNDER DOUBLER AT STN NS 240.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2002051300001	20020513	00001	EA  	2002	5	13	AUS20020311      	1	20020323	G	2430	A700ZF	RELAY           			CURTIS	P40   	P40NREED    	2622206	EA  	ALLSN 	V1710 	V1710*      	 	GL  					DC GENERATING SY	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					AVR605					(AUS) REVERSE CURRENT RELAY (RCR) FAILED. BATTERY DISCHARGED ANDRESULTED IN A TOTAL POWER FAILURE.						1	L	7	1 	4V	4	V	 	L182    	EXPE4V				 
2002050700077	20020507	00077	NM  	2002	5	7	AUS20020312      	1	20020405	G	5610	NAS44037	SCREW           	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FLIGHT COMPARTME	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FIRST OFFICERS FORWARD WINDSHIELD HAD TWO SCREWS WITH BROKENHEADS. SHANK AND THREADS STILL IN PLACE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002050700078	20020507	00078	NM  	2002	5	7	AUS20020313      	1	20020301	G	3210	MS24586C192	SPRING          	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MAIN LANDING GEA	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR LOCK SPRING BROKEN.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051000051	20020510	00051	EU  	2002	5	10	AUS20020314      	1	20020404	G	2421	503106680003	GENERATOR       	PLESSEY     	50306710000 	BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					AC GENERATOR	CONTAMINATED    	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 					TE1206					(AUS) NR 1 INTEGRATED DRIVE GENERATOR CONTAMINATED.  OPEN CIRCUIT ON FIELD WINDINGS.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2002050700079	20020507	00079	SW  	2002	5	7	AUS20020315      	1	20020407	G	5753	NAS130838D	BOLT            	            	            	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	TRAILING EDGE FL	BROKEN          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 	 				PN2736043010					(AUS) RH OUTBOARD FLAP ATTACHMENT BRACKET AND FLAP DISTORTED. INVESTIGATION FOUND THE BELLCRANK ATTACHMENT BOLT BROKEN. 	DAMAGEWAS FOUND TO A NUMBER OF RIBS AND BRACKETS LOCATED IN THE FLAPRECESS.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2002051000066	20020510	00066	NM  	2002	5	10	AUS20020316      	1	20020328	G	5514		BEAM            			BOEING	737   	73733A      	1384673	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HORIZONTAL STABILIZER UPPER TRAILING EDGE BEAM CORRODED IN AREA OF ELEVATOR STA 111.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002051000067	20020510	00067	WP  	2002	5	10	AUS20020317      	2	20020402	G	7261		O-RING          			FLTCHR	24    	FU24AIRPTS  	3530202	WP  	GARRTT	TPE331	TPE33110    	01514	WP  					OIL FILTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL FILTER O-RING SEAL RETAINING LAND WORN AND BROKEN  AWAY.						1	L	7	1 	3O	4	T	 	4A12    	E4WE				 
2002051000068	20020510	00068	NM  	2002	5	10	AUS20020318      	1	20020406	G	2910	BACT16AS060608W	FITTING         			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC SYSTEM TEE FITTING CRACKED AND CORRODED. FITTING IS IN  THE HYDRAULIC LINE TO THE LH HEAT EXCHANGER.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002050700080	20020507	00080	NM  	2002	5	7	AUS20020319      	1	20020406	G	7830	315A18141	NUT             	GE          	CFM563C     	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		THRUST REVERSER	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO1 ENGINE THRUST REVERSER FAULTY. FEEDBACK LEVER AND CABLE COULD BE MOVED FROM THE STOWED POSITION TO THE DEPLOYE	D POSITION WITH THE THRUST REVERSER LOCKED OUT. INVESTIGATION FOUND THE PROBLEM WAS CAUSED BY WEAR ON THE FEEDBACK NUT P	NO 315A1814-1.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002050700081	20020507	00081	NM  	2002	5	7	AUS20020320      	1	20020404	G	2761	6544851	HOUSING         	            	            	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		DRAG CONTROL ACT	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING NO4 GROUND SPOILER OUTBOARD ACTUATOR HOUSING HAD A SMALLPIECE OF THE BEARING LUG BROKEN AWAY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002050700082	20020507	00082	EA  	2002	5	7	AUS20020321      	2	20020302	G	8530	73413	PUSHROD         	LYC         	O320B2C     	ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  	 		            		RECIPROCATING EN	DISTORTED       	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 	 		330  		L1180039A					(AUS) NO4 CYLINDER EXHAUST VALVE PUSHROD BENT. EXHAUST VALVE DID NOTAPPEAR TO BE STUCK OR TIGHT IN THE VALVE GUIDE.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002051000069	20020510	00069	WP  	2002	5	10	AUS20020323      	2	20020327	G	7261	3102173	PUMP            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LT ENGINE	CRACKED         	W				O				OTHER                   				K	E		FLUID LOSS                	VIBRATION/BUFFET          		CR	CRUISE         	1			AU	S 			72   							(AUS) LT ENGINE OIL PRESSURE PUMP CRACKED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2002050700083	20020507	00083	EA  	2002	5	7	AUS20020324      	2	20020330	G	8520		CRANKSHAFT      	LYC         	O540E4C5    	BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	O540E4C5    	41532	EA  	 		            		RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	D	 	VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CL	CLIMB          	1			AU	S 	 									(AUS) CRANKSHAFT FRACTURED IN AREA JUST FORWARD OF THE NO2 MAIN BEARING. CRANKCASE FRACTURED AND SEPARATED FROM ENGINE. 	PROPELLER SEPARATED. DAMAGE TO COWLS AND FUSELAGE. AIRCRAFT ISREGISTERED IN VANUATU.					1	H	7	2 	3O	3	O	 	A17EU   	E295				 
2002050700084	20020507	00084	CE  	2002	5	7	AUS20020325      	1	20020313	G	2720	VARIOUS	BOLT            	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	RUDDER CONTROL S	LOOSE           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		3775 							(AUS) FORWARD RUDDER PUSH-PULL TUBE FORWARD BELLCRANK BOLTS LOOSE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002050700085	20020507	00085	NM  	2002	5	7	AUS20020326      	1	20020405	G	3250	980222001	SWITCH          	            	            	PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	LANDING GEAR STE	INTERMITTENT    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NOSE LANDING GEAR STEERING SWITCH INTERMITTENT IN OPERATION.BRAKE CALIPERS LEAKING.						1	M	7	2 	3O	3	O	RT	A17WE   	E14EA	5	C	P25EA	 
2002051000070	20020510	00070	EA  	2002	5	10	AUS20020327      	2	20020405	G	7314	BB017	SEAL            			NEWZE 	FU24  	FU24954     	6280102	WP  	LYC   	O720  	IO720A1B    	41546	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE FUEL PUMP	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			284  							(AUS) ENGINE FUEL PUMP REAR SEAL LEAKING. FOUND DURING INSPECTION IAW AD/FSM/25.						1	L	7	1 	3O	3	O	 	A9PC    	1E15	5	C	P25EA	 
2002051000071	20020510	00071	CE  	2002	5	10	AUS20020328      	1	20020328	G	2700		CONTROL CABLE   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FLIGHT CONTROLS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALL AILERON SYSTEM CABLES AND FLAP CABLES (4OFF) HAD BROKEN STRANDS OR WERE WORN EXCESSIVELY.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002051000072	20020510	00072	CE  	2002	5	10	AUS20020329      	1	20020328	G	7603		BRACKET         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	POWER LEVER	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) THROTTLE AND MIXTURE CABLE CLAMP BRACKET INSTALLED UPSIDE DOWN.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002051000073	20020510	00073	SO  	2002	5	10	AUS20020330      	2	20020328	G	8550		LINE            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE OIL	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) CRANKCASE OIL PRESSURE LINE LOOSE.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002050700086	20020507	00086	GL  	2002	5	7	AUS20020331      	2	20020328	G	7532	23039404	BLEED VALVE     	ALLSN       	23039404    	HUGHES	369   	369E        	4470707	WP  	ALLSN 	25OC  	250C20R     	 	GL  	 		            		COMPRESSOR BLEED	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 	 		678  		FF32777					(AUS) COMPRESSOR BLEED VALVE SUSPECT STICKING.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002050700087	20020507	00087	CE  	2002	5	7	AUS20020332      	1	20020328	G	7120	05510171	MOUNT           	LYC         	O320E2D     	CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE MOUNT SEC	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE MOUNT CRACKED IN AREA OF LOWER CROSSOVER TUBE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002050700088	20020507	00088	CE  	2002	5	7	AUS20020333      	1	20020321	G	7120	05510171	MOUNT           	LYC         	O320E2D     	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE MOUNT SEC	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE MOUNT CRACKED IN AREA OF LOWER CROSSOVER TUBE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002051000074	20020510	00074	NM  	2002	5	10	AUS20020334      	1	20020408	G	2750		CONTROL CABLE   			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					TE FLAPS	MISROUTED       	W				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		LD	LANDING        	1			AU	S 										(AUS) FLAP CABLE RUN NR 244B BROKEN. FLAP CABLE RUN NO 242B FRAYED. INVESTIGATION FOUND THE CABLES HAD BEEN INCORRECTLY 	ROUTED ON THE WRONG SIDE OF THE PULLEY CABLE KEEPER. SUSPECT CAUSED DURINGAIRCRAFT MANUFACTURE. PERSONNEL/MAINTENANCE/MA	NUFACTURING ERROR.				2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2002051000079	20020510	00079	NE  	2002	5	10	AUS20020335      	2	20020402	G	7321	1853M33P06	EEC             			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					LT ENGINE	FAILED          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LT ENGINE ELECTRONIC CONTROL UNIT (EEC) SUSPECT FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2002050700089	20020507	00089	NM  	2002	5	7	AUS20020336      	1	20020124	G	5312		BULKHEAD        	            	            	BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		FUSELAGE MAIN, B	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		55274							(AUS) FUSELAGE BULKHEAD LOCATED AT BS 950 CONTAINED LEVEL 2 CORROSION IN LOWER CHORD.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002051000080	20020510	00080	NM  	2002	5	10	AUS20020337      	1	20020124	G	5314		KEELBEAM        			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			55274							(AUS) KEELBEAM EXTENSION CONTAINED LEVEL 2 CORROSION IN THE AREA LOCATED BETWEEN STN BS 950.12 AND BS 957.12 BL6L.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002051000081	20020510	00081	NM  	2002	5	10	AUS20020338      	1	20020409	G	2620	6546858302	LINE            			BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					EXTINGUISHER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRE EXTINGUISHER LINE AND B-SYSTEM CASE DRAIN LINE CHAFING IN  AREA ADJACENT TO NR 6 FLAP TRACK. HOLE WORN IN EXT	INGUISHER LINE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002051000082	20020510	00082	CE  	2002	5	10	AUS20020339      	1	20020410	G	8120	4066109028	TURBOCHARGER    			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		TO	TAKEOFF        	1			AU	S 			94   							(AUS) ENGINE TURBOCHARGER FAULTY.  INVESTIGATION FOUND BLADE TIP RUBBING AND SHAFT BENT.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002050700090	20020507	00090	CE  	2002	5	7	AUS20020340      	1	20020329	G	5342	12324001	BRACKET         	            	            	CESSNA	210   	210M        	2073450	CE  	LYC   		            			MCAULY	D3A34	D3A34C402   	GL  	FUSELAGE, STABIL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH REAR HORIZONTAL STABILISER ATTACHMENT BRACKET CRACKED.						1	H	7	1 	3O			 	3A21    		5	C	P47GL	 
2002051000083	20020510	00083	SW  	2002	5	10	AUS20020342      	1	20020410	G	2910	27810322683	LINE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) STAINLESS STEEL HYDRAULIC PRESSURE LINE WORN THROUGH ON ADEL CLAMP BOLT. PIPE IS LOCATED BETWEEN HYDRAULIC PUMP AN	D FIREWALL.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2002050700091	20020507	00091	NE  	2002	5	7	AUS20020343      	2	20020319	G	7320	0301037290	PIPE            	TMECA       	ARRIEL1D1   	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  	 		            		FUEL CONTROLLING	LOOSE           	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 	 				9103					(AUS) P2 REGULATOR PIPE FROM THE COMPRESSOR SCROLL TO THE FCU LOOSE.PERSONNEL/MAINTENANCE ERROR.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002051000084	20020510	00084	SW  	2002	5	10	AUS20020344      	1	20020411	G	6220	471201171	HUB             			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			968  							(AUS) MAIN ROTOR HUB CRACKED IN AREA OF BEARING SPINDLE RADIUS. FOUND DURING INSPECTION IAW AD/BELL47/72 A2.						1	G	7	1 	3O	3	O	 	2H3     	1E13				 
2002050700092	20020507	00092	CE  	2002	5	7	AUS20020345      	1	20020303	G	5741	12210302	FITTING         	CESSNA      	210M        	CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	WING, FUSELAGE A	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING ATTACHMENT FITTING CONTAINED A SUBSURFACE DEFECT IN THE AREA ADJACENT TO BUT NOT INTO THE MAIN WING ATTACH	MENT BOLT HOLE. FOUND DURING EDDY CURRENT INSPECTION.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002051000085	20020510	00085	EU  	2002	5	10	AUS20020346      	1	20020412	G	2910	HTE96352	SELECTOR VALVE  			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYD SYSTEM	LEAKING         	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) YELLOW HYDRAULIC SYSTEM SELECTOR VALVE INTERNAL LEAK.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2002050700093	20020507	00093	CE  	2002	5	7	AUS20020347      	1	20020403	G	5540	51310123	HINGE           	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RUDDER STRUCTURE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CENTRE RUDDER HINGE CRACKED ON LH SIDE OF THE LOWER SIDE OF THE FORWARD HALF.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002051000086	20020510	00086	NM  	2002	5	10	AUS20020348      	1	20020415	G	2761	NAS161210	O-RING          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					DRAG ACTUATOR	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 1 SPOILER ACTUATOR FILTER BLANKING PLUG O-RING SEAL LEAKING.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002051000087	20020510	00087	EU  	2002	5	10	AUS20020349      	1	20020415	G	2740	AN2418A	BOLT            			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	STAB CONTROL	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR FORWARD CONTROL ROD BOLT INSTALLED IN INCORRECT DIRECTION.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2002051000088	20020510	00088	EU  	2002	5	10	AUS20020350      	1	20020416	G	2740	68330252	KEY             			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	STAB CONTROL	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR KEYS (2OFF) WERE UNAPPROVED HANDMADE PARTS. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2002050700094	20020507	00094	SW  	2002	5	7	AUS20020351      	1	20020408	G	3213	5200011	STRUT           	            	            	MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	MCAULY	2D34C	2D34C53     	GL  	MAIN LANDING GEA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR LEG ASSEMBLY CRACKED AT THE UPPER FORWARDWELD JOINT.						1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P7EA	 
2002050700095	20020507	00095	SW  	2002	5	7	AUS20020352      	1	20020415	G	2510		SEAT BELT       	            	            	MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	MCAULY	2D34C	2D34C53     	GL  	FLIGHT COMPARTME	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) BOTH FORWARD SEAT BELTS WERE OF UNKNOWN ORIGIN WITH NOIDENTIFICATION LABLES. BELTS WERE IN EXTREMELY POOR CONDITIO	N.BELTS DID NOT MEET THE REQUIREMENTS OF AD/RES/29. UNAPPROVEDPART. PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P7EA	 
2002051000089	20020510	00089		2002	5	10	AUS20020353      	4	20020318	G	2565		PIN             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ESCAPE SLIDE	INSTALLED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT FORWARD DOORS AND LT AFT DOOR ESCAPE SLIDES HAD MAINTENANCE SAFETY PINS INSTALLED. PERSONNEL/MAINTENANCE	 ERROR.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002051000090	20020510	00090	EU  	2002	5	10	AUS20020354      	1	20020414	G	2460	MS33205	CIRCUIT BREAKER 			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	DC POWER	FAULTY          	W				O				OTHER                   				B	N		SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             		CR	CRUISE         	1			AU	S 										(AUS) CARGO/LAVATORY CIRCUIT BREAKER SUSPECT FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2002051000091	20020510	00091	CE  	2002	5	10	AUS20020355      	1	20020417	G	3233	98820041	PISTON          			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  					MLG ACTUATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR ACTUATOR PISTON AND GEAR TEETH DAMAGED. FOUND DURING INSPECTION IAW SEB 01-2 REV1. SUSPECT DAMAG	E OCCURRED DURING A PREVIOUS ACCIDENT.					1	H	7	1 	3O	3	O	RT	3A21    	E5CE				 
2002051000092	20020510	00092	GL  	2002	5	10	AUS20020356      	3	20020412	G	6114	C32303	HUB             			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	PROPELLER	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB HAD BEEN MACHINED IN THE AREA OF THE PRELOAD PLATE SHELF TO REMOVE DAMAGE CAUSED BY A GROUND STRIKE.	 MACHINING INTHIS AREA IS NOT APPROVED BY THE MANUFACTURER. UNAPPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	2A13    	E295	5	C	P27EA	 
2002051000093	20020510	00093	CE  	2002	5	10	AUS20020357      	1	20020410	G	2500	18836C200	RELAY           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	STRETCHER LOAD	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRETCHER LOADING DEVICE RELAY FAILED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002051000094	20020510	00094	NM  	2002	5	10	AUS20020358      	1	20020414	G	2782	4135T1003	ACTUATOR        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LE SLATS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INBOARD LEADING EDGE SLAT DRIVE ACTUATOR FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002051000095	20020510	00095	NE  	2002	5	10	AUS20020359      	1	20020316	G	6410	7610105501042	BLADE           			SKRSKY	S76   	S76B        	8143007	NE  										TAIL ROTOR	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR BLADE HONEYCOMB CONTAMINATED WITH WATER.						1	G	7	2 	4U			 	H1NE    					 
2002051000096	20020510	00096	SW  	2002	5	10	AUS20020360      	1	20020320	G	2434	302391	DIODE           			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR 2 DC GEN	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 										(AUS) NR 2 GENERATOR OFF LINE, THE EMERGENCY BUS INTERCONNECT CIRCUIT BREAKER POPPED,  PILOT LOST POWER TO THE NR 2 BUS.	 INVESTIGATION FOUND 2 DIODES ON THE EMERGENCY BUS FAILED RESISTANCE CHECK.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002051000097	20020510	00097	EA  	2002	5	10	AUS20020361      	2	20020320	G	7310	10544E	SLEEVE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL LINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			920  							(AUS) THE FIRE SLEEVE OF FUEL HOSE (PN 10544E) WAS FOUND CHAFFED APPROX 0.005 IN (0.127MM) IN DEPTH THROUGH WALL OF FUEL	 HEATER.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002051000098	20020510	00098	NM  	2002	5	10	AUS20020362      	1	20020413	G	7830	LJ76662	SEGMENT         			BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					THRUST REVERSER	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING INSPECTION, THE LT ENGINE INBOARD THRUST REVERSER NR 1 CASCADE (PN LJ76662) AND THE SUPPORT RING SECTION (P	N LJ7599) WERE FOUND MISSING.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2002050700096	20020507	00096	NM  	2002	5	7	AUS20020363      	1	20020412	G	3230	AS4624J030055	HOSE            	            	            	BOEING	767   	76733A      	1385209	NM  	      		            			 		            		LANDING GEAR RET	RUPTURED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) RH MLG WOULD NOT RETRACT DURING CLIMB. GROUND INVESTIGATION FOUND THE HYDRAULIC HOSE CONNECTED TO THE 'UP' ACTUATO	R HAD RUPTURED.					2	L	7	2 	4F			RT	A1NM    					 
2002050700097	20020507	00097	EA  	2002	5	7	AUS20020364      	2	20020418	G	8530	15F22200	PUSHROD         	LYC         	O235L2C     	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	 		            		RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1091 		L1909915					(AUS) DURING PERIODIC ENGINE INSPECTION, THREE PUSHRODS WERE FOUNDCRACKED AT THE BALLENDS. TWO HAD CRACKS 0.470IN (12MM)	 LONG AND THE THIRD HAD A CRACK JUST STARTING.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002051000099	20020510	00099	EU  	2002	5	10	AUS20020365      	1	20020418	G	3230	SA7670006128	HOSE            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	RUPTURED        	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) AIRCRAFT SUFFERED GREEN SYSTEM HYDRAULIC FLUID LOSS DURING TAXI.INSPECTION FOUND THAT THE FLEXIBLE EXTEND HOSE TO 	THE NOSELANDING GEAR ACTUATOR HAD RUPTURED.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2002051000100	20020510	00100	NM  	2002	5	10	AUS20020366      	1	20020404	G	3830	NAS192201253	CLAMP           			BOEING	737   	737800*     	       	NM  										WASTE DISPOSAL	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD GALLEY SINK DRAIN HOSE FOUND NOT CONNECTED TO FLOOR HOSE DUE TO A MISSING CLAMP, CAUSING LEAKAGE THROUGHOU	T GALLEY AREA. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F			RT	A16WE   					 
2002050700098	20020507	00098	SO  	2002	5	7	AUS20020367      	1	20020417	G	3260	922AA2YA6PZ722	PROXIMITY SENSOR	            	            	EMB   	120   	EMB120      	3260201	SO  	      		            			 		            		LANDING GEAR POS	FAULTY          	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			AU	S 	 									(AUS) ON APPROACH TO LAND, LANDING GEAR WAS SELECTED DOWN AND THE LH MAIN LANDING GEAR SYSTEM 'A' RED LIGHT REMAINED ILL	UMINATED. GROUND INVESTIGATION FOUND THE LH MAIN LANDING GEAR SYSTEM 'A'PROXIMITY SENSOR OPERATING INTERMITTENTLY.					2	L	7	2 	4T			RT	A31SO   					 
2002051000101	20020510	00101	NM  	2002	5	10	AUS20020368      	1	20020420	G	7120		FAIRING         			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE MOUNT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING A TRANSIT INSPECTION OF NR 3 ENGINE, THE FAIRING AROUNDTHE 'A' FRAME STRUT (10 O'CLOCK POSITION) WAS FOUND 	MISSING.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2002051000102	20020510	00102	NM  	2002	5	10	AUS20020369      	1	20020420	G	2910	AS11708K0165	LINE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					HYDRAULIC SYSTEM	RUPTURED        	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) DURING TAXI FOR TAKE-OFF, THE RT HYDRAULIC QUANTITY DECREASED TO ZERO WITH ASSOCIATED SYSTEM AND PRESSURE LIGHTS I	LLUMINATING. INVESTIGATION FOUND THAT THE PRESSURE LINE FROM THE AC PUMP HAD BURST.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002050700099	20020507	00099	NM  	2002	5	7	AUS20020370      	1	20020411	G	2620		LANYARD         	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	 		            		EXTINGUISHING SY	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) DURING SCHEDULED MAINTENANCE IT WAS DISCOVERED THAT A LANYARD INSTALLED BY SB8-26-9 WAS MISSING. IT WAS ALSO FOUND	 THAT THE P2AND P4 LANYARDS HAD BEEN FITTED TO THE INCORRECT SQUIBS.PERSONNEL/MAINTENANCE ERROR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2002051000103	20020510	00103	NM  	2002	5	10	AUS20020371      	1	20020420	G	2781	189929	SENSOR          			BOEING	737   	737400      	138449A	NM  										LE SLAT	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) AFTER TAKE-OFF, THE LEADING EDGE TRANSIT LIGHT REMAINED ILLUMINATED. INVESTIGATION FOUND THAT THE NR 2 LEADING EDG	E FLAP EXTEND SENSOR HAD FAILED.					2	L	7	2 	4F			RT	A16WE   					 
2002051000104	20020510	00104	NM  	2002	5	10	AUS20020372      	1	20020418	G	2752	65B156398	CAM             			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					TE FLAPS	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING A TRANSIT INSPECTION, A FLAP ROD WAS FOUND PROTRUDING FROM THE NR 7 FLAP TRACK FAIRING.INVESTIGATION FOUND 	THE AFT FLAP SEQUENCING ROD BROKEN AND THE 'GENEVA' CAM MECHANISM SHEARED.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2002051000105	20020510	00105	EU  	2002	5	10	AUS20020373      	1	20020423	G	3246	5010488	WHEEL           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					MLG	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING A TURN-A-ROUND INSPECTION, THE PILOT DISCOVERED A 7.8IN(20CM) BEAD SECTION MISSING FROM THE NR 3 MAIN WHEEL	 AND THE TIRE WAS DEFLATED.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
2002051000106	20020510	00106	NM  	2002	5	10	AUS20020374      	1	20020422	G	3240	AS11506K0280	LINE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					MLG BRAKES	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) AT AIRCRAFT ARRIVAL, HYDRAULIC FLUID WAS NOTED FLOWING FROM THE TOP OF THE RH MAIN LANDING GEAR.LEAK WAS TRACED TO	 A FLEXIBLE BRAKE LINE ABOVE THE OLEO.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002051000107	20020510	00107	NM  	2002	5	10	AUS20020375      	1	20020423	G	2150	78279016	ACM             			DHAV  	DHC8  	DHC8202     	2809007	NM  										CABIN COOLING	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 			2250 							(AUS) UNABLE TO REDUCE AIR CONDITIONING DUCT TEMPERATURE BELOW 18 DEGREES MANUAL AND AUTO CABIN TEMPERATURE WAS EXCESSIV	E. INVESTIGATION FOUND THAT THE AIR CYCLE MACHINE HAD A SMALL AIRLEAK EMINATING FROM THE TURBINE SEAL FACE.					2	H	7	2 	4T			RT	A13NM   					 
2002051300002	20020513	00002	NM  	2002	5	13	AUS20020376      	1	20020425	G	3233	8300101	ACTUATOR        			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  					MLG	CONTAMINATED    	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) WHEN LANDING GEAR WAS SELECTED DOWN, THE NLG FAILED TO EXTEND WITH BOTH THE GEAR DOOR AND UNSAFE LIGHTS ILLUMINATE	D. AFTER APPROXIMATELY ONE MINUTE THE NLG EXTENDED AND LOCKED DOWN WITH NO INPUT FROM CREW.  INVESTIGATION FOUND THAT TH	E NLG ACTUATOR CONTAINED A CONTAMINANT WITHIN THE UNIT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2002050700100	20020507	00100	SO  	2002	5	7	AUS20020378      	2	20020419	G	8530	643767P005	VALVE GUIDE     	CONT        	IO520L      	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	 		            		RECIPROCATING EN	LOOSE           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		517  							(AUS) NO.2 CYLINDER REVEALED A LEAKING EXHAUST VALVE DURING A COMPRESSION TEST AND ON DISASSEMBLY THE EXHAUST AND INLET 	GUIDESFELL OUT OF THE HEAD.  FURTHER INVESTIGATION OF THE REMAINING CYLINDERS FOUND THAT THE NO.4 CYLINDER INLET GUIDE W	AS ALSO LOOSE IN HEAD. PERSONNEL/MAINTENANCE ERROR.				1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2002051300003	20020513	00003	SO  	2002	5	13	AUS20020379      	1	20020205	G	2913		BRUSHES         			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HYD PUMP MOTOR	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 										(AUS) MLG HYDRAULIC PUMP MOTOR FAILED TO OPERATE DUE TO WORN BRUSHES.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920	 
2002051300004	20020513	00004	NE  	2002	5	13	AUS20020380      	2	20020425	G	7200	RB211	ENGINE          			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NR 4	FAILED          	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			7010 							(AUS) ON ROTATION A LOUD BANG WAS HEARD AND NR 4 EPR INDICATION DROPPED AND SPARKS WERE REPORTED FROM THE NR 4 ENGINE. T	HE ENGINE WAS SHUT DOWN.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2002051300005	20020513	00005	SW  	2002	5	13	AUS20020382      	1	20020228	G	2710	7300051	CONTROL ROD     			MOONEY	M20   	M20C        	5870208	SW  	CONT  	IO360 	IO360*      	17025	CE  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT AILERON CONTROL LINKS CRACKED.  FOUND IAW AD/M20/52 & MOONEY SB M20-264.						1	L	7	1 	3O	3	O	 	2A3     	E1CE				 
2002050700101	20020507	00101	NE  	2002	5	7	AUS20020383      	2	20020415	G	7532	2856201	BLEED VALVE     	SEMCA       	2856201     	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		COMPRESSOR BLEED	MALFUNCTIONED   	W			    	K	 	 	 	NONE                    				R	 	 	PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			AU	S 	 		27   		178					(AUS) PILOT REPORTED CHANGES IN ENGINE PERFORMANCE WITH DECREASE IN ENGINE TORQUE AND INCREASE IN COMPRESSOR RPM.  SUSPE	CT A RECENTLY FITTED COMPRESSOR BLEED VALVE WAS INCORRECTLY SET-UP AT OVERHAULFOR MODULATION POINT OPERATION.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002051300006	20020513	00006		2002	5	13	AUS20020384      	4	20020419	G	3424	4714E	INDICATOR       			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					TURN AND BANK	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			636  							(AUS) TURN COORDINATOR INDICATION ON RT TURN ONLY.  INVESTIGATION FOUND INTERNALLY THAT THE INDICATOR FORK HAD DISLODGED	 FROM THE ROTOR BUMP POST.					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2002050700102	20020507	00102	CE  	2002	5	7	AUS20020385      	1	20020422	G	3230	24411001	PIVOT           	            	            	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	 		            		LANDING GEAR RET	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) BOTH LH AND RH MLG PIVOT ASSEMBLIES SUSPECTED CRACKED. DYECHECKING PIVOTS LATER DID NOT SHOW CLEARLY ANY DEFECTS. 	INSPECTION CARRIED OUT IAW AD/CESSNA 170/69.					1	H	7	1 	3O	3	O	 	3A17    	E286				 
2002061300034	20020613	00034	CE  	2002	6	13	AUS20020386      	1	20020422	G	3233	12810013	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MLG ACTUATOR CRACKED. FOUND DURING INSPECTION IAW SEB01-2.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2002061300036	20020613	00036	NM  	2002	6	13	AUS20020390      	1	20020321	G	5720	6512601185	BRACKET         			BOEING	727   	727281      	138408N	NM  	PWA   	JT8   	JT8D17      	52049	NE  					LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			40425							(AUS) LT WING BRACKET ATTACHED TO LOWER CHORD DELAMINATED FROM CORROSION ZONE 72, STN WS204.0. CPCP - LEVEL 2 CORROSION.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002061300038	20020613	00038	NM  	2002	6	13	AUS20020392      	1	20020322	G	5511		SPAR            			BOEING	727   	727281      	138408N	NM  	PWA   	JT8   	JT8D17      	52049	NE  					HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			40425							(AUS) HORIZONTAL STABILISER CENTRAL UPPER REAR SPAR AREA CORRODED ZONE97 STN BS1586.81. CPCP - LEVEL 2 CORROSION.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002061300042	20020613	00042	NM  	2002	6	13	AUS20020398      	1	20020315	G	5347	CZ4952	SEAT TRACK      			BOEING	727   	727281      	138408N	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			40425							(AUS) SEAT TRACK CORRODED AT ZONE 24 STA 1130 TO STA 1110 LBL 2475 LT.CPCP - LEVEL 2 CORROSION.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002061300089	20020613	00089	EA  	2002	6	13	AUS20020404      	2	20020430	G	7314	RG17980	PUMP            			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE FUEL	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AFTER ENGINE CHANGE AND DURING GROUND RUNS THE ENGINE FAILED WHEN THE BOOST PUMP WAS TURNED OFF.  SUBSEQUENT INVES	TIGATION FOUND THAT THE INCORRECT FUEL PUMP PN RG17980 WAS FITTED AT OVERHAUL IN LIEU OF PUMP PN RG17980D. BECAUSE THE I	NLET PORT IS ON THE OPPOSITE SIDE OF THE PUMP THE USE OF THIS PUMP CAUSES THE AIRFRAME SUPPLY TO BE CONNECTED TO THE PUM	P OUTLET AND VICE VERSA. THE SPLINE LENGTH OF THE INCORRECT PUMP IS SHORTER THAN THAT OF THE CORRECT ITEM AND ONLY ENGAG	ES BY APPROXIMATELY 6.3MM(0.25IN).		1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002112700064	20021127	00064	CE  	2002	11	27	AUS20020407      	1	20020502	G	3222	1158200683	FORK            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NOSE/TAIL LANDIN	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NLG ASSEMBLY TUBE UNCHROMED PORTION EXCEEDED 1.27MM (0.050IN) AND LENGTH OF THE TUBE EXCEEDED 91MMM (23.10IN).  FO	UND DURING INSPECTION IAW AD/BEECH200/45 AND SB2102 REV5.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2002061300127	20020613	00127	SO  	2002	6	13	AUS20020410      	2	20020405	G	7322	1048931	CARBURETOR      			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING GROUND RUNS FOLLOWING ENGINE CHANGE THE ENGINE WAS FOUND TO BE RUNNING ROUGH, TOO LEAN AND MIXTURE ADJUSTME	NT WOULD NOT CORRECT THE FAULT. CARBURETOR WAS DISMANTLED AND THE FOLLOWING DEFECTS DISCOVERED:-  1. MAIN JET INCORRECT 	PN.  2. AIR METERING JET INCORRECT PN (USED)   3. AIR METERING PIN SPRING UNSERVICEABLE.  4. AIR METERING/ACCELERATION P	UMP LINKAGE WORN AND NOT SECURED CORRECTLY TO THROTTLE SHAFT5. FLOAT BRACKET WORN (USED)6. FLOAT NEEDLE WORN (USED)  7. 	STEEL SPLIT PINS USED IN LINKAGE CARBURETTOR WAS NEWLY OVERHAULED BY CONSOLIDATED FUEL SYSTEMS ON  FAA FORM 8130-3.		1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002061300045	20020613	00045	WP  	2002	6	13	AUS20020411      	2	20020429	G	7261	4235530121	INSERT          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ENGINE	DISLODGED       	W				O				OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			6178 							(AUS) LT ENGINE OIL BYPASS VALVE ATTACHMENT STUD INSERT PN 423-553-0121 (COMPLETE WITH BOLT) CAME LOOSE IN THE GEARBOX C	ASING ALLOWING THE OIL FILTER BYPASS VALVE BODY TO SEPARATE FROM THE CASING.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2002061400001	20020614	00001	NM  	2002	6	14	AUS20020412      	1	20020216	G	2823	D406	SELECTOR SWITCH 			BAC   	MK3A  	MK3A        	05623P4	NM  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	AMTR	C8289	C8289       	GL  	FUEL SYSTEM	LOOSE           	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 										(AUS) DURING THE FIRST FLIGHT FOLLOWING AIRCRAFT RESTORATION THE ENGINE DEVELOPED POWER SURGES. INVESTIGATION FOUND THAT	 THE FUEL SELECTOR LEVER WAS LOOSE AND NOT ALIGNED WITH THE TANK SELECTION.					1	L	7	1 	3T	3	I	RT	EXPA1L71	A8EU	5	N	EXPP5N	 
2002061400003	20020614	00003	EA  	2002	6	14	AUS20020416      	2	20020412	G	8530	L16068A	PISTON          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NR 3 CYLINDER	DAMAGED         	W				A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE VIBRATION. CRANKCASE PRESSURISED AND OIL VENTED OVERBOARD. ENGINE SEIZED ON SHUTDOWN. INVESTIGATION FOUN	D A HOLE BURNED IN THE NR 3 CYLINDER PISTON.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002061400004	20020614	00004		2002	6	14	AUS20020417      	4	20020328	G	6113	05501623	PLATE           			CESSNA	170   	170         	2072302	CE  	CONT  	C145  	C1452       	17012	SO  	AMTR	C8289	C8289       	GL  	PROP SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER SPINNER BACKPLATE CRACKED. CRACK TRAVELED AROUND PROPELLER FLANGE AREA AND RADIATED OUT TO THE FLANGE.						1	H	7	1 	3O	3	O	NT	A799    	E253	5	N	EXPP5N	 
2002061400005	20020614	00005	WP  	2002	6	14	AUS20020418      	1	20020422	G	3213	AN626A	BOLT            			NEWZE 	FU24  	FU24A954    	6280104	WP  	LYC   	O720  	IO720A1B    	41546	EA  					MLG	BROKEN          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) MAIN LANDING GEAR TORQUE LINK BOLT FAILED. LOWER HALF OF OLEO STRUT, TORQUE LINKS, AXLE AND WHEEL ASSEMBLY POPPED 	OUT AFTER TAKEOFF.					1	L	7	1 	3O	3	O	 	A9PC    	1E15				 
2002061400006	20020614	00006	EA  	2002	6	14	AUS20020422      	2	20020424	G	7414		BEARING         	SLICK       	6330        	GIPPLD	GA200 	GA200       	       	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	MAGNETO	MISOVERHAULED   	W				A				UNSCHED LANDING         				W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		CR	CRUISE         	1			AU	S 										(AUS) RT MAGNETO BEARING INCORRECTLY ASSEMBLED. ROTOR HARD TO ROTATE. COIL FAULTY.						1	L	7	1 	3O	3	O	NC	A00001LA	1E4	5	C	P920	 
2002061300051	20020613	00051	SO  	2002	6	13	AUS20020424      	1	20020502	G	3230	67031002	FITTING         			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR RETRACTION FITTING BROKEN. DOWNLOCKS JAMMED IN THE UP POSITION.						1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2002061400012	20020614	00012		2002	6	14	AUS20020432      	4	20020501	G	2562	012096	BATTERY         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ELT BATTERIES INCORRECTLY FITTED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002061400013	20020614	00013	GL  	2002	6	14	AUS20020434      	3	20020417	G	6114	D5858C402	HUB             			CESSNA	188   	188B        	2073007	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C402   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CORRODED IN AREA OF BLADE SOCKETS AND ON SHIM FACES.						1	L	7	1 	3O	3	O	 	A9CE    	E5CE	5	C	P47GL	 
2002061400023	20020614	00023	SO  	2002	6	14	AUS20020447      	1	20020503	G	5751	3539200LH	RIB             			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT AILERON RIBS PN 35392-00 (LT) AND PN 35392-01 (RT) CRACKED ALONG RADIUS OF FRONT FLANGE.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002061400026	20020614	00026	GL  	2002	6	14	AUS20020450      	1	20020408	G	5712		RIB             			AMTR  	VANS  	RV8         	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					WING ROOT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING ROOT RIB FAULTY DUE TO MOISTURE INGRESS. FOUND DURING INSPECTION IAW AD/CA25/7-1.						1	L	7	1 	3O	3	I	NT	EXPA1L71	EXPE3I				 
2002061400027	20020614	00027	GL  	2002	6	14	AUS20020451      	1	20020502	G	5712		RIB             			AMTR  	VANS  	RV8         	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					WING ROOT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING RIB LOCATED THIRD OUTBOARD FROM THE WING ROOT CONTAMINATED WITH MOISTURE. FOUND DURING INSPECTION IAW AD/CA25	/7-1.					1	L	7	1 	3O	3	I	NT	EXPA1L71	EXPE3I				 
2002061400028	20020614	00028	CE  	2002	6	14	AUS20020452      	1	20020510	G	2711		CONTROL CABLE   			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	AILERON TAB	MISRIGGED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) AILERON TRIM SYSTEM RIGGED IN REVERSE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002061400030	20020614	00030	CE  	2002	6	14	AUS20020454      	1	20020403	G	5610	07135381	WINDSHIELD      			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	COCKPIT	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) REPLACEMENT FRONT WINDSCREEN WAS THE WRONG SIZE. THE HEIGHT OF THE SCREEN WAS TOO SHORT AND THE RT SIDE WAS NOT LO	NG ENOUGH. A SECOND REPLACEMENT WINDSCREEN HAD SIMILAR PROBLEMS. BOTH SCREENSWERE GENUINE MANUFACTURER SUPPLIED PARTS. M	ANUFACTURING ERROR.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002061300058	20020613	00058	CE  	2002	6	13	AUS20020455      	1	20020517	G	5720	08113508	FITTING         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	STUB WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			14201							(AUS) LT AND RT LOWER STUB WING FITTINGS CRACKED. FOUND DURING NDTINSPECTION.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002112500027	20021125	00027	NE  	2002	11	25	AUS20020459      	1	20020509	G	2435		STARTER GEN     			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 2	MALFUNCTIONED   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	04										(AUS) DC GENERATING SYSTEM FAULTY.  INVESTIGATION COULD FIND NO CAUSE FOR THE PROBLEM BUT THE FOLLOWING ITEMS WERE REPLA	CED; NR 2 ENGINE STARTER-GENERATOR  NR 2 GENERATOR CONTROL UNIT NR 2 TRIPLE TACHO INDICATOR NR 2 ENGINE T5 GAUGE.  SUSPE	CT CAUSED BY A VOLTAGE SPIKE.				1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2002061300065	20020613	00065	CE  	2002	6	13	AUS20020473      	1	20020506	G	5514	00244002373	FITTING         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	HORIZONTAL STAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT HORIZONTAL STABILISER ATTACHMENT HOLES WORN. HOLES IN STUB SPAR ALSO WORN.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2002061400041	20020614	00041	EA  	2002	6	14	AUS20020474      	2	20020211	G	7200	PCE22284	ENGINE          			PIPER 	PA36  	PA36285     	7103610	SO  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NACELLE	MAKING METAL    	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) ENGINE SURGING. INVESTIGATION FOUND METAL CONTAMINATION OF THE ENGINE.						1	L	7	1 	3O	3	T	 	A10SO   	E4EA	6	C	P15EA	 
2002061300066	20020613	00066	EA  	2002	6	13	AUS20020475      	2	20020519	G	7421	L1316339A	SPARK PLUG      	LYC         	O320D2A     	AVIONS	R2160 	R2160       	0960101	EU  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	NR 4 CYLINDER	FOULED          	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			2032 		L1316339A					(AUS) NR 4 CYLINDER SPARK PLUGS FOULED.						1	L	7	1 	3O	3	O	RT	A48EU   	E274	5	N	P88614	 
2002061300070	20020613	00070	CE  	2002	6	13	AUS20020481      	1	20020510	G	7170		FITTING         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE DRAIN	LOOSE           	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LT AFT INDUCTION DRAIN FITTING LOOSE ALLOWING FUEL TO RUN DOWN THE OUTSIDE OF THE DRAIN LINE AND DRIP ONTO THE EXH	AUST.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002061400050	20020614	00050	EA  	2002	6	14	AUS20020483      	2	20020411	G	8500		ENGINE          			PIPER 	PA25  	PA25150     	7102503	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	NACELLE	MALFUNCTIONED   	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE REMOVED FOR INVESTIGATION INTO LOW OIL PRESSURE AND HIGH OIL TEMPERATURE.						1	H	7	1 	3O	3	O	 	EXPA1H71	E274	5	N	P88614	 
2002070800092	20020708	00092	CE  	2002	7	8	AUS20020506      	1	20020530	G	5711	HDHEO00636	STRAP           	CESSNA      	421C        	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	WING SPAR	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AIRCRAFT HAS HDH SPAR STRAP MODIFICATION FITTED. INVESTIGATIONFOUND NO EVIDENCE OF ONGOING NDT INSPECTION IAW HDH 	EDD/6 ISSUE 2 BEING CARRIED OUT. NDT TECHNIQUE IS NOT POSSIBLE IN THIS MODELAIRCRAFT.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2002070800093	20020708	00093	CE  	2002	7	8	AUS20020507      	1	20020530	G	5314	12136643	KEEL            	            	            	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUSELAGE MAIN, K	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FORWARD FUSELAGE RH KEEL MEMBER CRACKED IN UPPER FLANGE.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002070800094	20020708	00094	SO  	2002	7	8	AUS20020508      	1	20020527	G	3241	426871	CONTROL BOX     	            	            	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	BRAKE ANTISKID S	FAULTY          	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 				290					(AUS) ANTISKID CONTROL BOX FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2002070800095	20020708	00095	NE  	2002	7	8	AUS20020510      	2	20020524	G	7320	9580115900	SENSOR          	TMECA       	ARRIEL1S1   	SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  	 		            		FUEL CONTROLLING	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 				15069					(AUS) NO2 ENGINE OVERSPEED SENSOR FAULTY.						1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2002070800096	20020708	00096	NM  	2002	7	8	AUS20020516      	1	20020527	G	5210		DOOR            	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		PASSENGER/CREW D	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) AIRCRAFT UNABLE TO MAINTAIN PRESSURISATION. LOUD AIR NOISE COMING FROM DOOR L1.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800097	20020708	00097	GL  	2002	7	8	AUS20020520      	2	20020522	G	7261		OIL SYSTEM      	GE          	CF680C2     	BOEING	767   	76733A      	1385209	NM  	GE    	CF6   	CF680C2*    	 	GL  	 		            		TURBINE ENGINE O	CONTAMINATED    	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 									(AUS) RH ENGINE D SUMP OIL SCAVENGE LINES AND D SUMP OIL FILTER COKED WITH CARBON BUILDUP CAUSING SUMP TO FILL WITH OIL 	AND VENTOVERBOARD. OIL TYPE HAD BEEN CHANGED FROM 2830 TO MJ2 SIX MONTHSPREVIOUSLY.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002070800098	20020708	00098	NM  	2002	7	8	AUS20020524      	1	20020510	G	2913	312A101029	PIPE            	            	            	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		HYDRAULIC PUMP,	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE HYDRAULIC PUMP CASE DRAIN PIPES LOCATED IN LH AND RH PYLONS CHAFED BEYOND LIMITS IN AREAS LOCATED ADJACENT 	TO PYLONSKIN CUTOUT PANELS 5726L AND 5826R.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800099	20020708	00099	CE  	2002	7	8	AUS20020525      	1	20020529	G	5312	2112136	BULKHEAD        	CESSNA      	210N        	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUSELAGE MAIN, B	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				21063317					(AUS) REAR FUSELAGE BULKHEAD CRACKEDIN AREA OF TOP LH HORIZONTALATTACHMENT BOLT LOCATION.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P36EA	 
2002070800100	20020708	00100	CE  	2002	7	8	AUS20020526      	1	20020529	G	5320	12324001LH	BRACKET         	CESSNA      	210N        	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUSELAGE, MISCEL	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				21063317					(AUS) BRACKETS PNO 1232400-1 (LH) AND PNO 1232400-2 (RH) CORRODED.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P36EA	 
2002070800101	20020708	00101		2002	7	8	AUS20020528      	4	20020603	G	2565	D31354433	SLIDE           	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		ESCAPE SLIDE	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		3185 		1649					(AUS) DOOR 2R ESCAPE SLIDE FAILED TO INFLATE DURING FUNCTIONAL TEST.SLIDE INFLATED USING THE MANUAL INFLATION SYSTEM. SL	IDE LIGHTINGALSO INOPERATIVE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800102	20020708	00102	EU  	2002	7	8	AUS20020533      	1	20020112	G	3260		WARNING SYSTEM  	            	            	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  	 		            		LANDING GEAR POS	FAULTY          	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		AP	APPROACH       	1			AU	S 	 									(AUS) NLG DOOR INTRANSIT LIGHT ILLUMINATED. INVESTIGATION COULD FIND NO CAUSE FOR THE DEFECT.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2002070800103	20020708	00103	EU  	2002	7	8	AUS20020538      	1	20020203	G	3230		DIODE           	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) LANDING GEAR RETRACTION SYSTEM DIODE FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002070800104	20020708	00104	EU  	2002	7	8	AUS20020539      	1	20020205	G	2410		FITTING         	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		ALTERNATOR-GENER	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO1 ENGINE CONSTANT SPEED DRIVE (CSD) OIL PRESSURE FITTINGLEAKING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002070800105	20020708	00105	EU  	2002	7	8	AUS20020540      	1	20020204	G	2930		SWITCH          	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		HYDRAULIC INDICA	FAULTY          	W			    	K	 	 	 	NONE                    				K	M	J	FLUID LOSS                	OVER TEMP                 	WARNING INDICATION        	NR	NOT REPORTED   	1			AU	S 	 									(AUS) HYDRAULIC TEMPERATURE SWITCH FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002070800106	20020708	00106	EU  	2002	7	8	AUS20020541      	1	20020206	G	3230	200498005	ACTUATOR        	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 	 		3363 		CWDDDH292					(AUS) RH MAIN LANDING GEAR DOWNLOCK ACTUATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002070800107	20020708	00107	NM  	2002	7	8	AUS20020542      	1	20020602	G	5610	5893543129	WINDSHIELD      	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FLIGHT COMPARTME	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		22409		94116H5469					(AUS) CAPTAINS NO1 WINDOW CRACKED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800108	20020708	00108	GL  	2002	7	8	AUS20020543      	2	20020605	G	7261	1537L6850603	OIL SYSTEM      	GE          	CF680C2     	BOEING	767   	76733A      	1385209	NM  	GE    	CF6   	CF680C2*    	 	GL  	 		            		TURBINE ENGINE O	CONTAMINATED    	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 	 									(AUS) LH ENGINE NO6 BEARING SCAVENGE FILTER BLOCKED WITH CARBON PARTICLES AND D' SUMP SCAVENGE LINES COKED CAUSING OIL T	O BE VENTED OVERBOARD. ENGINE OIL TYPE HAD BEEN CHANGED FROM EXXON 2380 TO MOBIL JET II.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002070800109	20020708	00109		2002	7	8	AUS20020546      	4	20020516	G	6122	C290D4T4	CSU             	MCAULY      	C290D4T4    	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	PROPELLER GOVERN	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				792168					(AUS) PROPELLER GOVERNOR (CSU) LEAKING OIL.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002070800110	20020708	00110		2002	7	8	AUS20020547      	4	20020305	G	6122	C290D4T2	CSU             	MCAULY      	C290D4T2    	CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	PROPELLER GOVERN	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 		792  		794696					(AUS) PROPELLER GOVERNOR (CSU) FAULTY. SUSPECT CAUSED BY FAULTY SPEEDER SPRING.						1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2002070800111	20020708	00111		2002	7	8	AUS20020552      	4	20020512	G	2565	D31591478	SLIDE           	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		ESCAPE SLIDE	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		9369 		1706					(AUS) DOOR 1L ESCAPE SLIDE LANYARD ATTACHMENT FROM BATTERY FIRING PIN FAULTY. SLIDE LIGHTING FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800112	20020708	00112	NM  	2002	7	8	AUS20020556      	1	20020608	G	5610	57176244	WINDOW          	            	            	BOEING	737   	7373Q8      	1384670	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FLIGHT COMPARTME	CRACKED         	W			    	K	 	 	 	NONE                    				O	B	 	OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			AU	S 	 				97119H5359					(AUS) FIRST OFFICER'S SLIDING WINDOW CRACKED ACCOMPANIED BY ELECTRICALBURNING OF THE SEALS AND CONDUCTORS.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800113	20020708	00113	CE  	2002	7	8	AUS20020560      	1	20020531	G	7820	K70105	MUFFLER         	CONT        	IO520BA     	BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	ENGINE NOISE SUP	DISTORTED       	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 	 									(AUS) RH MUFFLER BUCKLED AND DISTORTED IN AREA UNDER THE HEATER SHROUD. ONE HEAT TRANSFER STUD MISSING. EXHAUST GAS ESCA	PING INTO CABIN HEATER SYSTEM.					1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2002070800114	20020708	00114	SO  	2002	7	8	AUS20020561      	1	20020521	G	2140	A23D0475	REGULATOR       	JANITROL    	FR65D793EL  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				A99110013					(AUS) COMBUSTION HEATER FUEL REGULATOR LEAKING. FOUND DURING INSPECTION IAW AD/AIRCON/9 PT2.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002070800115	20020708	00115		2002	7	8	AUS20020563      	4	20020529	G	3457	KA33	COOLING FAN     	            	            	GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK4     	GL  	GLOBAL POSITIONI	SEIZED          	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 	 									(AUS) GPS COOLING FAN SEIZED.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2002070800116	20020708	00116	SO  	2002	7	8	AUS20020564      	2	20020606	G	8530		PISTON          	CONT        	IO470F      	CESSNA	210   	2105A       	2073406	CE  	CONT  	O470  	IO470F      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO4 CYLINDER PISTON SKIRT BROKEN IN AREA BELOW THE BOTTOM PISTONRING. INVESTIGATION FOUND SIMILAR DAMAGE TO THE NO	2 PISTON.					1	H	7	1 	3O	3	O	 	3A21    	3E1	5	C	P3EA	 
2002070800117	20020708	00117	EU  	2002	7	8	AUS20020569      	1	20020418	G	2131	1026445	CONTROLLER      	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		CABIN PRESSURE C	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 		11564		30156					(AUS) CABIN PRESSURE CONTROLLER FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002070800118	20020708	00118	EA  	2002	7	8	AUS20020572      	2	20020410	G	7210	3037080	GEARBOX         	PWA         	PT6A34      	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  	 		            		TURBINE ENGINE R	SEIZED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 	 									(AUS) LH ENGINE REDUCTION GEARBOX SEIZED. METAL CONTAMINATION OF OILSYSTEM.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002070800119	20020708	00119	EU  	2002	7	8	AUS20020575      	1	20020216	G	3233		ACTUATOR        	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR ACT	FAULTY          	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR FAULTY. INVESTIGATION FOUND RH MAIN LANDINGGEAR ACTUATOR SLOW TO RETRACT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002070800120	20020708	00120		2002	7	8	AUS20020578      	4	20020502	G	6122	C290D4T4	CSU             	MCAULY      	D3A32C90    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	PROPELLER GOVERN	FAULTY          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 	 		246  							(AUS) CONSTANT SPEED UNIT (CSU) FAULTY.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002070800121	20020708	00121	CE  	2002	7	8	AUS20020579      	1	20020605	G	5712	11812004826	RIB             	            	            	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	WING, RIB/BULKHE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH WING CORRODED IN AREA OF LOWER AFT INBOARD CORNER. CORROSION AFFECTED LOWER WING SKIN, REAR SPAR AND THE UPPER 	SURFACE OF THEHORIZONTAL LEG OF THE CENTRE WING MAIN RIB.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002070800122	20020708	00122	EA  	2002	7	8	AUS20020580      	2	20020501	G	8520	L1845851A	CRANKCASE       	LYC         	IO360C1C6   	PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 				L1845851A					(AUS) CRANKCASE FAILED. LIMITED INFORMATION PROVIDED.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2002070800123	20020708	00123	EU  	2002	7	8	AUS20020586      	1	20020306	G	2720		CABLE           	            	            	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  	 		            		RUDDER CONTROL S	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RUDDER CABLE WORN.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2002070800124	20020708	00124	EU  	2002	7	8	AUS20020587      	1	20020306	G	2730	A2737114500000	CABLE           	            	            	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  	 		            		ELEVATOR CONTROL	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ELEVATOR CABLES PNO A2737114500000 AND PNO A2737114000000 WORN.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2002070800125	20020708	00125	EU  	2002	7	8	AUS20020588      	1	20020318	G	2741		SWITCH          	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		STABILIZER POSIT	FAULTY          	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 									(AUS) STABILISER CONTROL SWITCH FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002070800126	20020708	00126	NM  	2002	7	8	AUS20020592      	1	20020613	G	5620	75620003103	WINDOW          	DHAV        	85323917001 	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PASSENGER COMPAR	FRACTURED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 		17389		1348					(AUS) RH SIDE PASSENGER WINDOW OUTER PANE CRACKED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002070800127	20020708	00127	NM  	2002	7	8	AUS20020596      	1	20020612	G	2410		CSD             	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		ALTERNATOR-GENER	FAILED          	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 	 									(AUS) NO2 GENERATOR CONSTANT SPEED DRIVE FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800128	20020708	00128	NM  	2002	7	8	AUS20020604      	1	20020618	G	5230		FRAME           	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		CARGO/BAGGAGE DO	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FORWARD CARGO DOOR LOWER CORNER FRAMES CRACKED. FOUND DURINGINSPECTION IAW ADB737/142.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800129	20020708	00129	NM  	2002	7	8	AUS20020607      	1	20020521	G	5230		DOOR            	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		CARGO/BAGGAGE DO	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FORWARD CARGO DOOR LOWER CROSSBEAM T' CHORD CRACKED IN TWO PLACES. AFT END OF WEB CRACKED. FOUND DURING INSPECTION	 IAW AD/B737/142.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800130	20020708	00130	SO  	2002	7	8	AUS20020608      	1	20020607	G	3230	4204200	ARM             	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR RET	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR ARM BROKEN AND BENT.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002070800131	20020708	00131	WP  	2002	7	8	AUS20020610      	1	20020615	G	6420	269A60923	BOLT            	            	            	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  	 		            		TAIL ROTOR HEAD	BROKEN          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 	 									(AUS) TAIL ROTOR FORK BOLT BROKEN IN HALF.						1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2002070800132	20020708	00132	SO  	2002	7	8	AUS20020611      	1	20020618	G	5230		DOOR            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	CARGO BAY	SEPARATED       	W				K				NONE                    				D			INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 										(AUS) NOSE BAGGAGE DOOR SEPARATED FROM AIRCRAFT.  DOOR LOCK INSPECTED AND FOUND TO BE SERVICEABLE.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
2002070800133	20020708	00133	EA  	2002	7	8	AUS20020612      	2	20020618	G	8520	LW18840	CAMSHAFT        	LYC         	AEIO360B2F  	MUDRY 	10    	CAP10B      	0950102	EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	RECIPROCATING EN	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CAMSHAFT LOBES AND ASSOCIATED LIFTERS (3OFF) BADLY WORN.						1	L	7	1 	3O	3	O	 	A36EU   	1E10	5	N	P3EU	 
2002070800134	20020708	00134	NM  	2002	7	8	AUS20020618      	1	20020625	G	7722		GAUGE           	GE          	CFM563C     	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		ENGINE EGT/TIT I	FAULTY          	W			    	K	 	 	 	NONE                    				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 									(AUS) NO2 ENGINE EGT GAUGE FAULTY. FAULT LIGHT ON FIRE PANELILLUMINATED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002070800135	20020708	00135	EU  	2002	7	8	AUS20020619      	2	20020625	G	7261		OIL SYSTEM      	GE          	CFM563C     	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TURBINE ENGINE O	CONTAMINATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ENGINE OIL SYSTEM CONTAMINATED WITH FUEL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002080800069	20020808	00069	SO  	2002	8	8	AUS20020623      	1	20020620	G	5753		RIB             			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E1A     	41508	EA  	SNSNCH	74D	74DM        	EA  	TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP NOSE RIBS SEVERELY CORRODED.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002080800070	20020808	00070	NM  	2002	8	8	AUS20020624      	1	20020626	G	2761	251A12403	ACTUATOR        			BOEING	737   	737832      	13844CF	NM  	GE    	CFM56 	CFM567B24   	 	NE  					DRAG CONTROL	LEAKING         	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 			705  							(AUS) NR 9 FLIGHT SPOILER ACTUATOR LEAKING FROM ACTUATOR BODY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2002080700060	20020807	00060	NM  	2002	8	7	AUS20020625      	1	20020625	G	3242	NAS1802311	SCREW           	            	            	BOEING	767   	767         	UTILUSE	NM  	GE    	CF6   	CF680C2*    	 	GL  	 		            		BRAKE	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) BRAKE RETAINING BOLT LOCK BOLTS MISSING. AIRCRAFT IS FOREIGNREGISTERED DQ-FJC. PERSONNEL/MAINTENANCE ERROR.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002080700061	20020807	00061	NE  	2002	8	7	AUS20020627      	2	20020422	G	8530	114651	CYLINDER        	PWA         	R183092     	DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	RECIPROCATING EN	SEPARATED       	W			    	K	 	 	 	NONE                    				E	F	 	VIBRATION/BUFFET          	FLT CONT AFFECTED         		LD	LANDING        	1			AU	S 	 		645  		355640					(AUS) RH ENGINE NO13 CYLINDER HEAD SEPARATED. INVESTIGATION FOUND THATTHE FRACTURE OCCURRED APPROXIMATELY 25.4MM (1IN) B	ELOW THEHEAD/BARREL JOIN AND WAS TEMPERATURE RELATED.					2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2002080700062	20020807	00062	SW  	2002	8	7	AUS20020628      	1	20020421	G	6322		STUD            	BELL        	476618011   	BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435B1A   	41516	EA  	 		            		ROTORCRAFT COOLI	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 	 									(AUS) COOLING FAN MOUNT STUD LOCATED ON CRANKCASE FAILED. LOSS OF TENSION ALLOWED BELT TO FALL OFF AND DESTROY THE COOLI	NG FAN.					1	G	7	1 	3O	3	O	 	2H3     	1E13				 
2002080700063	20020807	00063	EU  	2002	8	7	AUS20020629      	1	20020621	G	5743		FITTING         	            	            	MUDRY 	10    	CAP10B      	0950102	EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	WING, LANDING GE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR LH FORWARD INBOARD LOWER AND RH FORWARD OUTBOARD LOWER ATTACHMENT BLOCKS CRACKED. FOUND DURING INSPEC	TION IAWAD/CAP/4A2.					1	L	7	1 	3O	3	O	 	A36EU   	1E10	5	N	P3EU	 
2002080700064	20020807	00064	SO  	2002	8	7	AUS20020631      	2	20020614	G	8550	632856	PUMP            	CONT        	IO520F      	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE OIL PUMP HOUSING CRACKED. CRACK APPEARS TO ORIGINATE FROMA CASTING MARK. FOUND WHEN OIL FILTER ADAPTER WAS 	REMOVED FOR RECTIFICATION OF AN OIL LEAK.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002080700065	20020807	00065	NE  	2002	8	7	AUS20020632      	2	20020627	G	7261	9505	PUMP            	TMECA       	ARRIEL1D1   	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  	 		            		TURBINE ENGINE O	FOD             	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		TX	TAXI/GRND HDL  	1			AU	S 	 				9505					(AUS) ENGINE OIL PUMP INLET FOD. INVESTIGATION FOUND A SMALL PIECE OF RUBBER TUBING LODGED IN THE OIL PUMP INLET, RESTRI	CTING OIL FLOWTO THE PUMP. ENGINE WAS BEING GROUND RUN FOR INSTALLATION FOLLOWING REPAIR. PERSONNEL/MAINTENANCE ERROR.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002080900002	20020809	00002	EU  	2002	8	9	AUS20020635      	1	20020613	G	2550	52801702	CARGO HOOK      			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					CARGO BAY	BROKEN          	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 										(AUS) CARGO HOOK KEEPER ASSEMBLY ARM (1OFF) BROKEN AND THE OTHER ARMBENT. THE LOAD BEAM WAS ALSO BENT. THE LOAD WAS UNIN	TENTIONALLY RELEASED.					1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2002080700066	20020807	00066		2002	8	7	AUS20020639      	4	20020628	G	6122		SPRING          	HARTZL      	F624ZL      	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER GOVERN	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 	 		170  							(AUS) GOVERNOR SPEEDER SPRING FAILED. SPRING WAS A NEW ITEM FITTEDDURING OVERHAUL 169.7 HOURS PREVIOUSLY.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002080700067	20020807	00067	CE  	2002	8	7	AUS20020642      	1	20020411	G	2720	5052432634	ARM             	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	RUDDER CONTROL S	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CAPTAINS RH RUDDER PEDAL ARM FAILED. INVESTIGATION FOUND THAT THE PIVOT BOLT HOLE WAS WORN AND ELONGATED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002080700068	20020807	00068	SW  	2002	8	7	AUS20020643      	1	20020628	G	3233	ED12758	CLEVIS          	            	            	GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK4     	GL  	LANDING GEAR ACT	FRACTURED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 	 		3244 							(AUS) MAIN LANDING GEAR HYDRAULIC RAM RODEND CLEVIS FRACTURED.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2002080700069	20020807	00069	CE  	2002	8	7	AUS20020644      	1	20020521	G	3230		GEARBOX         	            	            	CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) LANDING GEAR ACTUATOR REDUCTION GEARBOX GEAR TEETH WORN. ELECTRIC DRIVE MOTOR INTERMITTENT IN OPERATION AND CLUTCH	 INEFFECTIVE.					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2002080700070	20020807	00070	CE  	2002	8	7	AUS20020648      	1	20020704	G	2810		FUEL TANK       	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUEL STORAGE	COLLAPSED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH AUXILIARY FUEL CELL COLLAPSED. VELCRO ATTACHMENT PADS HADBECOME UNGLUED AND SEPARATED FROM THE TOP SURFACE OF T	HE FUEL CELL. INSPECTION FOUND THAT THE RH FUEL VENT HEATING ELEMENT HADFAILED, ALLOWING THE VENT TO BECOME BLOCKED WITH	 ICE CAUSING THEFUEL CELL TO COLLAPSE.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002080700071	20020807	00071		2002	8	7	AUS20020656      	4	20020706	G	2564	733M2537017	LIFE RAFT       	            	            	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		LIFERAFT	FOULED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		748  		11208487					(AUS) DURING LIFERAFT REMOVAL FOR FITMENT TO ANOTHER AIRCRAFT, THE HOOK ATTACHED TO THE END OF THE ACTIVATION LANYARD BE	CAME LODGED INTHE CEILING STRUCTURE AT THE REAR OF THE OVERHEAD STOWAGE AREA. AS THE LIFERAFT WAS REMOVED FROM THE STOWA	GE AREA, THELANYARD  UNWOUND.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002080700072	20020807	00072	SO  	2002	8	7	AUS20020658      	1	20020628	G	2823	480700	PIN             	            	            	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	FUEL SELECTOR/SH	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SELECTOR ROLL PINS BROKEN. RH FUEL SELECTOR HAD ONE ROLL PIN MISSING.						1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2002080900024	20020809	00024	NM  	2002	8	9	AUS20020664      	1	20020701	G	3260	980209001	DOWNLOCK SWITCH 			PIPER 	PA60  	PA60601B    	7106011	NM  	LYC   	O540  	IO540S1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	MLG	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH CONTACTS DIRTY.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2002080900028	20020809	00028	SO  	2002	8	9	AUS20020667      	1	20020503	G	3233		BRUSHES         			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MLG MOTOR	LOOSE           	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR MOTOR BRUSHES ADRIFT IN BRUSH HOLDER. MOTOR FAILED.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920	 
2002080700073	20020807	00073	EA  	2002	8	7	AUS20020669      	2	20020709	G	7414	10349276	CONDENSER       	BENDIX      	S6LSC200    	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  	 		            		MAGNETO/DISTRIBU	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				C119810E					(AUS) MAGNETO CONDENSER INTERNAL FAILURE.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002080700074	20020807	00074	CE  	2002	8	7	AUS20020670      	1	20020709	G	2701	AN2278B	STUD            	            	            	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	CONTROL COLUMN S	FRACTURED       	W			    	K	 	 	 	NONE                    				O	F	 	OTHER                     	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 	 									(AUS) AILERON CONTROL SYSTEM STUD FRACTURED. CLAMP PNO AN737TW56-66 LOOSE AT BOTTOM OF CONTROL COLUMN ALLOWING THE CONTR	OL COLUMN BOOT PNO 101-54149-37 TO MOVE UNSECURED AROUND THE CONTROLCOLUMN. LH AILERON CONTROL CABLE TURNBUCKLE LOCKWIRE	 CAUGHT ONBRACKET PNO 50-524466-7 WHEN THE CONTROL WHEEL WAS MOVED TO THE RIGHT.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2002080700075	20020807	00075	SW  	2002	8	7	AUS20020674      	1	20020701	G	5711		WEB             	            	            	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	WING SPAR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		20624							(AUS) WING SPAR INNER WEB CRACKED. FOUND DURING INSPECTION IAWAD/SWSA226/86.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2002080700076	20020807	00076	CE  	2002	8	7	AUS20020679      	1	20020710	G	3234	MS166245018	RETAINER        	            	            	CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  	 		            		LANDING GEAR SEL	SEPARATED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 	 									(AUS) LANDING GEAR SELECTOR CIRCLIP (RETAINER) DISLOCATED.						1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2002080700077	20020807	00077	GL  	2002	8	7	AUS20020681      	2	20020525	G	7240	23056130	LINER           	RROYCE      	A250C20R2   	HUGHES	369   	369E        	4470707	WP  	ALLSN 	25OC  	250C20R     	 	GL  	 		            		TURBINE ENGINE C	FAULTY          	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 	 				CAE295414					(AUS) ENGINE EXHIBITED LOW POWER FOLLOWING REPLACEMENT OF COMBUSTIONLINER. SUSPECT BOTTOM LOUVRES INCORRECTLY SET. THE L	INER FITTED WAS ZERO HOURS TIME SINCE OVERHAUL.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002080700078	20020807	00078	NM  	2002	8	7	AUS20020682      	1	20020708	G	2410	73511A	CSD             	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		ALTERNATOR-GENER	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		16787		B1966					(AUS) NO1 ENGINE CONSTANT SPEED DRIVE (CSD) FAILED. OIL LEAKING FROMDRAIN POINT.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002080700079	20020807	00079		2002	8	7	AUS20020684      	4	20020706	G	2564	733M2537011	LIFE RAFT       	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		LIFERAFT	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				11686790					(AUS) LIFE RAFT HAD ONE INFLATION BOTTLE INDICATING APPROXIMATELY 50PSI (LOWER END OF RED SCALE). LIFE RAFT HAD BEEN REC	EIVED FROMSTORES.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002080700080	20020807	00080	SO  	2002	8	7	AUS20020687      	1	20020711	G	2820	AN8336	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM 90 DEGREE ELBOW CORRODED. ELBOW IS LOCATED ON THE LHFIREWALL.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700081	20020807	00081	SO  	2002	8	7	AUS20020688      	1	20020711	G	2820	8623810	PIPE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700082	20020807	00082	SO  	2002	8	7	AUS20020689      	1	20020711	G	2820	8623803	PIPE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700083	20020807	00083	SO  	2002	8	7	AUS20020690      	1	20020711	G	2820	8623809	PIPE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700084	20020807	00084	SO  	2002	8	7	AUS20020691      	1	20020711	G	2820	8623804	PIPE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700085	20020807	00085	SO  	2002	8	7	AUS20020692      	1	20020711	G	2820	8623808	PIPE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700086	20020807	00086	SO  	2002	8	7	AUS20020693      	1	20020711	G	2820	AN8218	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM 90 DEGREE ELBOW CORRODED. ELBOW IS LOCATED IN LHWING.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700087	20020807	00087	SO  	2002	8	7	AUS20020694      	1	20020711	G	2820	AN8376	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM 45 DEGREE ELBOW CORRODED. ELBOW IS LOCATED IN LHWING.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700088	20020807	00088	SO  	2002	8	7	AUS20020695      	1	20020711	G	2820	AN83364	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM 90 DEGREE ELBOW CORRODED. ELBOW IS LOCATED IN LHWING.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080700089	20020807	00089	SO  	2002	8	7	AUS20020696      	1	20020711	G	2820	AN8336	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM 90 DEGREE ELBOW CORRODED. ELBOW IS LOCATED ON RHFIREWALL.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002080900043	20020809	00043	CE  	2002	8	9	AUS20020698      	1	20020605	G	5753		SKIN            			CESSNA	182   	182P        	2075816	CE  										TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SKINS CONTAINED EXTENSIVE SURFACE CORROSION.						1	H	7	1 	3O			NT	TA13    					 
2002080700090	20020807	00090	NE  	2002	8	7	AUS20020699      	2	20020711	G	7324	3019906	FLOW DIVIDER    	PWA         	PT6A42      	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUEL DIVIDER	FAULTY          	W			    	K	 	 	 	NONE                    				E	B	 	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			AU	S 	 				PCE93710					(AUS) ENGINE FUEL SYSTEM FLOW DIVIDER FAULTY. IGNITION LEAD ALSO FOUNDTO BE UNSERVICEABLE. ENGINE WAS UNDERGOING GROUND 	RUNS FOLLOWINGENGINE INSTALLATION. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002080700091	20020807	00091	CE  	2002	8	7	AUS20020702      	1	20020613	G	5312		RIVET           	BEECH       	1014100131  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUSELAGE MAIN, B	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AVIONICS SHELF SUPPORT ANGLE RIVET CORRODED AND RIVET HEADSHEARED. FOUND DURING INSPECTION OF FORWARD PRESSURE BUL	KHEAD LOCATED AT FS 84.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002080700092	20020807	00092	CE  	2002	8	7	AUS20020703      	1	20020531	G	5312		RIVET           	BEECH       	1014100131  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUSELAGE MAIN, B	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AVIONICS SHELF SUPPORT ANGLE RIVET CORRODED AND RIVET HEADSHEARED. FOUND DURING INSPECTION OF FORWARD PRESSURE BUL	KHEAD LOCATED AT FS 84.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2002080700093	20020807	00093	CE  	2002	8	7	AUS20020704      	1	20020619	G	5312		RIVET           	BEECH       	1014100131  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUSELAGE MAIN, B	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AVIONICS SHELF SUPPORT ANGLE RIVET CORRODED AND RIVET HEADSHEARED. RIVET WAS THE FOURTH RIVET FROM THE INBOARD END	. FOUND DURING INSPECTION OF FORWARD PRESSURE BULKHEAD LOCATED AT FS 84.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002080700094	20020807	00094	EU  	2002	8	7	AUS20020705      	1	20020708	G	5743		FITTING         	            	            	MUDRY 	10    	CAP10B      	0950102	EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	WING, LANDING GE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH MAIN LANDING GEAR ATTACHMENT BLOCKS CRACKED. RH FILLERDELAMINATED FROM SPAR ADJACENT TO UNDERCARRIAGE AT	TACHMENT. FOUND DURING INSPECTION IAW AD/CAP10/4A2.					1	L	7	1 	3O	3	O	 	A36EU   	1E10	5	N	P3EU	 
2002080700095	20020807	00095	SW  	2002	8	7	AUS20020706      	1	20020701	G	7312	10544E	HEATER          	PWA         	PT6T3BG     	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  	 		            		FUEL HEATER	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		39   		63314					(AUS) FUEL/OIL HEATER LEAKING OIL FROM WELD LINE ON MAIN BODY.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002080700096	20020807	00096	EU  	2002	8	7	AUS20020708      	1	20020717	G	8012	0174078030	DRAIN VALVE     	TMECA       	ARRIEL1B    	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		ENGINE START VAL	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 		105  		529					(AUS) ENGINE START DRAIN VALVE FAULTY.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002080700097	20020807	00097	CE  	2002	8	7	AUS20020710      	1	20020620	G	5341	817841232	BOLT            	            	            	BEECH 	200   	B200T       	1152929	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE, WING A	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) UPPER FORWARD WING ATTACHMENT BOLT SUSPECT CRACKED. FOUND DURINGFLUORESCENT INSPECTION IAW AD/B200/38 A4 AND BEECH	 S.I.R.M.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2002080700098	20020807	00098	EU  	2002	8	7	AUS20020711      	1	20020710	G	6720	704A34130103	CONTROL CABLE   			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					TAIL ROTOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT REAR TAIL ROTOR CONTROL CABLE CONTAINED BROKEN STRANDS IN AN AREA WHERE THE CABLE PASSES THROUGH FAIRLEAD.  FAI	RLEAD INSPECTED AND FOUND SERVICEABLE.					2	G	7	2 	4U	4	U		H4EU    	E12NE				 
2002080700099	20020807	00099	SO  	2002	8	7	AUS20020713      	1	20020618	G	2731		CABLE           	            	            	PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCE2Y	HCE2YK2     	GL  	ELEVATOR TAB CON	SEPARATED       	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 	 									(AUS) FORWARD LH STABILATOR TRIM CABLE DISCONNECTED FROM TRIM WHEEL.BALL END OF CABLE HAD COME OUT OF THE SOCKET ON THE 	SIDE OF THE WHEEL.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P9EA	 
2002080700100	20020807	00100	SO  	2002	8	7	AUS20020716      	2	20020618	G	8530	654833	PISTON          	CONT        	O470R       	CESSNA	182   	182L        	2072726	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	RECIPROCATING EN	DAMAGED         	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 	 		56   		81880					(AUS) PISTON DAMAGED DUE TO DETONATION. PISTON RINGS BROKEN AND OIL RETURN DRAIN HOLE ENLARGED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002080700101	20020807	00101	CE  	2002	8	7	AUS20020717      	1	20020320	G	7160	MS35206218	SCREW           	LYC         	O360A4K     	BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  	SNSNCH	76E	76EM8       	EA  	ENGINE AIR INTAK	MISSING         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 				L2093036A					(AUS) CARBURETTOR HEAT INOPERATIVE DUE TO MISSING SCREWS (3OFF) AND NUTS ALLOWING THE BUTTERFLY VALVE TO ROTATE FREELY O	N THE SHAFT PNO 169-910049-47.					1	L	7	1 	3O	3	O	 	A1CE    	E286	5	N	P4EA	 
2002080700102	20020807	00102	CE  	2002	8	7	AUS20020718      	1	20020607	G	3230	3581507711	BRACKET         	BEECH       	UPLOCK      	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	LANDING GEAR RET	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR UPLOCK ASSEMBLY BRACKET AND SPRING MISSING.THE BRACKET IS ATTACHED TO THE RIB LOCATED IN THE 	RH WHEEL BAY BY THREE RIVETS AND IT APPEARS THAT THE RIVETS FAILED PROBABLY DUE TO AGE HARDENING. LANDING GEAR COLLAPSED	 ON TOUCHDOWN.				1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2002080700103	20020807	00103	NM  	2002	8	7	AUS20020721      	1	20020715	G	3230	AE2464163E0192	HOSE            	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		LANDING GEAR RET	RUPTURED        	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR DOWNLOCK ACTUATOR HYDRAULIC HOSE RUPTURED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002080700104	20020807	00104	EA  	2002	8	7	AUS20020725      	2	20020716	G	7414	10357584	GEAR            	BENDIX      	S4LN20      	FUJI  	FA200 	FA200160    	3730101	WP  	LYC   	O320  	O320D2A     	41508	EA  	MCAULY	1C172	1C172MGM    	GL  	MAGNETO/DISTRIBU	STRIPPED        	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 		991  		9215					(AUS) RH MAGNETO DISTRIBUTOR GEAR HAD FIFTEEN TEETH STRIPPED.						1	L	7	1 	3O	3	O	 	A4PC    	E274	5	N	P910	 
2002080700105	20020807	00105	EA  	2002	8	7	AUS20020726      	2	20020708	G	8530	LW19001	EXHAUST VALVE   	LYC         	O320D2A     	FUJI  	FA200 	FA200160    	3730101	WP  	LYC   	O320  	O320D2A     	41508	EA  	MCAULY	1C172	1C172MGM    	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 		991  							(AUS) NO3 CYLINDER EXHAUST VALVE HEAD CRACKED AND BURNT.						1	L	7	1 	3O	3	O	 	A4PC    	E274	5	N	P910	 
2002080700106	20020807	00106	CE  	2002	8	7	AUS20020727      	1	20020722	G	5610	10138402522	WINDSHIELD      	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	FLIGHT COMPARTME	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 				98180H9754					(AUS) RH WINDSHIELD INNER PLY SHATTERED. WINDSHIELD HEAT WAS OFF' AT THE TIME.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2002080700107	20020807	00107	NM  	2002	8	7	AUS20020728      	1	20020704	G	3230	85420011061	DOOR            	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR RET	OUT OF ADJUST   	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR CENTRE DOOR ASSEMBLY OUT OF ADJUSTMENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002080700108	20020807	00108	NM  	2002	8	7	AUS20020730      	1	20020717	G	2920	849557	POWER UNIT      	            	            	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	HYDRAULIC SYSTEM	FAULTY          	W			    	K	 	 	 	NONE                    				K	J	M	FLUID LOSS                	WARNING INDICATION        	OVER TEMP                 	CR	CRUISE         	1			AU	S 	 		3194 		MX627765					(AUS) STANDBY HYDRAULIC POWER UNIT FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002080700109	20020807	00109	NM  	2002	8	7	AUS20020733      	1	20020719	G	2410	735511A	CSD             	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		ALTERNATOR-GENER	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				B1377					(AUS) NO1 ENGINE CONSTANT SPEED DRIVE (CSD) LEAKING OIL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002080700110	20020807	00110	SO  	2002	8	7	AUS20020735      	1	20020716	G	2910	2677A4EE	VALVE           	EMB         	EMB120      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	HYDRAULIC SYSTEM	FAILED          	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 				120135					(AUS) GREEN HYDRAULIC SYSTEM FILL CHECK VALVE CRACKED AND LEAKING.VALVE IS LOCATED IN THE AREA OF THE RH ENGINE NACELLE.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2002080700111	20020807	00111	NM  	2002	8	7	AUS20020738      	1	20020720	G	2820		LINE            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		AIRCRAFT FUEL DI	LEAKING         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH ENGINE FUEL FEED LINE LEAKING AT WING SPAR OUTLET CONNECTION.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002080900070	20020809	00070	CE  	2002	8	9	AUS20020742      	1	20020725	G	3230		LANDING GEAR    			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MAINS	MISRIGGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR INCORRECTLY RIGGED. LANDING GEAR COMPONENTS DAMAGED DUE TO THE EXTENT THAT THE LANDING GEAR WAS OUT O	F RIG. THE DEFECTS INCLUDE BENT RETRACT RODS, DENTED AND BENT UNDERCARRIAGE DRIVE TUBES, CORROSION AND RUST ON DRIVE TUB	ES, SEIZED AND RUSTED HARDWARE, PHYSICAL CONTACT DAMAGE TO UPPER DRAG LINKS FROM UPLOCK HOOK ASSEMBLY. PERSONNEL/MAINTEN	ANCE ERROR. POOR MAINTENANCE.			1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002080700112	20020807	00112	SO  	2002	8	7	AUS20020745      	1	20020725	G	7820	2634505	MUFFLER         	LYC         	IO540E1A5   	PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	IO540E1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE NOISE SUP	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		400  							(AUS) LH MUFFLER OUTLET PIPE CRACKED AT REAR SUPPORT CLAMP.						1	L	7	1 	3O	3	O	 	1A15    	1E4	5	C	P920	 
2002080700113	20020807	00113	EA  	2002	8	7	AUS20020746      	2	20020724	G	7230	3018389	SPACER          	PWA         	PT6A41      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE ENGINE C	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		3748 		PCE81011					(AUS) ENGINE FIRST STAGE COMPRESSOR SPACER DAMAGED DUE TO RUBBING ONTHE FIRST STAGE COMPRESSOR STATORS.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2002080700114	20020807	00114	NM  	2002	8	7	AUS20020747      	1	20020725	G	5347	1A0870129	SEAT TRACK      	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		SEAT/CARGO ATTAC	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) CAPTAINS SEAT FAILED TO LOCK IN SEAT TRACKS. SEAT SLID COMPLETELY BACK DURING TAKEOFF.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002080700115	20020807	00115	NE  	2002	8	7	AUS20020749      	2	20020717	G	7421	9550168760	IGNITER         	TMECA       	ARRIEL1B    	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		SPARK PLUG/IGNIT	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				945					(AUS) ENGINE IGNITER CENTRE ELECTRODE MISSING. IMPACT DAMAGE ON FIRST STAGE TURBINE AND FREE TURBINE BLADES.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002080700116	20020807	00116	CE  	2002	8	7	AUS20020751      	1	20020712	G	5342	04320049	BRACKET         	            	            	CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	2A34C	D2A34C98    	GL  	FUSELAGE, STABIL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) STEEL BRACKET ASSEMBLY CRACKED IN TWO PLACES. ONE CRACK LOCATED AT WELD SEAM AND ONE CRACK IN AREA OF ANCHOR NUT A	TTACHMENT.BRACKET ATTACHES VERTICAL FIN TO TAILPLANE AND TAILPLANE TO FUSELAGE.					1	H	7	1 	3O	3	O	 	3A19    	E223	5	C	P3EA	 
2002080900080	20020809	00080	SO  	2002	8	9	AUS20020752      	1	20020719	G	3230	751658	ARM             			PIPER 	PA23  	PA23250     	7102308	SO  						AMTR	C8289	C8289       	GL  	MLG	MISRIGGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EMERGENCY LANDING GEAR EXTENSION SYSTEM CO2 DISCHARGE UNIT LEVER ARM INCORRECTLY RIGGED. PERSONNEL/MAINTENANCE ERR	OR.					1	L	7	2 	3O			 	1A10    		5	N	EXPP5N	 
2002080700117	20020807	00117	EA  	2002	8	7	AUS20020754      	2	20020717	G	7414		MAGNETO         	LYC         	IO540K1B5   	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAGNETO/DISTRIBU	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO2 ENGINE NO2 MAGNETO FAULTY. MAGNETO MODELS 10-349370-4 AND 10-349310-8.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002080700118	20020807	00118	EA  	2002	8	7	AUS20020756      	2	20020620	G	7414	1052948	SHAFT           	CONT        	106006163   	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  	 		            		MAGNETO/DISTRIBU	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				D129606E					(AUS) RH MAGNETO ROTATING SHAFT BROKEN.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002080700119	20020807	00119	CE  	2002	8	7	AUS20020757      	1	20020710	G	7603	99104351	CABLE           	CONT        	TSIO520VB   	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	POWER LEVER	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE CONTROL CABLE INNER CABLE FAILED AT SWAGED ATTACHMENT TO THE COCKPIT END FITTING.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002080900102	20020809	00102	EU  	2002	8	9	AUS20020759      	1	20020717	G	2932	9738114306	PRESSURE SWITCH 			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYDRAULIC SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) HYDRAULIC PRESSURE SWITCH FAILED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002080700120	20020807	00120	CE  	2002	8	7	AUS20020763      	1	20020724	G	2820		CONNECTOR       	            	            	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	AIRCRAFT FUEL DI	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FLEXIBLE FUEL LINE CONNECTORS PERISHED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002080700121	20020807	00121	CE  	2002	8	7	AUS20020765      	1	20020724	G	2820		CONNECTOR       	            	            	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	AIRCRAFT FUEL DI	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FLEXIBLE FUEL LINE CONNECTORS PERISHED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002080700122	20020807	00122	EA  	2002	8	7	AUS20020766      	2	20020717	G	7421	RHB37E	SPARK PLUG      	CHAMPION    	RHB37E      	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	SPARK PLUG/IGNIT	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH ENGINE NO2 CYLINDER TOP SPARK PLUG DEFECTIVE. PLUG GAP WAS OUT OF ADJUSTMENT AND CERAMIC INSULATOR CRACKED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002080700123	20020807	00123	CE  	2002	8	7	AUS20020774      	1	20020724	G	7920	124700210CR0310	HOSE            	CONT        	GTSIO520L   	CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE OIL DISTR	TRANSPOSED      	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 		1329 							(AUS) LH ENGINE OIL FILTER SUPPLY AND DISCHARGE HOSES TRANSPOSED. OIL FILTER RUPTURED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	RT	A7CE    	E7CE	5	C	P45GL	 
2002080700124	20020807	00124	NM  	2002	8	7	AUS20020775      	1	20020729	G	2750	5906989202	FITTING         	SUNDSTRANDEM	745581A     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TRAILING EDGE FL	SEPARATED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				1981					(AUS) SECONDARY DRIVE FLEXIBLE SHAFT ALUMINIUM END FITTING SEPARATEDFROM THE OUTER WIRE BRAID. THE INNER FLEX DRIVE WAS 	FOUND TO BE SLIGHTLY BENT AT ONE END. DURING REMOVAL OF THE DRIVE SHAFT, IT WAS FOUND THAT THE OTHER ALUMINIUM END FITTI	NG HAD COME FREE FROM THE OUTER WIRE BRAID.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002080700125	20020807	00125	NM  	2002	8	7	AUS20020776      	1	20020729	G	5751	85740005003	AILERON         	            	            	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	AILERONS	DAMAGED         	W			    	K	 	 	 	NONE                    				C	 	 	F.O.D.                    			CL	CLIMB          	1			AU	S 	 				8824330429					(AUS) RH AILERON DAMAGED IN AREA OF LH TRAILING EDGE. DAMAGE WAS THEEXIT POINT OF A LIGHTNING STRIKE. THE AREA OF DAMAGE	 WASAPPROXIMATELY 193.5SQUAREMM (3SQIN) THROUGH SEVEN RIVET HEADS WITH A HOLE OF APPROXIMATELY 25.4MM (1IN). SEE MDR 02/	0777 FORINFORMATION ON DAMAGE CAUSED AT THE OTHER LIGHTNING EXIT POINT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002080700126	20020807	00126	NM  	2002	8	7	AUS20020777      	1	20020729	G	5520	85740001003	ELEVATOR        	            	            	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ELEVATOR STRUCTU	DAMAGED         	W			    	K	 	 	 	NONE                    				C	 	 	F.O.D.                    			CL	CLIMB          	1			AU	S 	 									(AUS) AIRCRAFT STRUCK BY LIGHTNING. LIGHTNING EXITED AIRCRAFT AT THE RH OUTBOARD TRAILING EDGE OF THE RH ELEVATOR. DAMAG	E WAS A DEFORMEDAREA OF APPROXIMATELY 200MM BY 100MM (8IN BY 4IN) AND AN EXIT HOLE OF APPROXIMATELY 38.1MM (1.5IN). SEE 	MDR 02/0776 FOR INFORMATION ON THE DAMAGE CAUSED AT THE OTHER EXIT POINT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002090600048	20020906	00048	NM  	2002	9	6	AUS20020779      	1	20020724	G	2731	AR7077M3	ACTUATOR        	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		ELEVATOR TAB CON	FAULTY          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 	 		17816		AA0301					(AUS) STABILISER TRIM ACTUATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002090600049	20020906	00049	NM  	2002	9	6	AUS20020780      	1	20020725	G	2510	110764101	INERTIA REEL    	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FLIGHT COMPARTME	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FIRST OFFICERS SEAT BELT SHOULDER HARNESS RH INERTIA REEL FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002090900001	20020909	00001	EU  	2002	9	9	AUS20020781      	1	20020429	G	2752	9787320307	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLAP ACTUATOR FAULTY.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002090600050	20020906	00050	SO  	2002	9	6	AUS20020782      	1	20020730	G	2731	4173404	CABLE           	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR TAB CON	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) REAR ELEVATOR TRIM CABLE PNO 41734-78 BROKEN AT TRIM SERVO. INSPECTION OF FORWARD ELEVATOR TRIM CABLE PNO 41734-77	 DAMAGEDDUE TO CABLE OVERRUN ON DRUM.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002090600051	20020906	00051	NM  	2002	9	6	AUS20020784      	1	20020729	G	2824		VALVE           	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUEL TRANSFER VA	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 	 									(AUS) FUEL CROSSFEED VALVE FAILED IN THE OPEN' POSITION.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002090600052	20020906	00052	CE  	2002	9	6	AUS20020788      	1	20020711	G	3252	08424057	BARREL          	CESSNA      	0842410     	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	SHIMMY DAMPER	BROKEN          	W			    	K	 	 	 	NONE                    				O	F	 	OTHER                     	FLT CONT AFFECTED         		LD	LANDING        	1			AU	S 	 									(AUS) NOSE LANDING GEAR SHIMMY DAMPER BODY BROKEN AWAY FROM ATTACHMENTLUG.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002090600053	20020906	00053	EA  	2002	9	6	AUS20020789      	2	20020614	G	8540	STD2208	SCREW           	LYC         	VO540C2A    	HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  	 		            		RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 	 				L89543					(AUS) ENGINE ACCESSORY DRIVE GEAR PNO 67609 TO STARTER DRIVE GEAR PNO 67583 ATTACHMENT STUDS (6OFF) PNO STD-2208 AND DOW	ELS (3OFF) PNO72139 SHEARED.					1	G	7	1 	3O	3	O	 	4H11    	E304				 
2002090600054	20020906	00054	SW  	2002	9	6	AUS20020790      	1	20020710	G	7603	660166007	CABLE           	LYC         	IO360A3B6   	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C212   	GL  	POWER LEVER	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE THROTTLE CABLE WORN. CABLE WAS STIFF TO OPERATE AND JAMMED ON SEVERAL OCCASIONS.						1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2002090900008	20020909	00008	SW  	2002	9	9	AUS20020793      	1	20020729	G	7120	BC001198050	MOUNT           			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE UPPER MOUNT HEAT DAMAGED. HEAT DAMAGE ALSO FOUND ON HOSES PN SS1001K000312 AND PN SS1001F0000100.  NO CA	USE OF DAMAGE WAS FOUND BUT IT IS SUSPECTED THAT A FUEL LEAK HAD OCCURRED AT THE NR 10 FUEL NOZZLE FITTING ALTHOUGH THE 	FITTING WAS FOUND TO BE CORRECTLY TORQUED.				2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2002090600055	20020906	00055	SO  	2002	9	6	AUS20020797      	1	20020518	G	3230	AN8374D	FITTING         	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR RET	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HYDRAULIC ELBOW FITTING ON INNER LH LANDING GEAR DOOR ACTUATORBROKEN.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002090600056	20020906	00056	EU  	2002	9	6	AUS20020798      	1	20020515	G	2700		RELAY           	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		FLIGHT CONTROL S	FAULTY          	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 									(AUS) FLIGHT CONTROL TAKEOFF WARNING RELAY FAULTY. CONNECTOR LOCATED AT REAR PRESSURE BULKHEAD DIRTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002090600057	20020906	00057	EU  	2002	9	6	AUS20020799      	1	20020526	G	2460		CONNECTOR       	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		DC POWER DISTRIB	FAULTY          	W			    	K	 	 	 	NONE                    				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 									(AUS) NO2 GENERATOR FEED PLUG SUSPECT DIRTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002090600058	20020906	00058	EU  	2002	9	6	AUS20020800      	1	20020510	G	2432	23531	BATTERY         	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		BATTERY/CHARGER	OVERHEATED      	W			    	K	 	 	 	NONE                    				H	M	J	ELECT. POWER LOSS-50 PC   	OVER TEMP                 	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 	 		87   							(AUS) FORWARD BATTERY OVERHEATED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002090600059	20020906	00059	EU  	2002	9	6	AUS20020801      	1	20020502	G	3230		DOWNLOCK        	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR RET	CONTAMINATED    	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		NR	NOT REPORTED   	1			AU	S 	 									(AUS) LANDING GEAR DOWNLOCK SWITCH AND DOOR UPLOCK SWITCH CONTAMINATEDWITH DIRT AND GREASE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002090600060	20020906	00060	EU  	2002	9	6	AUS20020804      	1	20020516	G	3232	1252515	ACTUATOR        	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR DOO	LEAKING         	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 	 		20074		AH665					(AUS) RH MAIN LANDING GEAR DOOR AFT ACTUATOR LEAKING INTERNALLY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002090600061	20020906	00061	EU  	2002	9	6	AUS20020806      	1	20020514	G	2432	23531	BATTERY         	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		BATTERY/CHARGER	OVERHEATED      	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		12   		D1433					(AUS) FORWARD BATTERY OVERHEATED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002090600062	20020906	00062	NM  	2002	9	6	AUS20020807      	1	20020716	G	2421		GENERATOR       	            	            	DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW123D      	52152	NE  	 		            		AC GENERATOR-ALT	FAULTY          	W			    	K	 	 	 	NONE                    				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 	 									(AUS) NO1 AC GENERATOR FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2002090600063	20020906	00063	NM  	2002	9	6	AUS20020809      	1	20020724	G	2720		MODULE          	            	            	BOEING	767   	76733A      	1385209	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		RUDDER CONTROL S	FAILED          	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 	 									(AUS) RUDDER RATIO MODULE FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2002090600064	20020906	00064	NM  	2002	9	6	AUS20020813      	1	20020801	G	2740	91238071	RELAY           	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		STABILIZER CONTR	FAULTY          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 	 									(AUS) STABILISER TRIM RELAY FAULTY. RELAY R64 AUXILIARY CONTACTS 13 AND 14 FAILED TO OPEN WHEN ENERGISED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002090600065	20020906	00065	EA  	2002	9	6	AUS20020818      	2	20020510	G	7310		LINE            	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE FUEL DIST	LOOSE           	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 	 									(AUS) FUEL PRESSURE LINE ON FCU LOOSE. LOSS OF POWER.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002090600066	20020906	00066	SW  	2002	9	6	AUS20020819      	2	20020604	G	7414	105413Y	SEAL            	JACOBP      	R755A2      	CESSNA	195   	195         	2073102	CE  	JACOBP	R755  	R755A2      	35006	SW  	HAMSTD	2B	2B20        	NE  	MAGNETO/DISTRIBU	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				5396927866					(AUS) MAGNETO/DISTRIBUTOR OIL SEAL DETERIORATED AND LEAKING. FURTHERINVESTIGATION ALSO FOUND CONTACTS BURNT AND PITTED. 	CAPACITOR UNSERVICEABLE.					1	H	7	1 	3R	3	R	NC	A790    	TC237	5	C	P255	 
2002090900023	20020909	00023	CE  	2002	9	9	AUS20020820      	1	20020801	G	5313	0713006	STRINGER        			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470R       	17026	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT LOWER ENGINE MOUNT STRINGER CRACKED IN LOWER RH RADIUS OF "U"  SECTION. CRACK RUNS FROM THE FORWARD EDGE AND AL	ONG THE AFT BEND.					1	H	7	1 	3O	3	O	 	5A6     	E273				 
2002090600067	20020906	00067	NE  	2002	9	6	AUS20020821      	2	20020715	G	7310	5905587	FILTER          	PWA         	PW118A      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ENGINE FUEL DIST	DIRTY           	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 	 				2011TLZ					(AUS) RH ENGINE FUEL FILTER LIGHTLY CONTAMINATED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2002090600068	20020906	00068	SO  	2002	9	6	AUS20020822      	2	20020802	G	8530	629690	PISTON PIN      	CONT        	TSIO360KB   	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	RECIPROCATING EN	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		661  		315114					(AUS) NO1 ENGINE PISTON PINS (6OFF) HAD SEVERE DAMAGE TO THE ALUMINIUMEND CAPS. THE END CAPS HAD MIGRATED OUTWARDS AND W	ERE RUBBING ONTHE CYLINDER WALLS. METAL CONTAMINATION OF ENGINE OIL SYSTEM.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002090600069	20020906	00069	SO  	2002	9	6	AUS20020823      	2	20020807	G	8530	648002	SHAFT           	CONT        	TSIO360KB   	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	RECIPROCATING EN	SCORED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1071 							(AUS) ROCKER SHAFT AND BUSH SCORED. SUSPECT CAUSED BY LACK OF LUBRICATION.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002090600070	20020906	00070	SO  	2002	9	6	AUS20020824      	1	20020716	G	2810	492308	DRAIN VALVE     	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	FUEL STORAGE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH FUEL SYSTEM DRAIN VALVE CORRODED DUE TO WATER CONTAMINATION. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600071	20020906	00071	SO  	2002	9	6	AUS20020825      	1	20020716	G	2810	492308	DRAIN VALVE     	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	FUEL STORAGE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH FUEL DRAIN VALVE CORRODED DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600072	20020906	00072	SO  	2002	9	6	AUS20020826      	1	20020716	G	2820	6390194	HOSE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH FUEL HOSE UNSERVICEABLE.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600073	20020906	00073	SO  	2002	9	6	AUS20020827      	1	20020716	G	2820	6390194	HOSE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH FUEL HOSE UNSERVICEABLE.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090900024	20020909	00024	SO  	2002	9	9	AUS20020828      	1	20020717	G	2820	AN83244	FITTING         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	FUEL DIST	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SYSTEM FITTING UNSERVICEABLE.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600074	20020906	00074	SO  	2002	9	6	AUS20020829      	1	20020716	G	2820	8623840	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE UNSERVICEABLE.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600075	20020906	00075	SO  	2002	9	6	AUS20020830      	1	20020716	G	2820	8623839	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE UNSERVICEABLE.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600076	20020906	00076	SO  	2002	9	6	AUS20020831      	1	20020716	G	2820	8623806	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE UNSERVICEABLE.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600077	20020906	00077	SO  	2002	9	6	AUS20020832      	1	20020716	G	2820	8623805	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE UNSERVICEABLE.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600078	20020906	00078	SO  	2002	9	6	AUS20020833      	1	20020717	G	2820	8625402	FITTING         	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM T' FITTING UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600079	20020906	00079	SO  	2002	9	6	AUS20020834      	1	20020716	G	2822	AN8166	NIPPLE          	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	FUEL BOOST PUMP	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PUMP NIPPLE UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600080	20020906	00080	SO  	2002	9	6	AUS20020835      	1	20020717	G	2820	8623812	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600081	20020906	00081	SO  	2002	9	6	AUS20020836      	1	20020717	G	2820	8623811	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600082	20020906	00082	SO  	2002	9	6	AUS20020837      	1	20020717	G	2820	AN9196D	REDUCER         	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM REDUCER UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600083	20020906	00083	SO  	2002	9	6	AUS20020838      	1	20020717	G	2820	AN8266D	FITTING         	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM T' FITTING UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600084	20020906	00084	EA  	2002	9	6	AUS20020839      	2	20020717	G	7314	LW15399	PUMP            	LYC         	O360E1A6    	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ENGINE FUEL PUMP	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE FUEL PUMP CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600085	20020906	00085	SO  	2002	9	6	AUS20020840      	1	20020716	G	2822	480543	PUMP            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	FUEL BOOST PUMP	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PUMP CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600086	20020906	00086	SO  	2002	9	6	AUS20020841      	1	20020716	G	2822	480543	PUMP            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	FUEL BOOST PUMP	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PUMP CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600087	20020906	00087	SO  	2002	9	6	AUS20020842      	1	20020716	G	2822	AN8226	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	FUEL BOOST PUMP	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PUMP ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600088	20020906	00088	SO  	2002	9	6	AUS20020843      	1	20020717	G	2820	AN8376	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600089	20020906	00089	SO  	2002	9	6	AUS20020844      	1	20020717	G	2820	AN8378	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600090	20020906	00090	SO  	2002	9	6	AUS20020845      	1	20020717	G	2820	AN8218	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600091	20020906	00091	SO  	2002	9	6	AUS20020846      	1	20020716	G	2820	AN8336	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600092	20020906	00092	SO  	2002	9	6	AUS20020847      	1	20020715	G	2820	63901101	HOSE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		2816 							(AUS) FUEL SYSTEM HOSE UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600093	20020906	00093	SO  	2002	9	6	AUS20020848      	1	20020715	G	2820	6390124	HOSE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		281  							(AUS) FUEL SYSTEM HOSE UNSERVICEABLE DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090900025	20020909	00025	EA  	2002	9	9	AUS20020849      	2	20020717	G	7322	105219	CARBURETOR      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CARBURETOR CORRODED DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600094	20020906	00094	SO  	2002	9	6	AUS20020850      	1	20020717	G	2820	8623803	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600095	20020906	00095	SO  	2002	9	6	AUS20020851      	1	20020717	G	2820	8623804	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600096	20020906	00096	SO  	2002	9	6	AUS20020852      	1	20020717	G	2820	8623807	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600097	20020906	00097	SO  	2002	9	6	AUS20020853      	1	20020717	G	2820	8623810	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600098	20020906	00098	SO  	2002	9	6	AUS20020854      	1	20020717	G	2820	8623809	TUBE            	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600099	20020906	00099	SO  	2002	9	6	AUS20020855      	2	20020807	G	8530	646460	EXHAUST VALVE   	CONT        	TSIO360KB   	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	RECIPROCATING EN	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1071 							(AUS) NO3 CYLINDER EXHAUST VALVE TIP WORN EXCESSIVELY. CORRESPONDINGROCKER DAMAGED ON CONTACT AREA. EXHAUST VALVES PNO 6	46460 AND INLET VALVES PNO 646459 IN OTHER CYLINDERS ALSO SHOWING SIGNS OFPITTING ON THE TIPS.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002090600100	20020906	00100	NM  	2002	9	6	AUS20020857      	1	20020807	G	3230	AE2464163E0192	HOSE            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		LANDING GEAR RET	RUPTURED        	W			    	K	 	 	 	NONE                    				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR UPLOCK ACTUATOR HOSE RUPTURED. LOSS OF HYDRAULIC FLUID CAUSED FAILURE OF LH ENGINE DRIVEN HYD	RAULICPUMP.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002090900027	20020909	00027	CE  	2002	9	9	AUS20020858      	1	20020704	G	2434	A165235	BOLT            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ALTERNATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			290  							(AUS) ALTERNATOR THROUGH BOLTS LOOSE. ROTOR RUBBING ON FIELD WINDINGS CAUSING DAMAGE TO STATOR.  SUSPECT CAUSED BY FAILU	RE TO RETORQUE BOLTS AFTER FIFTEEN HOURS OPERATION.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002090600101	20020906	00101	CE  	2002	9	6	AUS20020859      	1	20020725	G	3246	4075D	WHEEL           	            	            	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	WHEEL/SKI/FLOAT	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WHEEL CRACKED ALONG INBOARD EDGE OF BEAD SEAT. CRACK LENGTH APPROXIMATELY 120MM (4.72IN).						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002090600102	20020906	00102	EU  	2002	9	6	AUS20020860      	1	20020725	G	5540	68340451	BRACKET         	PARTEN      	RUDDER      	PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	RUDDER STRUCTURE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				146					(AUS) TOP RUDDER HINGE BRACKET CRACKED.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2002090900028	20020909	00028	CE  	2002	9	9	AUS20020861      	1	20020624	G	5312		BULKHEAD        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER REAR PRESSURE BULKHEAD CRACKED. CRACK IS LOCATED IN THE AREA ONE ROW OF RIVETS DOWN FROM THE LAP JOINT AND D	IRECTLY ABOVE THE OUTFLOW VALVE. CRACKING IS SIMILAR TO THAT DESCRIBED IN AD/B200/67 BUT WAS NOT FOUND DURING THE AD CHE	CK. THE AIRCRAFT HAS 321 CYCLES TO RUN UNTIL THE NEXT INSPECTION IAW AD/B200/67.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002090600103	20020906	00103	SO  	2002	9	6	AUS20020864      	1	20020717	G	2820	AN8166	NIPPLE          	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM NIPPLE CORRODED DUE TO FUEL SYSTEM WATERCONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600104	20020906	00104	SO  	2002	9	6	AUS20020865      	1	20020717	G	2820	AN8166	NIPPLE          	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM NIPPLE CORRODED DUE TO FUEL SYSTEM WATERCONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600105	20020906	00105	SO  	2002	9	6	AUS20020866      	1	20020717	G	2820	AN8226	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM ELBOW UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600106	20020906	00106	SO  	2002	9	6	AUS20020867      	1	20020717	G	2820	AN8226	ELBOW           	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM ELBOW UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600107	20020906	00107	SO  	2002	9	6	AUS20020868      	1	20020717	G	2820	AN9102	COUPLING        	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM COUPLING UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600108	20020906	00108	SO  	2002	9	6	AUS20020869      	1	20020717	G	2820	AN9102	COUPLING        	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM AFT COUPLING UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600109	20020906	00109	SO  	2002	9	6	AUS20020870      	1	20020717	G	2820	AN9102	COUPLING        	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM FORWARD COUPLING UNSERVICEABLE AND CORRODED DUE TOFUEL SYSTEM WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600110	20020906	00110	SO  	2002	9	6	AUS20020871      	1	20020717	G	2820	AN9102	COUPLING        	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AIRCRAFT FUEL DI	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL SYSTEM AFT COUPLING UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600111	20020906	00111	SO  	2002	9	6	AUS20020875      	1	20020516	G	2910	1107212159	HOSE            	            	            	EMB   	110   	EMB110P1    	3260122	SO  	      		            			 		            		HYDRAULIC SYSTEM	FAILED          	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 	 									(AUS) HYDRAULIC HOSE FAILED IN AN AREA APPROXIMATELY 200MM (8IN) ALONGTHE LENGTH ALONG THE HOSE. LOSS OF HYDRAULIC FLUID	. SUSPECT HOSEHAD SUFFERED SOME DISTRESS DURING ITS LIFE.					1	L	7	2 	4T			 	A21SO   					 
2002090600112	20020906	00112	CE  	2002	9	6	AUS20020876      	1	20020422	G	5312		BULKHEAD        	            	            	CESSNA	206   	U206G       	2073356	CE  	      		            			 		            		FUSELAGE MAIN, B	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH FORWARD DOORPOST BULKHEADCRACKED.						1	H	7	1 	3O			 	A4CE    					 
2002090600113	20020906	00113	EA  	2002	9	6	AUS20020877      	1	20020712	G	5310		STRUCTURE       	            	            	DHAV  	DHC6  	DHC6        	2802606	EA  	      		            			 		            		FUSELAGE MAIN, S	DAMAGED         	W			    	K	 	 	 	NONE                    				C	 	 	F.O.D.                    			LD	LANDING        	1			AU	S 	 									(AUS) FORWARD BULKHEAD, NLG ATTACHMENT FITTINGS AND SURROUNDING LOWER FUSELAGE STRUCTURE DAMAGED WHEN THE NOSEWHEEL CONT	ACTED A ROCKDURING LANDING.					1	H	7	2 	3T			RT	A9EA    					 
2002090600114	20020906	00114		2002	9	6	AUS20020878      	4	20020520	G	2312		ANTENNA         	            	            	DHAV  	DHC6  	DHC6        	2802606	EA  	      		            			 		            		VHF COMMUNICATIO	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) VHF ANTENNA DAMAGED BY IMPACT FROM AN UNKNOWN OBJECT. FUSELAGESKIN AFT OF THE ANTENNA MOUNT SUFFERED A 50.8MM (2IN	) TEAR. THE ANTENNA IS MOUNTED ON THE LOWER FUSELAGE AT STN 376. FOD					1	H	7	2 	3T			RT	A9EA    					 
2002090600115	20020906	00115	EA  	2002	9	6	AUS20020879      	1	20020716	G	3246	JUN01727	WHEEL           	CLEVELAND   	1500X12X14  	DHAV  	DHC6  	DHC6        	2802606	EA  	      		            			 		            		WHEEL/SKI/FLOAT	DAMAGED         	W			    	K	 	 	 	NONE                    				O	E	 	OTHER                     	VIBRATION/BUFFET          		LD	LANDING        	1			AU	S 	 				JUN01727					(AUS) LH MAIN WHEEL OUTER HUB DAMAGED. TYRE DEFLATED.						1	H	7	2 	3T			RT	A9EA    					 
2002090600116	20020906	00116	NM  	2002	9	6	AUS20020880      	1	20020523	G	2750		TORQUE TUBE     	            	            	DHAV  	DHC8  	DHC8*       	       	NM  	      		            			 		            		TRAILING EDGE FL	FAILED          	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 	 									(AUS) FLAP DRIVE TORQUE TUBE SEVERED AT A POINT APPROXIMATELY 4 METRESOUTBOARD OF THE LH NACELLE.						2	H	7	2 	4T			RT	A13NM   					 
2002090600117	20020906	00117	EA  	2002	9	6	AUS20020881      	2	20020702	G	7532		BLEED VALVE     	PWA         	PT6A41      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	 		            		COMPRESSOR BLEED	CONTAMINATED    	W			    	K	 	 	 	NONE                    				E	F	 	VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 	 									(AUS) NO2 ENGINE HP BLEED VALVE PISTON CONTAMINATED WITH GRIME.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002090600118	20020906	00118	SO  	2002	9	6	AUS20020885      	2	20020802	G	8530	637836	VALVE SPRING    	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1310 		268396R					(AUS) NO6 CYLINDER INNER EXHAUST VALVE SPRING BROKEN. METAL CONTAMINATION OF OIL SYSTEM.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002090600119	20020906	00119	SO  	2002	9	6	AUS20020886      	1	20020812	G	3246	16103000	WHEEL           	CLEVELAND   	4076A       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WHEEL/SKI/FLOAT	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NOSE WHEEL CRACKED FROM BEAD SEAT AREA THROUGH TO OUTER SURFACE.CRACK LENGTH 76.2MM (3IN).						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002090900039	20020909	00039	SO  	2002	9	9	AUS20020890      	1	20020503	G	2913		MOTOR           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HYDRAULIC PUMP,	CONTAMINATED    	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) POWER PACK ELECTRIC MOTOR CONTAMINATED BY OIL. DURING LANDING THE LT MAIN LANDING GEAR COLLAPSED.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2002090600120	20020906	00120	CE  	2002	9	6	AUS20020891      	1	20020318	G	8120	BH003250	SEAL            	GARRTT      	4659302     	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	EXHAUST TURBOCHA	FAILED          	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 				BH003250					(AUS) TURBOCHARGER OIL SEAL FAILED ALLOWING OIL TO ENTER THE ENGINE VIA THE INDUCTION SYSTEM.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002090600121	20020906	00121	EA  	2002	9	6	AUS20020892      	2	20020726	G	7414	1050746Y	GEAR            	BENDIX      	S6LN200     	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCA2X	HCA2XL2     	GL  	MAGNETO/DISTRIBU	STRIPPED        	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 				A151211					(AUS) LH ENGINE RH MAGNETO DISTRIBUTOR GEAR TEETH STRIPPED. APPROXIMATELY HALF OF THE TEETH WERE SHEARED OFF AT THE ROOT	ENDS. SUSPECT CAUSED BY ENGINE BACKFIRE.					1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P908	 
2002090600122	20020906	00122	EA  	2002	9	6	AUS20020898      	2	20020813	G	7313	7415125248642	INJECTOR        	BENDIX      	RSA5AD1     	PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	FUEL INJECTOR NO	DIRTY           	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 	 		896  		58354					(AUS) NO2 CYLINDER FUEL INJECTOR NOZZLE DIRTY.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2002090600123	20020906	00123	SW  	2002	9	6	AUS20020899      	1	20020709	G	6220	204011151001	BOLT            	BELL        	205812001   	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313A      	41549	NE  	 		            		MAIN ROTOR HEAD	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				ADA05660					(AUS) MAIN ROTOR BLADE BOLT SUSPECT CRACKED. FOUND DURING FLUORESCENT MAGNETIC PARTICLE INSPECTION.						1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002090600124	20020906	00124	NM  	2002	9	6	AUS20020901      	1	20020813	G	7830	3810056105	MODULE          	GE          	CFM563C     	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		THRUST REVERSER	LEAKING         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 				01082					(AUS) RH ENGINE THRUST REVERSER HYDRAULIC ISOLATION LEVER ASSEMBLYFAILED ALLOWING HYDRAULIC FLUID TO LEAK.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002090600125	20020906	00125	NE  	2002	9	6	AUS20020903      	1	20020813	G	2612		WIRE            	            	            	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  	 		            		FIRE DETECTION	WORN            	W			    	K	 	 	 	NONE                    				E	B	N	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             	CR	CRUISE         	1			AU	S 	 									(AUS) NO2 ENGINE FIRE WARNING. PRIMARY AND SECONDARY FIRE EXTINGUISHERS DISCHARGED. INVESTIGATION COULD FIND NO EVIDENCE	 OF FIRE. CAUSEDBY CHAFING OF FIRE WARNING SYSTEM WIRE.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002090600126	20020906	00126	SO  	2002	9	6	AUS20020908      	1	20020720	G	3230	JE73	ACTUATOR        	            	            	PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LANDING GEAR RET	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR DOWNLOCK ACTUATOR DEFORMED AND CRACKED.INVESTIGATION FOUND WASHERS HAD BEEN ADDED BETWEEN THE	 FRONT ANDREAR HOOK ON THE LINK ASSEMBLY.					1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920	 
2002090600127	20020906	00127	SO  	2002	9	6	AUS20020909      	1	20020807	G	3230		DOWNLOCK        	            	            	PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR RET	SEIZED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR DOWNLOCK PARTIALLY SEIZED PREVENTING POSITIVE LOCKING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002090600128	20020906	00128	NM  	2002	9	6	AUS20020910      	1	20020816	G	3240		LINE            	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR BRA	LOOSE           	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR BRAKE HYDRAULIC LINE SWIVEL FITTING B' NUT  LOOSE. INVESTIGATION FOUND THE RH MAIN LANDING GE	AR DRAG STRUT  ACTUATOR SWIVEL FITTING LINE ALSO LOOSE. A SIGNIFICANT LOSS OF  HYDRAULIC FLUID OCCURRED. FURTHER INVESTI	GATION FOUND THAT THERE  WAS NO EVIDENCE OF FLUID LEAKING FROM THE LAST FLIGHT. FURTHER  INVESTIGATION FOUND EVIDENCE OF	 SABOTAGE/CRIMINAL ACTION.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002090600129	20020906	00129	SO  	2002	9	6	AUS20020911      	2	20020720	G	8530	537750	STUD            	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIPROCATING EN	SHEARED         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 		551  		PN653452					(AUS) CYLINDER ROCKER SHAFT BOLTS LOOSE. ONE STUD FRACTURED WITHSUBSEQUENT DAMAGE TO THE INLET VALVE PUSHROD AND TUBE.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002090600130	20020906	00130	SO  	2002	9	6	AUS20020912      	2	20020707	G	8520	65411912A2	CRANKCASE       	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 		1077 		810536R					(AUS) ENGINE CRANKCASE CRACKED. NO5 CYLINDER REAR HOLDDOWN STUD NUT LOOSENED LEADING TO FAILURE OF THE OTHER HOLDDOWN NU	TS ANDSEPARATION OF THE CYLINDER.					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002090600131	20020906	00131	CE  	2002	9	6	AUS20020913      	1	20020805	G	2700	051010544	CABLE           	            	            	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	AMTR	C8289	C8289       	GL  	FLIGHT CONTROL S	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CONTROL CABLE CORRODED WITH APPROXIMATELY 50% OF THE STRANDSBROKEN/FRAYED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	EXPP5N	 
2002090600132	20020906	00132	CE  	2002	9	6	AUS20020914      	1	20020725	G	7602	S123411	CABLE           	LYC         	O320E2D     	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	AMTR	C8289	C8289       	GL  	MIXTURE CONTROL	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MIXTURE CONTROL CABLE INNER WIRE WORN TO LESS THAN 50% OF NORMALTHICKNESS. CABLE DIAMETER WAS 62MM (0.024IN) INSTE	AD OF THE NORMAL DIAMETER 1.6MM (0.062IN).					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	EXPP5N	 
2002090600133	20020906	00133	CE  	2002	9	6	AUS20020915      	1	20020725	G	7603	S123017	CABLE           	LYC         	O320E2D     	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	AMTR	C8289	C8289       	GL  	POWER LEVER	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) THROTTLE CONTROL INNER CABLE WORN BY MORE THAN 60% OF THE DIAMETER. WIRE DIAMETER WAS 0.5MM (0.019IN) INSTEAD OF T	HE NORMAL 1.5MM (0.059IN).					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	EXPP5N	 
2002090600134	20020906	00134	CE  	2002	9	6	AUS20020916      	1	20020805	G	2700	051010545	CABLE           	            	            	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	AMTR	C8289	C8289       	GL  	FLIGHT CONTROL S	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CONTROL CABLE RUSTED IN AREA OF REAR FUSELAGE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	EXPP5N	 
2002090600135	20020906	00135	SO  	2002	9	6	AUS20020917      	1	20020818	G	5220	86602	WINDOW          	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	EMERGENCY EXITS	SEPARATED       	W			    	K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 	 									(AUS) EMERGENCY EXIT WINDOW SEPARATED FROM AIRCRAFT. THE EMERGENCY EXIT HAD BEEN REMOVED AND REINSTALLED THREE DAY PREVI	OUSLY TO CARRYOUT AD/GEN/37 (EMERGENCY EXIT INSPECTION). THE WINDOW SEPARATED DURING THE FIRST FLIGHT FOLLOWING THE INSP	ECTION. INVESTIGATION FOUND THAT THE FORWARD LOCKING LUG MAY NOT HAVE BEEN COMPLETELY ENGAGED. THE CORRECT LOCKING OF TH	E FORWARD LUG CANNOT BE POSITIVELY CONFIRMED AS THERE IS NO INSPECTION HOLE.			1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002090600136	20020906	00136	EU  	2002	9	6	AUS20020918      	1	20020812	G	3240	086170046	LINK            	            	            	REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	LANDING GEAR BRA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 	 		3859 							(AUS) COPILOTS OUTBOARD BRAKE PEDAL RH LINK ASSEMBLY CRACKED IN THE AREA OF THE WELD ATTACHING THE CLEVIS RODEND.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2002090600137	20020906	00137	CE  	2002	9	6	AUS20020926      	1	20020821	G	2750		CABLE           	            	            	CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  	 		            		TRAILING EDGE FL	FRAYED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TRAILING EDGE FLAP CABLES (14OFF) FRAYED. FLAP CABLE PART NUMBERS ARE:- PNO 6565007-102-1CR, PNO 6565007-100-1CR, 	PNO 6565007-114CR, PNO 6565007-112CR, PNO 6565007-401, PNO6565007-90CR, PNO 5565150-16CR (2OFF), PNO 5565150-3CR(2OFF), 	PNO 5565150-2CR, PNO 5565150-4CR, PNO 6565007-97-1CR & PNO6565007-95-1CR. CABLES ARE FRAYED ON THE INSIDE OF A TIGHT BEN	D RADIUS WHERE THEY ARE ATTACHED TO BELLCRANKS.			1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2002090600138	20020906	00138	CE  	2002	9	6	AUS20020927      	1	20020821	G	5712	651102829	RIB             	            	            	CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  	 		            		WING, RIB/BULKHE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING RIB WEB CRACKED DUE TO FLEXING CAUSED BY AILERON PULLEYBRACKET AND FLAP PULLEY BRACKET ATTACHED TO RIB.						1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2002090600139	20020906	00139	SO  	2002	9	6	AUS20020928      	1	20020821	G	5711	2355100	SPAR            	PIPER       	PA30160     	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				301785					(AUS) LH WING INBOARD SPAR LOWER SPAR CAP ASSEMBLY SEVERELY CORRODED. CORROSION IS INITIATED BY INGRESS OF EXHAUST GASSE	S THROUGH A FUEL DRAIN HOLE IN A PANEL FORWARD OF THE SPAR. THE FUEL DRAIN IS PART OF CANCELLED AD/PA30&39/20.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2002090900059	20020909	00059	GL  	2002	9	9	AUS20020930      	3	20020819	G	6114	FE248	HUB             			AMTR  	VANS  	RV8         	       	GL  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCF2Y	HCF2YR1     	GL  	PROPELLER	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB IS A SUSPECT UNAPPROVED PART.  INVESTIGATION FOUND THAT THE HUB SERIAL NUMBER IS NOT USED ON THIS TY	PE OF AIRCRAFT.  HUB FLANGE TYPE ALSO INCORRECT.  FURTHER INVESTIGATION FOUND THAT THE ORIGINAL MODEL STAMPINGS HAD BEEN	 PREVIOUSLY REMOVED. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.				1	L	7	1 	3O	3	O	NT	EXPA1L71	E1CE	5	C	P27EA	 
2002090900060	20020909	00060	GL  	2002	9	9	AUS20020931      	3	20020816	G	6111	F7666A2	BLADE           			AMTR  	VANS  	RV8         	       	GL  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCF2Y	HCF2YR1     	GL  	PROPELLER	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER BLADE SUSPECT UNAPPROVED PART.  INVESTIGATION FOUND THAT THE BLADE HAD ORIGINALLY BEEN AN FC7666A BLADE 	BUT HAD BEEN ILLEGALLY MODIFIED BY UNKNOWN PARTIES TO AN F7666A BLADE.  THE BLADE MANUFACTURER WAS CONTACTED AND CONFIRM	ED THAT THE BLADE WITH THE SN E1230 WAS ORIGINALLY AN FC8468-6R BLADE.   SUSPECT SERIAL NUMBER STAMPED ON BLADE WAS A BO	GUS NUMBER.  UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.			1	L	7	1 	3O	3	O	NT	EXPA1L71	E1CE	5	C	P27EA	 
2002090600140	20020906	00140	SO  	2002	9	6	AUS20020933      	1	20020813	G	5553		FITTING         	            	            	PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	2D34C215    	GL  	VERTICAL STABILI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) VERTICAL FIN ATTACHMENT FITTING HEAVILY CORRODED. FIN SPAR ALSO CORRODED WITH RIVETS MISSING. PART NUMBERS OF AFFE	CTED ITEMS:-PNO 86548-02, PNO 78935-27, PNO 35697-02 & PNO 38622-02.					1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2002090600141	20020906	00141	SO  	2002	9	6	AUS20020935      	1	20020820	G	5720	4465502	PLATE           	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WING, MISCELLANE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		12855							(AUS) WING SPLICE PLATE CONTAINED EXFOLIATION CORROSION ON THE RH AFT EDGE. FOUND DURING INSPECTION IAW AD/PA31/122 AMDT	1.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002090600142	20020906	00142	SO  	2002	9	6	AUS20020937      	2	20020701	G	8520	SA42720	BEARING         	CONT        	O470U       	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				286516R					(AUS) CRANKSHAFT MAIN BEARINGS SHOWED INDICATIONS OF PREMATURE FAILURE. BEARINGS PNO SA 633136 (2OFF) AND PNO SA 642720 	(6OFF). ENGINEWAS BEING BULK STRIPPED FOLLOWING PROPELLER STRIKE.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002090600143	20020906	00143	NE  	2002	9	6	AUS20020938      	2	20020818	G	7230	3040689	IMPELLER        	PWA         	PW118A      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	TURBINE ENGINE C	FOD             	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				PCE115662					(AUS) RH ENGINE LOW PRESSURE IMPELLER DAMAGED BEYOND LIMITS BY FOD.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2002090900065	20020909	00065	SO  	2002	9	9	AUS20020940      	1	20020823	G	2140	461731	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			181  							(AUS) FUEL PRESSURE REGULATOR LEAKING FUEL FROM DIAPHRAGM WHEN THE HEATER CYCLES OFF.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002090600144	20020906	00144	EA  	2002	9	6	AUS20020942      	2	20020722	G	8520	STD2209	BOLT            	LYC         	O540A1D5    	PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540A1D5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	RECIPROCATING EN	LOOSE           	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 									(AUS) ENGINE CRANKSHAFT GEAR RETAINING BOLT LOOSE. THE BOLT HEAD WASWORN DOWN FROM RUBBING ON THE INSIDE OF THE OIL PUMP	 DRIVESHAFT.THE CRANKSHAFT GEAR ROTATED ON THE BOLT, SHEARING THE DRIVE DOWEL AND GEAR TEETH. THE LH MAGNETO DRIVE GEAR 	DAMAGED IN AREA WHERE THE DRIVE COUPLING LUGS CONTACTED THE SIDES OF THE CUSHIONRETAINING POCKET. GEAR TOOTH DAMAGE TRAN	SFERRED BETWEEN GEARS,WITH BROKEN TOOTH FOUND WEDGED BETWEEN THE TEETH OF THE IDLER GEAR . ONE TOOTH BROKEN OFF IDLER GE	AR. LH MAGNETODISTRIBUTOR  GEAR TEETH STRIPPED. OIL PUMP HOUSING SCORED. GEAR PNO 13S19647.  BOLT PNO STD 2209. CRANKSHA	FT PNO 75039.	1	L	7	1 	3O	3	O	 	2A10    	E295	5	N	P874	 
2002090600145	20020906	00145	SO  	2002	9	6	AUS20020944      	2	20020811	G	7322	194580	PUMP            	FACET       	MA45        	CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	FUEL CONTROL/REC	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		873  		PAM681305					(AUS) CARBURETTOR ACCELERATOR PUMP WORN AND BROKEN.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P25EA	 
2002090600146	20020906	00146	CE  	2002	9	6	AUS20020945      	1	20020821	G	2810	05235221	STRAP           	            	            	CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	AMTR	C8289	C8289       	GL  	FUEL STORAGE	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH FUEL TANK REAR STRAP ASSEMBLY LOOSE. RH FUEL TANK REAR STRAP ASSEMBLY BROKEN NEAR THE SCREW END. FOUND DURING I	NSPECTION IAW CESSNA CONTINUED AIRWORTHINESS PROGRAM 28-30-01.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	EXPP5N	 
2002090600147	20020906	00147	SO  	2002	9	6	AUS20020948      	1	20020807	G	3230	9515340	TUBE            	            	            	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR UP' HYDRAULIC TUBE CORRODED AND LEAKING THROUGH CORROSION HOLE LOCATED UNDER P' CLAMP.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002090600148	20020906	00148	SO  	2002	9	6	AUS20020949      	1	20020807	G	3230	9515339	TUBE            	            	            	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR HYDRAULIC PIPE CORRODED IN AREA UNDER P' CLAMP.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002090600149	20020906	00149	SO  	2002	9	6	AUS20020950      	1	20020824	G	6123	7871300	PLATE           	HARTZL      	BHCC2YF2    	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER FEATHE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 	 									(AUS) PROPELLER PITCH LEVER FEATHER STOP PLATE CRACKED PREVENTING OPERATION OF PITCH LEVER.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002090600150	20020906	00150	SO  	2002	9	6	AUS20020951      	1	20020824	G	6123	7871300	PLATE           	HARTZL      	BHCC2YF2    	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER FEATHE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PROPELLER PITCH CONTROL LEVER FEATHER STOP GATE PLATE CRACKED.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002090600151	20020906	00151	CE  	2002	9	6	AUS20020952      	1	20020808	G	2710	556555037R	CABLE           	            	            	CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  	 		            		AILERON CONTROL	FRAYED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AILERON INTERCONNECT CABLE FRAYED IN AREA WHERE THE CABLEPASSES OVER THE CONTROL COLUMN UPPER PULLEY. PULLEY IS	 LOCATEDAPPROXIMATELY 200MM (8IN) BELOW THE CONTROL WHEEL.					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2002090600152	20020906	00152	EA  	2002	9	6	AUS20020955      	2	20020828	G	7414	10391586	DISTRIBUTOR     	BENDIX      	S6LN1209    	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAGNETO/DISTRIBU	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		324  		A235988					(AUS) MAGNETO DISTRIBUTOR BLOCK BEARING LOOSE. MAGNETO CONTAMINATED WITH METAL DUE TO CONTACT BETWEEN DISTRIBUTOR GEAR A	NDELECTRODES. SUSPECT FAILURE DUE TO APPLICATION OF GREASE PNO10-27165 TO THE DISTRIBUTOR GEAR SHAFT AND BLOCK BEARING.					1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002090600153	20020906	00153	SW  	2002	9	6	AUS20020959      	1	20020816	G	2910	212076006007	VALVE           	            	            	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  	 		            		HYDRAULIC SYSTEM	FAULTY          	W			    	K	 	 	 	NONE                    				K	F	 	FLUID LOSS                	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			AU	S 	 		897  		3763					(AUS) NO1 HYDRAULIC SYSTEM INTEGRATED VALVE ASSEMBLY FAULTY.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002090600154	20020906	00154	SW  	2002	9	6	AUS20020960      	1	20020805	G	7312	10544F	HEATER          	PWA         	PT6T3BF     	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  	 		            		FUEL HEATER	LEAKING         	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		TO	TAKEOFF        	1			AU	S 	 		136  		62109					(AUS) FUEL/OIL HEATER LEAKING FROM WELD ON THE TOP OF THE HEATER. NOCRACK OR HOLE WAS VISIBLE USING A X10 MAGNIFYING GLA	SS.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002091000003	20020910	00003	CE  	2002	9	10	AUS20020961      	1	20020822	G	3230	504501033	TORQUE TUBE     			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR TORQUE TUBE CRACKED IN WELDED AREA AROUND THE FORK BOLT.   TORQUE TUBE INTERNALLY CORRODED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002090600155	20020906	00155	NE  	2002	9	6	AUS20020962      	1	20020820	G	6321	223414	PRESSURE SWITCH 	            	            	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  	 		            		MAIN ROTOR BRAKE	FAILED          	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			AU	S 	 									(AUS) ROTOR BRAKE PRESSURE SWITCH FAILED INTERNALLY.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002090600156	20020906	00156	NM  	2002	9	6	AUS20020963      	1	20020806	G	5320		ANGLE           	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUSELAGE, MISCEL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ADJACENT INTERCOSTAL TO SKIN ATTACHMENT ANGLES (3OFF) CRACKED INAREA OF DOOR 1R SURROUND STRUCTURE. CRACKS RUN ALO	NG THE FOLD LINES OF THE ANGLES. ANGLES ARE LOCATED AT STN 290 BETWEENSTRINGERS NO9 AND NO13R.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002090600157	20020906	00157	NM  	2002	9	6	AUS20020965      	1	20020806	G	5753	654640716	FLAP TRACK      	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TRAILING EDGE FL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				2406					(AUS) RH NO5 FLAP TRACK CRACKED IN LOWER OUTBOARD FLANGE.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101600022	20021016	00022	NM  	2002	10	16	AUS20020968      	1	20020829	G	2425	6229436101	SYMBOL GENERATOR	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		AC INDICATING SY	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 				3654					(AUS) FIRST OFFICERS SYMBOL GENERATOR FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101800051	20021018	00051	CE  	2002	10	18	AUS20020970      	1	20020827	G	3230	504501032	TORQUE TUBE     			CESSNA	310   	310R        	2074245	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR TORQUE TUBE CRACKED IN WELDED AREA AROUNDTHE FORK BOLT. TORQUE TUBE INTERNALLY CORRODED.						1	L	7	2 	3O	3	O	 	3A10    	E3SO	5	C	P22EA	 
2002101600023	20021016	00023	EA  	2002	10	16	AUS20020971      	2	20020814	G	8530	SL73857	PISTON RING     	LYC         	TIO540A2C   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 									(AUS) NO6 CYLINDER OIL CONTROL PISTON RING BROKEN. BROKEN RING INGESTED BY OIL PUMP.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2002101600024	20021016	00024	GL  	2002	10	16	AUS20020972      	2	20020717	G	7250	895007	SEAL            	RROYCE      	250C30P     	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  	 		            		TURBINE SECTION	DAMAGED         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 				895007					(AUS) ENGINE REMOVED DUE TO METAL CONTAMINATION. INVESTIGATION FOUNDTHE ROTATING POWER TURBINE LABYRINTH SEAL CONTACTED 	THE NO6 AND NO7 BEARING SUMP STATIONARY SEALS. WEAR PATTERN ON THE SEAL AREAS ARE OVAL SUGGESTING THAT THE ENGINE HAD BE	EN SUBJECTEDTO A HEAVY LANDING AT SOME TIME PREVIOUS.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002101600025	20021016	00025	NE  	2002	10	16	AUS20020974      	2	20020820	G	7421	9550168760	IGNITER         	TMECA       	ARRIEL1B    	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		SPARK PLUG/IGNIT	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 				556					(AUS) ENGINE IGNITERS FAULTY. IGNITER IS MANUFACTURED BY EYQUEM.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002101600026	20021016	00026	NM  	2002	10	16	AUS20020975      	1	20020830	G	3260	864202	PROXIMITY SENSOR	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR POS	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 	 									(AUS) NOSE LANDING GEAR NO2 WEIGHT ON WHEELS PROXIMITY SENSOR FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002101600027	20021016	00027	NM  	2002	10	16	AUS20020976      	1	20020625	G	3242	NAS1802311	BOLT            	            	            	BOEING	767   	767         	UTILUSE	NM  	GE    	CF6   	CF680C2*    	 	GL  	 		            		BRAKE	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) BRAKE ROD PIN RETAINING BOLT LOCK BOLTS MISSING. AIRCRAFT ISFIJIAN REGISTERED DQ-FJC. PERSONNEL/MAINTENANCE ERROR.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002101600028	20021016	00028	WP  	2002	10	16	AUS20020977      	2	20020831	G	7310	31024692	MANIFOLD        	GARRTT      	TPE33111U   	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE FUEL DIST	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH ENGINE SECONDARY FUEL MANIFOLD CRACKED IN AREA OF UPPERNOZZLE END SWAGED FITTING. LEAKING FUEL CAUGHT FIRE CAUS	ING DAMAGE TO FIRE TUBING ON MANIFOLDS, SUPPLY LINE, ENGINE MOUNTSAND COWLS.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2002101600029	20021016	00029	EU  	2002	10	16	AUS20020983      	1	20020627	G	6120		PROPELLER       	ROTOL       	R3544123F13 	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	PROPELLER CONTRO	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 	 									(AUS) N2 ENGINE PROPELLER AUTOCOARSEN. CAUSED BY INCORRECT SELECTION OF PROPELLER CONTROLS.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL	 
2002101600030	20021016	00030	SO  	2002	10	16	AUS20020984      	1	20020901	G	3221	6705403	TRUNNION        	            	            	PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	NOSE/TAIL LANDIN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) NOSE LANDING GEAR TRUNNION ATTACHMENT LUG FOR THE EXTENSION SPRING FAILED. NOSE LANDING GEAR COLLAPSED DURING LAND	ING.					1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2002101600031	20021016	00031	NM  	2002	10	16	AUS20020985      	1	20020905	G	2120	BACC10DU450Y	CLAMP           	            	            	BOEING	727   	727281      	138408N	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		AIR DISTRIBUTION	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 		40934							(AUS) LH PRIMARY HEAT EXCHANGER SUPPLY LINE CLAMP BROKEN.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002101600032	20021016	00032	CE  	2002	10	16	AUS20020991      	1	20020830	G	2434	DOFF10300B	ALTERNATOR      	            	            	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	DC GENERATOR-ALT	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				A164887					(AUS) ALTERNATOR FIELD SHORTED.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002101600033	20021016	00033	CE  	2002	10	16	AUS20020993      	1	20020829	G	2434	DOFF10300B	ALTERNATOR      	            	            	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	DC GENERATOR-ALT	FAILED          	W			    	K	 	 	 	NONE                    				O	H	 	OTHER                     	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			AU	S 	 				O661466					(AUS) ALTERNATOR FIELD SHORTED.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P3EA9	 
2002101600034	20021016	00034	CE  	2002	10	16	AUS20020995      	1	20020906	G	5711	512204123	SPAR CAP        	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		14201							(AUS) LH WING LOWER REAR SPAR CAP CORRODED IN AREA BETWEEN THE VERTICAL FLANGE AND THE SPAR WEB. CORRODED AREA IS LOCATE	D FORWARD OF THEAILERON FROM WS 206 TO WS 229.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002101600035	20021016	00035	CE  	2002	10	16	AUS20020996      	1	20020906	G	5730	512201120	SKIN            	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	WING, PLATES/SKI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		14201							(AUS) RH WING LOWER SKIN CONTAINED THREE CORROSION HOLES INTO THE TANK. AFT STRINGER CONTAINED EXFOLIATION CORROSION IN 	THE SAME LOCATION AS ONE OF THE HOLES.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002101600036	20021016	00036	SO  	2002	10	16	AUS20020997      	1	20020906	G	5730	6206105	DOUBLER         	            	            	PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING, PLATES/SKI	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING WALK SKIN CORRUGATED DOUBLER CRACKED IN AREA NEAR RIB AT STN36.9.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2002101600037	20021016	00037	SO  	2002	10	16	AUS20020998      	1	20020906	G	5712	3821800	RIB             	            	            	PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING, RIB/BULKHE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH WING RIB CRACKED ALONG RIVET LINE IN THREE PLACES.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2002101600038	20021016	00038	NM  	2002	10	16	AUS20021001      	1	20020906	G	3230	60B0023813	FUSE            	            	            	BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  	 		            		LANDING GEAR RET	FAILED          	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 				3092051					(AUS) RH MAIN LANDING GEAR UP' HYDRAULIC FUSE FAILED. FUSE MAIN RESET  SPRING BROKEN.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2002101600039	20021016	00039	NM  	2002	10	16	AUS20021002      	1	20020906	G	2910	272T3100411	PIPE            	            	            	BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  	 		            		HYDRAULIC SYSTEM	CRACKED         	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 	 									(AUS) LH HYDRAULIC SYSTEM HYDRAULIC PIPE TO HEAT EXCHANGER LOCATEDUNDER THE SAILBAOT FAIRING CRACKED. LOSS OF LH HYDRAUL	IC SYSTEM FLUID. LH HYDRAULIC CASE DRAIN FILTER CONTAMINATED.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2002101600040	20021016	00040	EA  	2002	10	16	AUS20021005      	2	20020726	G	8520	UK	BEARING         	LYC         	IO360A1A    	MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE OIL FILTERS CONTAMINATED WITH METAL. SUSPECT CAUSED BY FAILURE OF EITHER MAIN BEARING OR BIGEND BEARING.						1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P920	 
2002101600041	20021016	00041	CE  	2002	10	16	AUS20021008      	1	20020830	G	5342	12310122	FITTING         	            	            	CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUSELAGE, STABIL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FORWARD FIN ATTACHMENT FITTING CRACKED IN AREA ADJACENT TO THE LH BOLT HOLE. FOUND DURING INSPECTION IAW AD/C206/7	A4.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002101600042	20021016	00042	SO  	2002	10	16	AUS20021009      	2	20020801	G	7414	103493505	MAGNETO         	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MAGNETO/DISTRIBU	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) IMPULSE COUPLINGS WORN ON BOTH MAGNETOS.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002101800080	20021018	00080	NM  	2002	10	18	AUS20021012      	1	20020909	G	2722	3790011107	ACTUATOR        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RUDDER	LEAKING         	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 					0347					(AUS) RUDDER RATIO CHANGER ACTUATOR LEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002101600043	20021016	00043	NM  	2002	10	16	AUS20021013      	1	20020822	G	5230	6546921225	BEAM            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		CARGO/BAGGAGE DO	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				002415					(AUS) FORWARD CARGO DOOR LOWER CROSS BEAM CRACKED ON THE FORWARD SIDE.CRACK STARTS AT THE EDGE OF THE CROSS BEAM AND RUN	S INTO A RIVETHOLE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101600044	20021016	00044	EU  	2002	10	16	AUS20021014      	1	20020910	G	7110		SCREW           	LYC         	IO540K1B5   	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE COWLING S	MISSING         	W			    	K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			CL	CLIMB          	1			AU	S 	 									(AUS) LH ENGINE COWL SCREW MISSING. SCREW IS LOCATED ON THE FORWARD INBOARD SIDE OF THE LH COWL.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002101600045	20021016	00045	NM  	2002	10	16	AUS20021015      	1	20020820	G	2897		HARNESS         	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUEL WIRING	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO2 FUEL TANK ELECTRICAL HARNESS CHAFING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101800081	20021018	00081	GL  	2002	10	18	AUS20021016      	3	20020814	G	6114	D2483	HUB             			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			702  							(AUS) PROPELLER HUB DAMAGED IN AREA OF PRELOAD PLATE SHELF. SUSPECT PROPELLER HAD SUFFERED A GROUND STRIKE AND THE DAMAG	ED AREA HAD BEEN REMOVED BY WHAT APPEARS TO BE SCRAPING. UNAPPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2002101800082	20021018	00082	GL  	2002	10	18	AUS20021017      	3	20020814	G	6114	D2483	HUB             			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			702  							(AUS) PROPELLER HUB DAMAGED IN AREA OF PRELOAD PLATE SHELF. SUSPECT PROPELLER HAD SUFFERED A GROUND STRIKE AND THE DAMAG	ED AREA HAD BEEN REMOVED BY WHAT APPEARS TO BE SCRAPING. UNAPPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2002101600046	20021016	00046	EA  	2002	10	16	AUS20021018      	2	20020906	G	8520	13F17785	CRANKSHAFT      	LYC         	TIO540S1AD  	PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1635 		L537461A					(AUS) CRANKSHAFT CRACKED IN FORWARD RADIUS OF NO4 MAIN BEARING JOURNAL. FOUND DURING MAGNETIC PARTICLE INSPECTION. ENGIN	E HAD A BULKSTRIP CARRIED OUT AT 86.2 HOURS DUE TO PROPELLER STRIKE.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P33EA	 
2002101600047	20021016	00047	SO  	2002	10	16	AUS20021019      	1	20020902	G	5711	2355100	SPAR CAP        	            	            	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320C1A    	41508	EA  	HARTZL	HCC2Y	BHCC2YF1    	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		5926 							(AUS) LH AND RH WING LOWER FORWARD SPAR CAPS CONTAINED SEVERE EXFOLIATION CORROSION IN AREA LOCATED AT WS 62 DUE TO ENGI	NEEXHAUST GASSES. AT LEAST 10% OF THE SPAR CAP MATERIAL IS AFFECTED BUT CAN ONLY BE SEEN WITH THE FUEL TANK BAYS REMOVED	.				1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P920	 
2002101600048	20021016	00048	SO  	2002	10	16	AUS20021020      	1	20020601	G	5243	120007993002	DOOR            	EMB         	EMB120      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	HYDRAULIC COMPAR	SEPARATED       	W			    	K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 	 		22271		120056					(AUS) RH HYDRAULIC BAY ACCESS DOOR MISSING. DOOR HAD OPENED IN FLIGHT AND HAD TORN AWAY FROM PIANO HINGE.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2002101600049	20021016	00049	NM  	2002	10	16	AUS20021025      	1	20020525	G	5712		RIB             	            	            	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		WING, RIB/BULKHE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		61831							(AUS) RH WING UPPER SKIN SUPPORT RIB CORRODED UNDER P' CLAMP LOCATED AT OUTBOARD END OF NO6 LEADING EDGE FLAP - ZONE 64 	STN WS 330.5.  FOUND DURING CPCP INSPECTION.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002101600050	20021016	00050	NM  	2002	10	16	AUS20021026      	1	20020606	G	5720		FITTING         	            	            	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		WING, MISCELLANE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		61831							(AUS) WIRING LOOM STANDOFF CORRODED. STANDOFF IS LOCATED IN RH WING LEADING EDGE ZONE 64 STN 286.897. FOUND DURING CPCP 	INSPECTION.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002101600051	20021016	00051	NM  	2002	10	16	AUS20021027      	1	20020606	G	5720		SUPPORT         	            	            	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		WING, MISCELLANE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		61831							(AUS) WIRING LOOM CLAMPS CORRODED. CLAMPS AT LOCATED AT UPPER SKINSUPPORT RIBS - ZONE 64 STN 244.217, STN 270.217, STN 2	98.497 ANDSTN 284.0. FOUND DURING CPCP INSPECTION.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002101600052	20021016	00052	NM  	2002	10	16	AUS20021028      	1	20020606	G	5713		STRINGER        	            	            	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		WING, LONGERON/S	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		61831							(AUS) UPPER WING STRINGERS CORRODED. STRINGERS ARE THE SECOND AND THIRD STRINGERS FROM LEADING EDGE LOCATED OUTBOARD OF 	STN 210.217.FOUND DURING CPCP INSPECTION.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002101600053	20021016	00053	NM  	2002	10	16	AUS20021029      	1	20020521	G	5751	65217271	HINGE           	            	            	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		AILERONS	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		61831							(AUS) RH OUTBOARD AILERON ATTACHMENT HINGE CORRODED. CORROSION IS LOCATED AT ZONE 88 WBL 492.0. FOUND DURING CPCP INSPEC	TION.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002101600054	20021016	00054		2002	10	16	AUS20021031      	4	20020911	G	2565	7A1323113	SLIDE           	            	            	      		            			      		            			 		            		ESCAPE SLIDE	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				GS1508					(AUS) ESCAPE SLIDE PACKING STRIP NOT REMOVED FOLLOWING OVERHAUL.PERSONNEL/MAINTENANCE ERROR.																			 
2002101600055	20021016	00055	CE  	2002	10	16	AUS20021032      	1	20020911	G	3260	35361133	BRACKET         	            	            	BEECH 	35    	V35A        	1151544	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	LANDING GEAR POS	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR STRUT SQUAT SWITCH ATTACHMENT BRACKETCORRODED THROUGH.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2002101600056	20021016	00056	NM  	2002	10	16	AUS20021033      	1	20020517	G	5751	65137463	HINGE           	            	            	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		AILERONS	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		61831							(AUS) OUTBOARD AILERON INPUT ROD ATTACHMENT FITTING CORRODED. AILERON UPPER SKIN CRACKED AND LOWER SKIN CORRODED. LOCATE	D IN ZONE 81WBL 492.0. FOUND DURING CPCP INSPECTION.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002101600057	20021016	00057	NM  	2002	10	16	AUS20021034      	1	20020521	G	5754	651626519	HINGE           	            	            	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		LEADING EDGE DEV	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		61831							(AUS) LEADING EDGE FLAP LH HINGE FITTING CONTAINED SEVERE EXFOLIATION CORROSION AROUND BUSH. FOUND DURING CPCP INSPECTIO	N.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002101600058	20021016	00058	CE  	2002	10	16	AUS20021036      	1	20020908	G	3233	12810061	ACTUATOR        	            	            	CESSNA	210   	210K        	2073446	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LANDING GEAR ACT	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 		1367 							(AUS) LH MAIN LANDING GEAR COULD NOT BE EXTENDED.  THE FAULT WAS TRACED TO A BROKEN ACTUATOR PISTON/RACK. BREAK OCCURRED	 IN THE RACK AREA TWO TEETH IN FROM THE END AND ORIGINATING AT THE BASE OF THESECOND TOOTH. THE CRACK FACE SHOWS EVIDENC	E OF BEACH MARKS'  INDICATING A FATIGUE FAILURE. SMOKE WAS ALSO REPORTED IN THE  COCKPIT PRIOR TO LANDING FOLLOWING ATTE	MPTS TO EXTEND GEAR. REASON STILL TO BE ESTABLISHED.			1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002101600059	20021016	00059	NE  	2002	10	16	AUS20021038      	1	20020910	G	3231	1945E81	SWIVEL          	            	            	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  	 		            		LANDING GEAR DOO	FRACTURED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH UNDERCARRIAGE DOOR LINK SWIVEL BROKEN. INVESTIGATION FOUND THAT THERE WAS AN INDICATION OF A PRE-EXISTING CRACK	 IN THE RADIUS THROUGH APPROXIMATELY ONE THIRD OF THE DIAMETER.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002101600060	20021016	00060	SW  	2002	10	16	AUS20021040      	1	20020907	G	5302	206031314037	LONGERON        	            	            	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  	 		            		ROTORCRAFT TAIL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TAIL BOOM LONGERON CRACKED AROUND TWO RIVET HOLES.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002101800099	20021018	00099	NM  	2002	10	18	AUS20021045      	1	20020916	G	5730	65C25204	SKIN            			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM563B1US  	 	GL  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2632 							(AUS) RT WING UPPER SURFACE CORRODED IN AREA LOCATED FORWARD OF THE FILLER CAP AT APPROXIMATELY WING STN 440. AN AREA OF	 6.35MM (0.250IN) BY 25.4MM (1IN) WAS REMOVED AT THE FORWARD EDGE OF THE FILLER CAP HOUSING.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2002101600061	20021016	00061	NM  	2002	10	16	AUS20021046      	1	20020906	G	5753		BOLT            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TRAILING EDGE FL	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH INBOARD FLAP ELEPHANT MOUNTING PLATE BOLTS/ANCHOR NUTS FAILED. DURING FLAP RETRACTION AFTER TAKEOFF, THE ELEPHA	NT EAR DAMAGEDTHE WING/BODY FAIRING CAUSING A 304.8CM (12IN) CRACK IN THE COMPOSITE MATERIAL.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101600062	20021016	00062	SO  	2002	10	16	AUS20021047      	1	20020905	G	3230	6703102	FITTING         	            	            	PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LANDING GEAR RET	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR FITTING BROKE INTO FOUR PIECES DURING FLIGHT AND LANDING GEAR FELL FREE BUT DID NOT LOCK. DUR	ING INVESTIGATION THE SAME PART WAS REMOVED FROM THE RH MAIN LANDINGGEAR (PNO 67031-03) AND WAS ALSO FOUND TO BE BADLY C	RACKED.				1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920	 
2002101600063	20021016	00063	NE  	2002	10	16	AUS20021048      	2	20020918	G	7260	LP5	FITTING         	PWA         	JT8D17      	BOEING	727   	727281      	138408N	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		TURBINE ENGINE A	LOOSE           	W			    	K	 	 	 	NONE                    				J	E	K	WARNING INDICATION        	VIBRATION/BUFFET          	FLUID LOSS                	DE	DESCENT        	1			AU	S 	 		40981							(AUS) NO2 ENGINE OIL QUANTITY INDICATION DROPPED FROM 7.6 LITRES (2GAL) TO 3.8 LITRES (1GAL) DURING APPROACH TO LAND. IN	VESTIGATION FOUND THAT THE AUXILIARY GEARBOX LP5 FITTING THREAD WAS DAMAGED AND LOOSE. PERSONNEL/MAINTENANCE ERROR.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002101600064	20021016	00064	NM  	2002	10	16	AUS20021049      	1	20020903	G	5753	654643814	FLAP TRACK      	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TRAILING EDGE FL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				2406					(AUS) NO5 FLAP TRACK BEAM CRACKED ON THE AFT LOWER FLANGE. CRACK LENGTH APPROXIMATELY 38MM (1.5IN).						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101600065	20021016	00065	SO  	2002	10	16	AUS20021050      	1	20020916	G	5751	315359	DOUBLER         	PIPER       	4020023     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	AILERONS	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				315359					(AUS) RH AILERON SPAR DOUBLER CRACKED IN AREA LOCATED IMMEDIATELY BELOW THE INBOARD HINGE ATTACHMENT PLATE LOWER BOLT HO	LE. CRACK LENGTH18MM (0.71IN). FOUND DURING DYE PENETRANT INSPECTION IAWAD/PA31/118 AMDT 1.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002101800101	20021018	00101	EA  	2002	10	18	AUS20021051      	2	20020708	G	8520	L89154A	CONNECTING ROD  			PAC   	CT4   	CT4A        	05623UC	GL  	LYC   	O720  	IO720A1B    	41546	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 										(AUS) DURING AGRICULTURE OPERATIONS (SPREADING SUPER) THE PILOT ENCOUNTERED EXCESSIVE ENGINE VIBRATION AND A POSSIBLE OV	ERSPEED (WAS UNABLE TO READ GAUGES). ENGINE WAS SHUT DOWN AND A FORCED LANDING CARRIED OUT. INITIAL INVESTIGATION FOUND 	THAT NR 4 OR NR 6  CONNECTING ROD ON THE LT SIDE OF ENGINE HAD PUNCTURED THROUGH THE CRANKCASE.				1	Q	7	1 	3I	3	O	RT	A9PC    	1E15				 
2002101600066	20021016	00066	EA  	2002	10	16	AUS20021053      	2	20020918	G	8520	72469	CRANKSHAFT      	LYC         	VO435B1A    	BELL  	47    	47G5A       	1181034	SW  	LYC   	O435  	VO435B1A    	41516	EA  	 		            		RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1050 							(AUS) CRANKSHAFT CRACKED. CRACK RAN THROUGH THE OIL GALLERY, ACROSS THE THRUST FACE AND THROUGH THE OPPOSITE OIL GALLERY	. CRACK EXTENDS THROUGH ALMOST 60% OF THE CIRCUMFERENCE OF BEARING JOURNALSURFACE.					1	G	7	1 	3O	3	O	 	2H3     	E279				 
2002101600067	20021016	00067	EU  	2002	10	16	AUS20021056      	2	20020828	G	7250	725545	TURBINE         	GE          	CFM563C1    	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TURBINE SECTION	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 	 				725545					(AUS) NO1 ENGINE SURGED/STALLED ON TAKEOFF. EGT INCREASED AND EXCEEDEDLIMITS. ENGINE INSPECTION FOUND TURBINE FAILURE.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101600068	20021016	00068	NM  	2002	10	16	AUS20021057      	1	20020916	G	2421		GENERATOR       	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		AC GENERATOR-ALT	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 	 									(AUS) APU GENERATOR FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101600069	20021016	00069	EU  	2002	10	16	AUS20021058      	1	20020917	G	5540	603300002	RUDDER          	            	            	REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	RUDDER STRUCTURE	FOD             	W			    	K	 	 	 	NONE                    				C	 	 	F.O.D.                    			TX	TAXI/GRND HDL  	1			AU	S 	 		6881 							(AUS) RUDDER DAMAGED BY ANOTHER AIRCRAFT TAXIING PAST. THE RUDDER SKINWAS DENTED AND BUCKLED AT THE MID POINT OF THE TRA	ILING EDGE. DURING DISASSEMBLY FOR REPAIR A PORTION OF THE RIB WAS ALSO DAMAGED.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2002101600070	20021016	00070	SO  	2002	10	16	AUS20021059      	2	20020918	G	8530	530348	PISTON          	CONT        	O200A       	CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 		1608 		66186					(AUS) PISTON SIDE BROKEN AWAY. METAL CONTAMINATION OF OIL FILTER.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2002101600071	20021016	00071	NM  	2002	10	16	AUS20021061      	1	20020921	G	5280	113T820175SP	DOOR            	MENASCO     	161T0000665 	BOEING	767   	76733A      	1385209	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		LANDING GEAR DOO	SEPARATED       	W			    	K	 	 	 	NONE                    				O	D	 	OTHER                     	INFLIGHT SEPARATION       		LD	LANDING        	1			AU	S 	 				T8189					(AUS) LH MAIN LANDING GEAR TRUNNION DOORS MISSING. DAMAGE CAUSED TO BRAKE AND LANDING GEAR HYDRAULIC LINES. LH HORIZONTA	L STABILISERHAD MINOR IMPACT DAMAGE TO THE LEADING EDGE.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2002101600072	20021016	00072	EA  	2002	10	16	AUS20021062      	2	20020913	G	8550		PLUG            	LYC         	TIO540A2B   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	RECIPROCATING EN	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE OIL PRESSURE DROPPING INTERMITTENTLY. INTERNAL INSPECTIONFOUND THE INTERNAL SUMP OIL PICKUP GALLERY PLUG MI	SSING. SUSPECTTHE PLUG WAS NOT INSTALLED DURING ENGINE OVERHAUL.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2002101600073	20021016	00073	EA  	2002	10	16	AUS20021063      	2	20020924	G	8520	L224361	CRANKCASE       	LYC         	TIO540A2B   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				L224361					(AUS) ENGINE CRANKCASE CRACKED ON LH SIDE ADJACENT TO THE FRONT CYLINDER. THIS DEFECT IS LINKED WITH MDR 02/1062 (MISSIN	G OIL PLUG).					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2002101800157	20021018	00157	GL  	2002	10	18	AUS20021066      	2	20020923	G	7200		ENGINE          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LEFT	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE PRODUCING LOW POWER.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002101600074	20021016	00074	NE  	2002	10	16	AUS20021067      	2	20020912	G	7310	82821013103	TUBE            	PWA         	PW123D      	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE FUEL DIST	LOOSE           	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ENGINE WASTE FUEL DRAIN TUBE DISCONNECTED FROM ENGINE FUEL NOZZLE MANIFOLD. INVESTIGATION FOUND THAT THE WASTE 	FUEL DRAINTUBE HAD BEEN DISCONNECTED THE PREVIOUS NIGHT AS PART OF THEPROCESS USED IN CARRYING OUT A COMPRESSOR WASH ON 	THE ENGINE. FOLLOWING THE COMPRESSOR WASH THE MAINTENANCE PERSONNEL FAILED TO RECONNECT THE LINE. PERSONNEL/MAINTENANCE 	ERROR.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002101600075	20021016	00075	EA  	2002	10	16	AUS20021068      	2	20020309	G	7322	252416315	FCU             	BENDIX      	RSA10ED1    	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	FUEL CONTROL/REC	OUT OF ADJUST   	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 	 		25   		2593524T					(AUS) ENGINE FUEL CONTROL UNIT OUT OF ADJUSTMENT.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2002102100003	20021021	00003	CE  	2002	10	21	AUS20021070      	1	20020911	G	5312	07126161	BULKHEAD        			CESSNA	182   	182F        	2072714	CE  						HARTZL	HC82X	HC82XF1     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR BULKHEAD LOCATED AT STA 309.187 CRACKED.						1	H	7	1 	3O			NT	3A13    		5	C	P878	 
2002102100004	20021021	00004	CE  	2002	10	21	AUS20021071      	1	20020920	G	5347	07106582	SEAT TRACK      			CESSNA	182   	182F        	2072714	CE  						HARTZL	HC82X	HC82XF1     	GL  	CABIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FRONT SEAT OUTBOARD SEAT TRACK CONTAINED NUMEROUS CRACKS.						1	H	7	1 	3O			NT	3A13    		5	C	P878	 
2002102100024	20021021	00024	CE  	2002	10	21	AUS20021072      	2	20020910	G	8550		FILTER          			AMTR  	VANS  	RV8         	       	GL  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENGINE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE SUMP FITTED WITH NO SUCTION FILTER IN THE OIL SYSTEM. APIECE OF LOCKWIRE APPROXIMATELY 15.875MM (0.625IN) L	ONG WAS FOUND IN AN OIL GALLERY. DAMAGE TO OIL PUMP, CRANKSHAFT REAR BEARINGAND THRUST BEARING SURFACES. ALL PISTON SKIR	TS SEVERELY SCORED.				1	L	7	1 	3O	3	O	NT	EXPA1L71	E1CE	5	C	P27EA	 
2002102100027	20021021	00027	CE  	2002	10	21	AUS20021073      	2	20020910	G	8550		FILTER          			AMTR  	VANS  	RV8         	       	GL  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENGINE	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) UNAPPROVED OIL FILTER INSTALLED.  PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.						1	L	7	1 	3O	3	O	NT	EXPA1L71	E1CE	5	C	P27EA	 
2002101600076	20021016	00076		2002	10	16	AUS20021074      	4	20020919	G	3417	HG480B43	ADC             	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		AIR DATA COMPUTE	FAILED          	W			    	K	 	 	 	NONE                    				I	G	 	FLT. ATTITUDE INST.       	MULTIPLE FAILURE          		CR	CRUISE         	1			AU	S 	 				H115742					(AUS) AIR DATA COMPUTER FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002101600077	20021016	00077	CE  	2002	10	16	AUS20021075      	1	20020815	G	3242	RFS1030	ROTOR           	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	BRAKE	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH INNER BRAKE ROTOR BROKEN INTO THREE PIECES.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2002101600078	20021016	00078	NE  	2002	10	16	AUS20021076      	2	20020911	G	7230	410100639	ROTOR           	GARRTT      	410102080   	BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  	 		            		TURBINE ENGINE C	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				86760A					(AUS) NO2 ENGINE COMPRESSOR AXIAL ROTOR DAMAGED BEYOND LIMITS. SUSPECTCAUSED BY FOD.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2002102100028	20021021	00028	SO  	2002	10	21	AUS20021077      	2	20020915	G	8550		OIL SYSTEM      			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	ENGINE	LOW             	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) ENGINE OIL QUANTITY LOW. ENGINE HAS A HISTORY OF HIGH OIL CONSUMPTION.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2002110600092	20021106	00092	NM  	2002	11	6	AUS20021079      	1	20020924	G	2840		LIGHT           	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUEL INDICATING	                	W			    	K	 	 	 	NONE                    				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 	 									(AUS) LH AND RH AUXILIARY FUEL TRANSFER LIGHTS ILLUMINATED. RH LIGHTTHEN EXTINGUISHED LEAVING THE LH LIGHT STILL ILLUMIN	ATED. THE RHLIGHT ILLUMINATED AGAIN LATER.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002110600093	20021106	00093	NM  	2002	11	6	AUS20021087      	1	20021002	G	3240	82920010335	PIPE            	            	            	DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF15      	NE  	LANDING GEAR BRA	LEAKING         	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 	 									(AUS) BRAKE ACCUMULATOR HYDRAULIC PRESSURE LINE LEAKING AT FLARE. SUSPECT CAUSED BY CORROSION PITTING OF THE FLARE. LOSS	 OF NO2 HYDRAULIC SYSTEM FLUID.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002110800014	20021108	00014	NM  	2002	11	8	AUS20021094      	1	20021004	G	2822	5006150A	VALVE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUEL BOOST PUMP	CONTAMINATED    	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LT FORWARD BOOST PUMP DISCHARGE CHECK VALVE CONTAMINATED BY DEBRIS.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2002110800015	20021108	00015	EA  	2002	11	8	AUS20021095      	2	20021008	G	8530	05K21232	CYLINDER        			GROB  	G115  	G115        	       	EU  	LYC   	O235  	O235H2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	SEPARATED       	W				O				OTHER                   				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	LD	LANDING        	1			AU	S 										(AUS) NR 1 CYLINDER SEPARATED. THE CYLINDER BASE FLANGE WAS STILL CONNECTED TO THE CRANKCASE.						1	L	7	1 	3O	3	O	NT	A57EU   	E223	5	N	P9045	 
2002110600094	20021106	00094	SW  	2002	11	6	AUS20021096      	1	20020927	G	6320	70061L275W210A	HOSE            	            	            	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  	 		            		MAIN ROTOR GEARB	WORN            	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 	 									(AUS) TRANSMISSION OIL HOSE HOLED AND LEAKING. HOSE WAS CHAFING ON AN ADJACENT PIPE. TRANSMISSION OIL LOST OVERBOARD.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002110800017	20021108	00017	GL  	2002	11	8	AUS20021098      	3	20021003	G	6111		BLADE           			AMTR  	VANS  	RV8         	       	GL  	LYC   	O360  	AEIO360*    	 	EA  	AMTR	C8289	C8289       	GL  	PROPELLER	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER LEADING EDGE DELAMINATING IN AREA OF TIP.						1	L	7	1 	3O	3	O	NT	EXPA1L71	1E10	5	N	EXPP5N	 
2002110800018	20021108	00018	SO  	2002	11	8	AUS20021099      	1	20020930	G	5753		STRUCTURE       			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540H2A5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT TRAILING EDGE FLAPS SEVERELY CORRODED AT HINGE ATTACHMENT TO MAIN SPAR.						1	L	7	1 	3O	3	O	 	2A10    	E295	5	N	P874	 
2002110600095	20021106	00095	SO  	2002	11	6	AUS20021102      	1	20020927	G	3230	9515340	TUBE            	            	            	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR UP' HYDRAULIC PIPE CORRODED.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002110600096	20021106	00096	SO  	2002	11	6	AUS20021103      	1	20020927	G	3230	9515339	TUBE            	            	            	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR DOWN' PIPE CORRODED.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002110600097	20021106	00097	SO  	2002	11	6	AUS20021104      	1	20020909	G	3230	9515339	TUBE            	            	            	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR DOWN' HYDRAULIC PIPE CORRODED.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002110600098	20021106	00098	SO  	2002	11	6	AUS20021105      	1	20020909	G	3230	9515340	TUBE            	            	            	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR UP' HYDRAULIC PIPE CORRODED.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002110600099	20021106	00099	NE  	2002	11	6	AUS20021108      	2	20021004	G	7321	8061965	FMU             	RROYCE      	BR700715A130	BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  	 		            		FUEL CONTROL/TUR	FAULTY          	W			    	K	E	 	 	NONE                    	ENGINE SHUTDOWN         			E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 									(AUS) LH ENGINE SPOOLED DOWN. FUEL METERING UNIT (FMU) PNO 18061-965AND ENGINE ELECTRONIC CONTROL (EEC) PNO 114E6112G119	 CHANGED ON ADVICE FROM MANUFACTURERS.					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2002111200004	20021112	00004	EU  	2002	11	12	AUS20021109      	1	20021007	G	3320		BALLAST         			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					GALLEY	BURNED OUT      	W				D				RETURN TO BLOCK         				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) REAR GALLEY WORK LIGHT BALLAST BURNED OUT.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2002110600100	20021106	00100	SO  	2002	11	6	AUS20021112      	2	20020522	G	8520	6419311075	BOLT            	CONT        	IO520M      	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		80   							(AUS) NO6 CYLINDER UPPER THROUGH BOLT FAILED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002110600101	20021106	00101	SW  	2002	11	6	AUS20021113      	1	20020925	G	3260		WARNING SYSTEM  	            	            	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LANDING GEAR POS	FAULTY          	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 	 									(AUS) LANDING GEAR INDICATIONS INCORRECT. GROUND RETRACTION TESTS COULD NOT DUPLICATE THE DEFECT.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2002110600102	20021106	00102	EU  	2002	11	6	AUS20021114      	1	20020914	G	7603	6227911301	SERVO           	RROYCE      	TAY62015    	FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  	 		            		POWER LEVER	STICKING        	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 	 				595					(AUS) LH AUTO THROTTLE SERVO BINDING.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2002110600103	20021106	00103	EA  	2002	11	6	AUS20021115      	1	20020917	G	5310	C2FS533	FORMER          	            	            	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	FUSELAGE MAIN, S	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) REAR FUSELAGE FORMER AND SKIN STRUCTURE LOCATED IN AREA BENEATH THE FORWARD TAILPLANE ATTACHMENT PICKUP BRACKETS P	NO C2FS5189ASEVERELY CORRODED. AIRCRAFT OPERATES AS A FLOATPLANE.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2002110600104	20021106	00104	EA  	2002	11	6	AUS20021116      	2	20021009	G	7414	ES10382585	CONTACTOR       	CONT        	103993101   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MAGNETO/DISTRIBU	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 				RAE2053					(AUS) MAGNETO CAM FOLLOWER SEPARATED FROM CONTACT ASSEMBLY.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002110600105	20021106	00105	SO  	2002	11	6	AUS20021119      	2	20020929	G	7314	64621218	PUMP            	CONT        	64621218    	BEECH 	35    	V35A        	1151544	CE  	CONT  	O550  	IO550B      	 	SO  	MCAULY	3A32C	3A32C76     	GL  	ENGINE FUEL PUMP	LEAKING         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 				L019915B					(AUS) ENGINE DRIVEN FUEL PUMP LEAKING. SUSPECT FAULTY SHAFT SEAL.						1	L	7	1 	3O	3	O	 	3A15    	E3SO	5	C	P21EA	 
2002110600106	20021106	00106	NM  	2002	11	6	AUS20021121      	1	20021006	G	7603	3200940010	SENSOR          	GE          	CFM563C     	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		POWER LEVER	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 				12207					(AUS) ENGINE AUTOTHROTTLE SENSOR SUSPECT FAULTY. LIMITED INFORMATIONPROVIDED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002110600107	20021106	00107	CE  	2002	11	6	AUS20021122      	1	20020901	G	3230	3581512512	ROD             	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR RETRACTION ROD FAULTY. ROD HAD BEENILLEGALLY REPAIRED IN AN ATTEMPT TO STRAIGHTEN THE ROD. RI	VETSHAD BEEN REPLACED WITH BOLTS AND PENNY WASHERS. UNAPPROVEDREPAIR. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600108	20021106	00108	CE  	2002	11	6	AUS20021123      	1	20020901	G	5712	95110233	RIB             	BEECH       	95110234    	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	WING, RIB/BULKHE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING RIB PNO 9511023-3 AND RH WING RIB PNO 9511023-4 CORRODEDTHROUGH. LH WING RIB CHANNEL PNO 9511023-5 AND RH 	WING RIBCHANNEL PNO 9511023-6 CORRODED THROUGH. RIBS AND CHANNELS ARE LOCATED AT STN 66.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600109	20021106	00109	CE  	2002	11	6	AUS20021125      	1	20020901	G	2711	135038	ROD END         	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	AILERON TAB CONT	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AILERON TRIM TAB RODEND FORK RUSTY AND CLEVIS PIN SEIZED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600110	20021106	00110	CE  	2002	11	6	AUS20021126      	1	20020901	G	5341		FITTING         	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	FUSELAGE, WING A	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING ATTACHMENT TOP BATHTUB FITTINGS CORRODED AND DRAIN HOLES BLOCKED. NO CORROSION PROTECTION ON FITTINGS.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600111	20021106	00111	CE  	2002	11	6	AUS20021127      	1	20020901	G	5320		DOUBLER         	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	FUSELAGE, MISCEL	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH FUSELAGE DOUBLERS LOCATED AT STN 0.00 CONTAINED EXFOLIATION CORROSION. ADJACENT RIB PNO 95-410005-4 CORR	ODEDAWAY. AIRCRAFT HAS OPERATED IN A SALT AIR ENVIRONMENT FOR A CONSIDERABLE TIME.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600112	20021106	00112	CE  	2002	11	6	AUS20021129      	1	20020901	G	2720		BEARING         	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	RUDDER CONTROL S	SEIZED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RUDDER BEARINGS UNSERVICEABLE. TOP BEARING SEIZED WITH A GROOVE WORN IN THE ATTACHMENT PIVOT BOLT. CENTRE BEARING 	WORN. LOWER BEARING PARTIALLY SEIZED.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600113	20021106	00113	CE  	2002	11	6	AUS20021130      	1	20020901	G	3230		CABLE           	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH MAIN LANDING GEAR UPLOCK CABLES RUSTY. UPLOCK SPRINGS BROKEN AND RUSTY. CLOSING PANELS IN WHEEL WELL BAY	S MISSING ALLOWING DIRT AND MUD ETC TO BUILD UP.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600114	20021106	00114	CE  	2002	11	6	AUS20021131      	1	20020901	G	5313		STRINGER        	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	FUSELAGE MAIN, L	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUSELAGE STRINGER LOCATED AT STN 107.00 CONTAINED SEVEREEXFOLIATION CORROSION. EVIDENCE OF WATER ENTRY OVER AN EXT	ENDED PERIOD.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600115	20021106	00115	CE  	2002	11	6	AUS20021132      	1	20020901	G	5314	96410032601	KEEL            	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	FUSELAGE MAIN, K	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH KEEL SPLICE JOINTS LOCATED IN NOSE LANDING GEAR WHEEL WELL AT STN 49.000 CONTAINED SEVERE EXFOLIATION CO	RROSION BETWEEN THE JOINT FACES. ATTACHMENT RIVET HEADS MISSING. AFFECTED PARTS WERE:-1. LH FORWARD KEEL PNO 96-410032-6	012. LH AFT KEEL PNO 96410032-133. RH FORWARD KEEL PNO 96-410032-6084. RH AFT KEEL PNO 96410032-608				1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600116	20021106	00116	CE  	2002	11	6	AUS20021133      	1	20020901	G	5712		RIB             	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	WING, RIB/BULKHE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH WING TRAILING EDGE RIBS CORRODED. RIBS AFFECTED ARE:- LH WING-PNO 95110014-121PNO 95110014-191PNO 951100	14-153PNO 95110014-129PNO 95110014-135RH WING-PNO 95110014-122PNO 95110014-192PNO 95110014-154PNO 95110014-130PNO 951100	14-120				1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600117	20021106	00117	CE  	2002	11	6	AUS20021135      	1	20020901	G	3260	35361145	LINK            	            	            	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	LANDING GEAR POS	SEIZED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) SQUAT SWITCH LINKS SEIZED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600118	20021106	00118	EU  	2002	11	6	AUS20021139      	2	20021009	G	7270		PANEL           	GE          	CFM563C     	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TURBINE ENGINE B	DAMAGED         	W			    	K	 	 	 	NONE                    				E	C	 	VIBRATION/BUFFET          	F.O.D.                    		TO	TAKEOFF        	1			AU	S 	 									(AUS) RH ENGINE BIRDSTRIKE. INVESTIGATION FOUND ENGINE NACELLE FAN DUCT EXTENSION UPPER ACOUSTIC PANEL MISSING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002110600119	20021106	00119	EU  	2002	11	6	AUS20021140      	2	20021008	G	7530	1211175010	ACTUATOR        	GE          	CFM563C     	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		COMPRESSOR BLEED	LEAKING         	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 	 				APHAL389					(AUS) NO2 ENGINE RH VARIABLE STATOR VANE ACTUATOR LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002110600120	20021106	00120	SO  	2002	11	6	AUS20021144      	2	20020910	G	8530	654840C	PISTON          	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIPROCATING EN	DAMAGED         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 				239168R					(AUS) LH ENGINE NO2 CYLINDER PISTON DAMAGED. SUSPECT CAUSED BYDETONATION.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002111200018	20021112	00018	SO  	2002	11	12	AUS20021145      	1	20021009	G	5711	6205400	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  	SNSNCH	74DM	M74DM       	EA  	LT & RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT AFT SPAR ASSEMBLIES CORRODED BETWEEN SPAR AND ATTACHMENT PLATE PNO 66762-00.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002110600121	20021106	00121	EA  	2002	11	6	AUS20021146      	1	20021009	G	5311	C2FS537A	CHANNEL         	            	            	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	FUSELAGE MAIN, F	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH CHANNELS SEVERELY CORRODED. AIRCRAFT OPERATES AS AFLOATPLANE.						1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2002110600122	20021106	00122	CE  	2002	11	6	AUS20021150      	1	20021004	G	7331	660526	TRANSDUCER      	PWA         	PT6A41      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL FLOW INDICA	LEAKING         	W			    	K	 	 	 	NONE                    				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	TO	TAKEOFF        	1			AU	S 	 				1399					(AUS) RH ENGINE FUEL FLOW TRANSDUCER OUTLET FITTING LOOSE AND LEAKING FUEL. TRANSDUCER IS MANUFACTURED BY SHADIN.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2002111200022	20021112	00022	EU  	2002	11	12	AUS20021151      	1	20021014	G	7714	230362601	PICKUP          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE RPM	FAULTY          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) NO4 ENGINE N2 PICKUP FAULTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2002110600123	20021106	00123	EU  	2002	11	6	AUS20021153      	1	20021011	G	2710	NB45B349	SLEEVE          	            	            	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERON CONTROL	SPLIT           	W			    	K	 	 	 	NONE                    				O	F	 	OTHER                     	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AILERON CONTROL ROD SLEEVE SPLIT THROUGH TAPER PIN HOLE.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002110600124	20021106	00124	EU  	2002	11	6	AUS20021155      	1	20021014	G	2731	SD3456028	CABLE           	            	            	STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	ELEVATOR TAB CON	BROKEN          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 	 									(AUS) ELEVATOR TRIM CABLE BROKEN.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2002111200029	20021112	00029	SO  	2002	11	12	AUS20021159      	2	20021009	G	8550	6320622	DIPSTICK        								CONT  	O520  	IO520F      	17032	SO  					ENGINE OIL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1687 							(AUS) ENGINE SUMP WORN INTERNALLY BY DIPSTICK ROD. DEPTH OF WEAR GROOVE APPROXIMATELY 0.635MM (0.025IN). THICKNESS OF SU	MP SKIN 1.27MM (0.050IN). TWO OTHER SIMILAR DEFECTS FOUND FROM THE SAME OPERATOR. ALL  HAVE BEEN ASSOCIATED WITH LATE MA	NUFACTURE RIVETED DIPSTICKS WITH SUFFIX AW OR BF. SUSPECT DESIGN PROBLEM WITH LATER MODEL DIPSTICKS.									3	O			E5CE				 
2002111200032	20021112	00032	CE  	2002	11	12	AUS20021162      	1	20021015	G	3260	P6340005	SWITCH          			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MLG	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWN SWITCH INTERMITTENT IN OPERATION.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002110600125	20021106	00125	SO  	2002	11	6	AUS20021165      	2	20021007	G	8520	634503	BEARING         	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1214 							(AUS) NO2 MAIN BEARING BROKEN. REMAINING MAIN BEARINGS MOVING SIDEWAYSCAUSING TANGS TO WEAR INTO CASE.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002110600126	20021106	00126	EU  	2002	11	6	AUS20021166      	1	20020913	G	7120		MOUNT           	LYC         	O320D2A     	AVIONS	R2160 	R2160       	0960101	EU  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE MOUNT SEC	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE MOUNT CRACKED IN SEVERAL AREAS. FURTHER INSPECTION FOUND BOTH LOWER ENGINE MOUNT BRACKETS LOCATED BEHIND TH	E FIREWALL ALSO CRACKED. LH AND RH TOP FUSELAGE SKINS REMOVED FOR INSPECTION ANDLH TOP MOUNT STRUCTURE FOUND CRACKED. LH	 RUDDER BAR ATTACHMENTPOINT CRACKED BENEATH ANCHOR NUT.				1	L	7	1 	3O	3	O	RT	A48EU   	E274	5	N	P88614	 
2002110600127	20021106	00127	NE  	2002	11	6	AUS20021171      	2	20021017	G	7421	9550168760	IGNITER         	TMECA       	ARRIEL1B    	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		SPARK PLUG/IGNIT	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				616					(AUS) ENGINE IGNITER BROKEN. BORESCOPE INSPECTION FOUND SEVEREDOWNSTREAM DAMAGE. IGNITER IS MANUFACTURED BY EQYEM.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002110600128	20021106	00128	NE  	2002	11	6	AUS20021180      	2	20021009	G	7421	SC2036	IGNITER         	TMECA       	ARRIEL1B    	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		SPARK PLUG/IGNIT	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				678					(AUS) ENGINE IGNITER ELECTRODE BROKEN OFF.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002110600129	20021106	00129	EU  	2002	11	6	AUS20021181      	1	20021011	G	5552	NB310077	BRACKET         	            	            	BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEVATOR/TAB, AT	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ELEVATOR OUTBOARD HINGE BRACKET WORN AND RIVETS LOOSE. FOUNDDURING INSPECTION IAW AD/BN2/70 AND BN2/SB259.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002110600130	20021106	00130	EU  	2002	11	6	AUS20021187      	1	20021016	G	6120	LW12920	PIPE            	LYC         	O360A1AD    	SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER CONTRO	FRACTURED       	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 	 		64   		L3377336A					(AUS) PROPELLER GOVERNOR EXTERNAL OIL PIPE FAILED AT CONNECTION TO THEGOVERNOR.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2002110600131	20021106	00131	NE  	2002	11	6	AUS20021190      	2	20021014	G	7210	3022383	SEAL            	PWA         	PW118A      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	TURBINE ENGINE R	LEAKING         	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 				115108					(AUS) NO2 ENGINE REDUCTION GEARBOX AUXILIARY GENERATOR OIL SEAL LEAKING. SEAL HAD BEEN CHANGED ON THE PRECEDING DAY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2002110600132	20021106	00132	SO  	2002	11	6	AUS20021192      	1	20021005	G	5412	70382	BULKHEAD        	            	            	PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NACELLE/PYLON, B	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH ENGINE NACELLE BULKHEAD CRACKED.						1	L	7	2 	4T	4	T	 	A23SO   	E4EA	6	C	P15EA	 
2002110600133	20021106	00133	SO  	2002	11	6	AUS20021193      	1	20021005	G	3211	40288006	TRUNNION        	            	            	PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MAIN LANDING GEA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LANDING GEAR TRUNNION CRACKED THROUGH VERTICAL WEB. CRACK LENGTHAPPROXIMATELY 12.7MM (0.5IN). AIRCRAFT OPERATES FR	OM ROUGHSTRIPS.					1	L	7	2 	4T	4	T	 	A23SO   	E4EA	6	C	P15EA	 
2002110600134	20021106	00134	NM  	2002	11	6	AUS20021195      	1	20021018	G	3246	LM522546	BEARING         	BFGOODRICH  	313061M     	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		WHEEL/SKI/FLOAT	DISINTEGRATED   	W			    	K	 	 	 	NONE                    				O	D	 	OTHER                     	INFLIGHT SEPARATION       		LD	LANDING        	1			AU	S 	 				27242941					(AUS) NO2 MAIN WHEEL OUTER BEARING COLLAPSED. WHEEL SEPARATED FROMAIRCRAFT LEAVING THE WHEEL NUT STILL SECURE ON THE AXL	E. DAMAGE TO AXLE SLEEVE.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002110600135	20021106	00135	NM  	2002	11	6	AUS20021197      	1	20021010	G	2750	113T22507	TORQUE TUBE     	            	            	BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  	 		            		TRAILING EDGE FL	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH INBOARD FLAP TORQUE TUBE AND COLLAR FITTING CORRODED BEYONDLIMITS. FOUND DURING INSPECTION IAW AD/B767/108.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2002110600136	20021106	00136	NM  	2002	11	6	AUS20021198      	1	20021011	G	2421		CONNECTOR       	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		AC GENERATOR-ALT	DAMAGED         	W			    	K	 	 	 	NONE                    				O	H	 	OTHER                     	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO1 GENERATOR PLUG AND SOCKET D5124 DAMAGED DUE TO ARCING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002110600137	20021106	00137	SO  	2002	11	6	AUS20021200      	1	20021002	G	8120	L86661C	BEARING         	LYC         	TIO540A2C   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	EXHAUST TURBOCHA	COLLAPSED       	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 	 		1253 		L86661C					(AUS) RH ENGINE TURBOCHARGER PNO 406610-9020BEARING COLLAPSED.TURBINE ASSEMBLY CONTACTED OUTER CASING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2002110600138	20021106	00138	CE  	2002	11	6	AUS20021201      	1	20021010	G	7120	08516004	BEAM            	CONT        	IO470V      	CESSNA	310   	310K        	2074228	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	ENGINE MOUNT SEC	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH ENGINE CROSSOVER BEAM CRACKED. FURTHER INVESTIGATION FOUND THAT THE LH MOUNTS DROPPED IN MOUNT BRACKETS AND PUT	 OUTWARD LOAD ON THE ENGINE LONGITUDINAL BEAMS.					1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P5EA	 
2002110600140	20021106	00140	WP  	2002	11	6	AUS20021209      	1	20020719	G	7820	G693	MUFFLER         	LYC         	O540F1B5    	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  	 		            		ENGINE NOISE SUP	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MUFFLER AND LH COLLECTOR CRACKED AND DISTORTED.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002110600141	20021106	00141	SO  	2002	11	6	AUS20021215      	1	20021014	G	8120	KHR0173	BEARING         	GARRTT      	LW12463     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	EXHAUST TURBOCHA	FAILED          	W			    	K	 	 	 	NONE                    				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		TO	TAKEOFF        	1			AU	S 	 				KHR0173					(AUS) LH ENGINE TURBOCHARGER FAILED. SUSPECT BEARING FAILED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002110600142	20021106	00142	EU  	2002	11	6	AUS20021216      	1	20021021	G	5620	1379595C3	WINDOW          	BAC         	137169C411  	BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	PASSENGER COMPAR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) PASSENGER WINDOW OUTER PANE CRACKED. WINDOW IS THE THIRD WINDOW ON THE LH SIDE.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2002110600143	20021106	00143	SO  	2002	11	6	AUS20021217      	1	20021009	G	6120	5417500	BALL JOINT      	HARTZL      	HCE3YR2     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER CONTRO	SHEARED         	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 	 									(AUS) RH ENGINE CSU BALL JOINT FAILED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002110600144	20021106	00144	CE  	2002	11	6	AUS20021218      	1	20021015	G	2752	64679	STUD            	CESSNA      	210N        	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	TRAILING EDGE FL	SHEARED         	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 	 		17386		64679					(AUS) FLAP MOTOR MOUNT STUD BROKEN. MOTOR SEPARATED FROM ACTUATOR.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2002110600145	20021106	00145	CE  	2002	11	6	AUS20021219      	1	20021023	G	2410	646655A1	HUB             	PRESTOLITE  	ALV9407     	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ALTERNATOR-GENER	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		759  		4M000043					(AUS) ALTERNATOR GEAR DRIVE HUB SLIPPING. FOUND DURING INSPECTION IAW MEB01-3.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002110600146	20021106	00146	NE  	2002	11	6	AUS20021220      	2	20021014	G	7321	324485318	FCU             	PWA         	PW123D      	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 	 		937  							(AUS) NO1 ENGINE FUEL CONTROL UNIT SUSPECT FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002111200069	20021112	00069	SO  	2002	11	12	AUS20021221      	2	20020901	G	8520		CRANKSHAFT      								CONT  	O520  	IO520L      	17032	SO  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CRANKSHAFT BIG END JOURNALS FOR NR 4 AND NR 5 CYLINDER CONNECTING ROD SEVERELY OVERHEATED. CRANKSHAFT AND CONNECTI	NG RODS DAMAGED BEYOND REPAIR. FOUND DURING ENGINE STRIP INSPECTION FOR LOW OIL PRESSURE.										3	O			E5CE				 
2002110600147	20021106	00147	CE  	2002	11	6	AUS20021222      	1	20021023	G	5741	0001100881	FITTING         	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	WING, FUSELAGE A	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7086 							(AUS) LH WING FORWARD LOWER ATTACHMENT BATHTUB FITTING CORRODED AND DAMAGED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600148	20021106	00148	CE  	2002	11	6	AUS20021223      	1	20021023	G	5741	0001100882	FITTING         	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	WING, FUSELAGE A	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7086 							(AUS) RH WING FORWARD LOWER ATTACHMENT BATHTUB FITTING CORRODED AND DAMAGED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600149	20021106	00149	CE  	2002	11	6	AUS20021224      	1	20021023	G	5741	0001102501	FITTING         	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	WING, FUSELAGE A	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7086 							(AUS) LH WING FORWARD TOP ATTACHMENT BATHTUB FITTING CORRODED AND DAMAGED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600150	20021106	00150	CE  	2002	11	6	AUS20021225      	1	20021023	G	5741	9511001621	FITTING         	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	WING, FUSELAGE A	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7086 							(AUS) RH WING REAR TOP ATTACHMENT BATHTUB FITTING CORRODED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600151	20021106	00151	CE  	2002	11	6	AUS20021226      	1	20021023	G	5741	0001102502	FITTING         	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	WING, FUSELAGE A	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7086 							(AUS) RH WING TOP FORWARD ATTACHMENT BATHTUB FITTING CORRODED.PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600152	20021106	00152	CE  	2002	11	6	AUS20021227      	1	20021023	G	5741	951100161	FITTING         	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	WING, FUSELAGE A	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7086 							(AUS) LH WING REAR UPPER ATTACHMENT BATHTUB FITTING CORRODED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600153	20021106	00153	CE  	2002	11	6	AUS20021228      	1	20021023	G	2820	369200141	CONNECTOR       	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7086 							(AUS) LH WING MAIN FUEL TANK OUTLET FUEL RESERVOIR CONNECTOR CORRODED DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600154	20021106	00154	CE  	2002	11	6	AUS20021229      	1	20021023	G	2820	369200141	CONNECTOR       	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7086 							(AUS) RH WING MAIN FUEL TANK OUTLET FUEL RESERVOIR CONNECTOR CORRODED DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002110600155	20021106	00155	SW  	2002	11	6	AUS20021231      	1	20021015	G	5340	2050308153	FITTING         	            	            	BELL  	204   	UH1H        	1181407	SW  	LYC   	T53   	T5313B      	41549	NE  	 		            		FUSELAGE MAIN, A	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TAILBOOM LH LOWER ATTACHMENT FITTING ON FUSELAGE HAD OVERSIZE HOLES ALLOWING THE HILOK' PINS TO LOOSEN. SUSPECT CA	USED BY POOR REPAIR WORK.					1	G	7	1 	4U	4	U	 	EXPA1G71	E17EA				 
2002110600156	20021106	00156	CE  	2002	11	6	AUS20021234      	1	20021025	G	5540	10152401215	TORQUE TUBE     	BEECH       	B200C       	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	RUDDER STRUCTURE	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				BL137					(AUS) RUDDER TORQUE TUBE RIVETS LOOSE AND RIVET HOLES WORN BY UP TO APPROXIMATELY 0.254MM (0.010IN) OVERSIZE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2002110600157	20021106	00157	EA  	2002	11	6	AUS20021235      	2	20020808	G	8540	60096	GASKET          	LYC         	O235L2C     	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RECIPROCATING EN	DAMAGED         	W			    	K	 	 	 	NONE                    				O	E	K	OTHER                     	VIBRATION/BUFFET          	FLUID LOSS                	IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE FUEL PUMP/BLANK PLATE GASKET CUT BY LOCKWIRE WRAPPED AROUND THE TWO MOUNTING BOLTS. GASKET LEAKING ENGINE O	IL. ENGINEWAS FITTED WITH A BLANKING PLATE AND NOT A FUEL PUMP. ENGINE WASA RECENTLY OVERHAULED AND FITTED UNIT. PERSONN	EL/MAINTENANCEERROR.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002110600158	20021106	00158	EU  	2002	11	6	AUS20021237      	1	20021027	G	5523	HC552H0004003	TRIM TAB        	            	            	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		ELEVATOR, TAB ST	LIGHTNING STRIKE	W			    	K	 	 	 	NONE                    				C	 	 	F.O.D.                    			DE	DESCENT        	1			AU	S 	 									(AUS) RH ELEVATOR SERVO TAB DAMAGED BY LIGHTNING STRIKE.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2002110600159	20021106	00159	SW  	2002	11	6	AUS20021238      	1	20021024	G	3221	AN415	BOLT            	            	            	GULSTM	112   	114         	7630314	SW  	LYC   	O540  	IO540T4B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	NOSE/TAIL LANDIN	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NOSE LANDING GEAR ACTUATOR REAR MAIN ATTACHMENT BOLT BROKEN INAREA OF SHAFT.						1	L	7	1 	3O	3	O	 	A12SO   	1E4	5	C	P920	 
2002110600160	20021106	00160	NM  	2002	11	6	AUS20021240      	1	20021001	G	2782	111015	PISTON          	SMITHSIND   	1U1110      	BOEING	727   	727281      	138408N	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		LEADING EDGE SLA	BROKEN          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 	 				6754DPGKMNP					(AUS) NO1 LEADING EDGE FLAP ACTUATOR PISTON SHEARED IN HALF. RETAINER PITTED, KEY CHROME CHIPPED AND RODEND REQUIRED REP	LACEMENT.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002111200077	20021112	00077	NE  	2002	11	12	AUS20021244      	2	20021029	G	7200	12679	ENGINE          			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NR 4	VIBRATES        	W				A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 										(AUS) NR 4 ENGINE VIBRATION EXCESSIVE. ENGINE VIBRATION WAS ACCOMPANIEDBY A NOTICEABLE AIRFRAME VIBRATION.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2002110600161	20021106	00161	NM  	2002	11	6	AUS20021247      	1	20021028	G	6520	A0211	GEARBOX         	ROBSIN      	A0211       	ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  	 		            		TAIL ROTOR GEARB	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 	 				0406					(AUS) TAIL ROTOR GEARBOX CHIP LIGHT ILLUMINATED. GEARBOX WAS FLUSHED. THE AIRCRAFT WAS FLOWN AGAIN AND CHIP LIGHT ONCE M	ORE ILLUMINATED. TAIL ROTOR GEARBOX WAS THEN CHANGED.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002120200131	20021202	00131	CE  	2002	12	2	AUS20021248      	1	20021024	G	2434	X4087	BEARING         	PRESTOLITE  	ALV9510R    	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	DC GENERATOR-ALT	DISINTEGRATED   	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 		20   		7040992					(AUS) LH ALTERNATOR OUTER BEARING COLLAPSED. ALTERNATOR CONTAMINATEDWITH METAL FROM FAILED BEARING.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2002120400026	20021204	00026	SO  	2002	12	4	AUS20021249      	1	20021016	G	5711	6210500	DOUBLER         			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	IO540*      	41532	EA  					WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING AFT SPAR OUTBOARD AILERON HINGE DOUBLER CRACKED FOR APPROXIMATELY 50 PERCENT OF ITS LENGTH.						1	L	7	1 	3O	3	O	 	2A13    	1E4				 
2002120200132	20021202	00132		2002	12	2	AUS20021250      	4	20021021	G	2211	065004203	CONTROLLER      	KING        	KC192       	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	AUTOPILOT COMPUT	FAULTY          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 	 				54245					(AUS) AUTOPILOT COMPUTER CONTROLLER FAULTY.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002120200133	20021202	00133	NM  	2002	12	2	AUS20021251      	1	20021018	G	5551	2200141	FITTING         	            	            	PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	HORIZONTAL STABI	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				13092					(AUS) RH HORIZONTAL STABILISER FORWARD ATTACHMENT FITTING CRACKED.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2002120400027	20021204	00027	SO  	2002	12	4	AUS20021252      	2	20021031	G	8530	630354	CYLINDER        			BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE CYLINDERS (4OFF) SEVERELY ERODED ON EXHAUST FLANGES. GASKETS LEAKING AND CAUSING BLOW-BY. ENGINE, ENGINE CO	MPONENTS AND FIREWALL CORRODED DUE TO EXHAUST GAS CONTAMINATION. AIRCRAFT HAD COMPLETED 20.7 HOURS SINCE LAST PERIODIC I	NSPECTION.				1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120400028	20021204	00028	EU  	2002	12	4	AUS20021253      	1	20021028	G	7714	230322704	PROBE           			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE RPM	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) NR 2 ENGINE N2 PROBE FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2002120400029	20021204	00029	CE  	2002	12	4	AUS20021254      	1	20021031	G	5711		SPAR            			BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	RT WING	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING SPAR REPAIRED DUE TO CORROSION. A LARGE DOUBLER IS ATTACHED TO THE AFT SIDE OF THE SPAR WEB. NO RECORD OF 	REPAIR OR REFERENCE TO AN ENGINEERING ORDER OR APPROVED DATA IS RECORDED IN THE LOGBOOK. THE OWNER STATES THE REPAIRS WE	RE CARRIED OUT IN AUGUST 2000. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED REPAIR.				1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120400030	20021204	00030	CE  	2002	12	4	AUS20021255      	1	20021031	G	5341	1694000135	BRACKET         			BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	WING TO BODY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD ATTACHMENT BRACKETS CRACKED. CRACKS ARE LARGE AND EASILY VISIBLE TOTHE NAKED EYE. LAST PERI	ODIC INSPECTION WAS 20.7 HOURS PREVIOUSLY. FOUND DURING INSPECTION IAW AD/BEECH23/14A2 AND BEECH SI NO 0042-031 REVII. P	ERSONNEL/MAINTENANCE ERROR.				1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120200134	20021202	00134		2002	12	2	AUS20021256      	4	20021031	G	6113	16991003021	SPINNER         	SNSNCH      	M74DC       	BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	PROPELLER SPINNE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PROPELLER SPINNER CRACKED IN SEVERAL PLACES. SPINNER APPEARS TO HAVE BEEN REPAIRED BY WELDING. THE QUALITY OF THE 	WELD REPAIRS IS VERY POOR WITH CRACKS EMANATING FROM THE WELDS. LAST PERIODIC INSPECTION 20.7 HOURS PREVIOUS. PERSONNEL/	MAINTENANCE ERROR.				1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120200135	20021202	00135		2002	12	2	AUS20021257      	4	20021031	G	6113	16996001119	BULKHEAD        	SNSNCH      	M74DC       	BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	PROPELLER SPINNE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PROPELLER SPINNER FORWARD BULKHEAD CRACKED IN SEVERAL PLACES. BULKHEAD APPEARS TO HAVE BEEN REPAIRED BY WELDING WI	TH THEQUALITY OF WELDS VERY POOR. CRACKS EMANATING FROM THE WELDS.AIRCRAFT HAD OPERATED FOR 20.7 HOURS SINCE THE LAST PE	RIODICINSPECTION. PERSONNEL/MAINTENANCE ERROR.				1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120200136	20021202	00136	CE  	2002	12	2	AUS20021258      	1	20021031	G	5347	169400005519	ANGLE           	            	            	BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	SEAT/CARGO ATTAC	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PILOTS INBOARD SEATBELT ATTACHMENT BRACKET CONTAINED SEVERE EXFOLIATION CORROSION. AIRCRAFT HAD OPERATED FOR 20.7 	HOURS SINCE LAST PERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120400031	20021204	00031	CE  	2002	12	4	AUS20021259      	1	20021031	G	5753	AN201KP3A	BEARING         			BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	TE FLAPS	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT TRAILING EDGE FLAP OUTBOARD HINGE BEARING LOOSE IN BRACKET.SUSPECT UNAPPROVED PART. AIRCRAFT HAD OPERATED FOR 2	0.7 HOURS SINCE LAST PERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120400093	20021204	00093	CE  	2002	12	4	AUS20021260      	1	20021031	G	7160		DUCT            			BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	ENG AIR INTAKE	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) UNAPPROVED SCAT HOSE FITTED BETWEEN AIR FILTER AND CARBURETTOR. SCAT HOSE IS NOT DESIGNED FOR NEGATIVE PRESSURE SU	CH AS FOUND ININDUCTION HOSES. WHEN REMOVED, THE HOSE WAS FOUND TO BE PARTIALLY COLLAPSED. CORRECT PNO 115167DXX100323. 	AIRCRAFT HADOPERATED FOR 20.7 HOURS SINCE LAST PERIODICINSPECTION. UNAPPROVED PART.  PERSONNEL/MAINTENANCE ERROR.				1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120200137	20021202	00137	CE  	2002	12	2	AUS20021261      	1	20021031	G	2701	3538006035	YOKE            	            	            	BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	CONTROL COLUMN S	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PILOTS CONTROL YOKE CRACKED. AN ATTEMPT HAD BEEN MADE TO REPAIR THE YOKE USING GLUE. AIRCRAFT HAD OPERATED FOR 20.	7 HOURS SINCE LAST PERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120200138	20021202	00138	CE  	2002	12	2	AUS20021262      	1	20021031	G	7120	J107784	MOUNT           	CONT        	IO346A      	BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	ENGINE MOUNT SEC	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE MOUNT RUBBERS BADLY DETERIORATED. AIRCRAFT HAS OPERATEDFOR 20.7 HOURS SINCE PERIODIC INSPECTION. PERSONNEL/	MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120200139	20021202	00139	SO  	2002	12	2	AUS20021263      	1	20021029	G	2460	1709C02500	CONTACTOR       	EMB         	EMB120      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	DC POWER DISTRIB	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 		27360		120163					(AUS) BATTERY CONTACTOR SUSPECT FAULTY. WIRES W010-0013-24 ANDW010-0038-24 BURNT. INVESTIGATION FOUND THE BATTERY CONTAC	TOR K0455 PNO 170GC02-500 HAD A DISLODGED LEAF CONTACT ON TERMINAL S. THE LOOSE TERMINAL SHORT CIRCUITED CAUSING EXCESS 	CURRENT INWIRES.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2002120400146	20021204	00146	WP  	2002	12	4	AUS20021264      	2	20021102	G	7250		SEAL            	HONEYWELL   		SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TURBINE SECTION	FAILED          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		DE	DESCENT        	1			AU	S 										(AUS) LT ENGINE LOW OIL PRESSURE. INSPECTION FOUND AN OIL LEAK IN THE AREA OF THE TURBINE. INVESTIGATION FOUND THE CAUSE	 OF THE OIL LOSS TO BE TURBINE SEAL FAILURE. THE CARBON FACE OF THE SEAL HAD DISINTEGRATED AND THE BELLOWS RUPTURED RESU	LTING IN THE LOSS OF OIL. THE RUPTURED BELLOWS CAUSED FURTHER DAMAGE TO THE AFT CURVIC COUPLING.				2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2002120200140	20021202	00140	CE  	2002	12	2	AUS20021266      	1	20021029	G	3233	12810013	ACTUATOR        	CESSNA      	98820152    	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR ACT	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				6007					(AUS) LH MAIN LANDING GEAR ACTUATOR BODY CRACKED FROM THE BEARING BOSSTO THE INTERNAL DIAMETER OF THE SECTOR GEAR ACCESS	 HOLE.					1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2002120200141	20021202	00141	SO  	2002	12	2	AUS20021267      	2	20021030	G	7322	6405637	BUTTERFLY VALVE 	CONT        	IO360HB     	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	FUEL CONTROL/REC	SEIZED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 		121  		I049121AR					(AUS) THROTTLE BUTTERFLY VALVE PARTIALLY SEIZED.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2002120200142	20021202	00142	SO  	2002	12	2	AUS20021268      	2	20021101	G	7322	6405637	BUTTERFLY VALVE 	CONT        	IO360HB     	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	FUEL CONTROL/REC	SEIZED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 		6    		C199101A					(AUS) THROTTLE BUTTERFLY VALVE SEIZED.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2002120200143	20021202	00143	SO  	2002	12	2	AUS20021269      	1	20021030	G	5711	620540	SPAR            	            	            	PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING REAR SPAR CONTAINS SEVERE EXFOLIATION CORROSION BETWEEN THE SPAR AND ATTACHMENT PLATE.						1	L	7	1 	3O	3	O	 	A3SO    	E295	5	C	P920	 
2002120200144	20021202	00144	NM  	2002	12	2	AUS20021274      	1	20021104	G	7922	SL53E19600	NUT             	SUPAIRPART  	VERNATHERM  	ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  	 		            		ENGINE OIL TEMPE	LOOSE           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				22099					(AUS) ENGINE OIL TEMPERATURE BYPASS VALVE (VERNATHERM) NUT LOOSE. SUSPECT ROLL PIN NOT FITTED DURING ASSEMBLY.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002120200145	20021202	00145	CE  	2002	12	2	AUS20021275      	1	20021022	G	3230	504501025	TORQUE TUBE     	            	            	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR TORQUE TUBE CRACKED AND TWISTED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002120200146	20021202	00146	WP  	2002	12	2	AUS20021277      	1	20021025	G	6320	369D2570421	HOSE            	DOUG        	369D25100505	HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  	 		            		MAIN ROTOR GEARB	WORN            	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 	 				0022220016					(AUS) TRANSMISSION OIL HOSE CHAFING ON AIRCRAFT STRUCTURE.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002120500008	20021205	00008	SO  	2002	12	5	AUS20021279      	1	20021015	G	2750		LEVER           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					TE FLAPS	BINDING         	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) FLAP LEVER FOULING ON ENGINE CONTROL FRICTION LEVER.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002120200147	20021202	00147		2002	12	2	AUS20021280      	4	20021031	G	6122	782490A50	CONTROL UNIT    	HAMSTD      	782490A50   	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER GOVERN	FAULTY          	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 	 		2593 		970817					(AUS) LH PROPELLER CONTROL UNIT FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002120200148	20021202	00148	NM  	2002	12	2	AUS20021281      	1	20021025	G	2820	20C1444	VALVE           	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		AIRCRAFT FUEL DI	FAULTY          	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 	 				2189					(AUS) FUEL TRANSFER SYSTEM CHECK VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002120200149	20021202	00149	NM  	2002	12	2	AUS20021282      	1	20021029	G	5753	6546486155	FLAP            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		TRAILING EDGE FL	DAMAGED         	W			    	K	 	 	 	NONE                    				O	D	 	OTHER                     	INFLIGHT SEPARATION       		IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH INBOARD MID FLAP UPPER SKIN DAMAGED. A SECTION OF METAL SKIN MEASURING APPROXIMATELY 150MM (5.9IN) BY 250MM (9.	84IN) WAS MISSING.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002120500009	20021205	00009	EU  	2002	12	5	AUS20021283      	1	20021031	G	3230	9740926112	RELAY           			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG HYD SYS	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					227					(AUS) HYDRAULIC POWER RELAY FAULTY.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120500010	20021205	00010	EU  	2002	12	5	AUS20021284      	1	20021004	G	5610	9598110103	WINDSHIELD      			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT WINDSHIELD OUTER LAYER CRACKED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120500011	20021205	00011	NE  	2002	12	5	AUS20021285      	2	20021101	G	7261		OIL SYSTEM      			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	LT ENGINE	LOW             	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AU	S 										(AUS) LT ENGINE OIL QUANTITY BELOW MINIMUM LEVEL. PERSONNEL/MAINTENANCE ERROR.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2002120500012	20021205	00012	NM  	2002	12	5	AUS20021286      	1	20021106	G	2597	TBY7MT006	WIRE HARNESS    			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					GALLEY	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRING HARNESS LOCATED IN GALLEY 4C AREA BURNED.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2002120200150	20021202	00150		2002	12	2	AUS20021288      	4	20021021	G	3460		COMPUTER        	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FLIGHT MANAGEMEN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) FLIGHT MANAGEMENT COMPUTER FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002120200151	20021202	00151	EU  	2002	12	2	AUS20021290      	2	20021104	G	7530	7064004	MOTOR           	GE          	CFM563C     	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		COMPRESSOR BLEED	LEAKING         	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 	 				13711					(AUS) NO1 ENGINE VBV GEAR MOTOR LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002120200152	20021202	00152	NM  	2002	12	2	AUS20021291      	1	20021106	G	2761	82950010271	PIPE            	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	DRAG CONTROL ACT	LEAKING         	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 	 									(AUS) RH INBOARD ROLL SPOILER ACTUATOR PRESSURE LINE LEAKING FROM PINHOLE. LOSS OF NO1 HYDRAULIC SYSTEM FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002120500016	20021205	00016	CE  	2002	12	5	AUS20021293      	1	20021104	G	2710		BELLCRANK       			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	AILERON CONTROL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AILERON BELLCRANK STOP BENT. DAMAGE ALSO TO PUSH-PULL ROD AND ATTACHMENT HARDWARE AS WELL AS TO THE AILERON CON	TROL BRACKET AND SECURING RIVETS.					1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL	 
2002120200153	20021202	00153	CE  	2002	12	2	AUS20021294      	1	20021030	G	3233	2379828	PLUNGER         	WESTERNHYD  	99101363    	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR ACT	STICKING        	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 	 		300  							(AUS) RH MAIN LANDING GEAR ACTUATOR DOWN MICROSWITCH PLUNGER STUCK.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002120200154	20021202	00154	EA  	2002	12	2	AUS20021298      	2	20021101	G	8520	11F20022D3	CRANKCASE       	LYC         	LTIO540J2B  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 		1699 		L241661A					(AUS) CRANKCASE PNO 11F20022-D3) CRACKED AT THROUGH BOLT LOCATION. NO4CYLINDER PNO LW-12066 HOLDDOWN STUDS (7OFF8) SHEAR	ED ALLOWING PARTIAL SEPARATION OF THE CYLINDER FROM THE CRANKCASE. UNABLE TOASCERTAIN CHAIN OF EVENTS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002120200155	20021202	00155	CE  	2002	12	2	AUS20021299      	1	20021109	G	5347	24140021	SEAT TRACK      	            	            	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SEAT/CARGO ATTAC	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH INBOARD AND LH OUTBOARD SEAT TRACKS WORN BEYOND LIMITS. FOUNDDURING INSPECTION IAW AD/C172/53 AMDT2.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002120200156	20021202	00156	NM  	2002	12	2	AUS20021300      	1	20021103	G	7120	LM43154	HOUSING         	LORD        	LM431SA18   	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE MOUNT SEC	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH ENGINE REAR MOUNT HOUSING CRACKED. RH ENGINE REAR MOUNTHOUSING REWORKED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002120200157	20021202	00157	EU  	2002	12	2	AUS20021303      	1	20021106	G	5711	6814013B3	SPAR CAP        	            	            	PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	WING SPAR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING SPAR CAP CRACKED. PREVIOUS CRACK HAD BEEN REPAIRED USINGSTAINLESS STEEL LAMINATIONS. DURING EDDY CURRENT I	NSPECTION IAW AD/P68/43 AMDT1 IT WAS FOUND THAT THE CRACK HAD GROWN FROM 10MM (0.39IN) TO 21MM (0.826IN) ON THE VERTICAL	 FACE.				1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2002120200158	20021202	00158	NM  	2002	12	2	AUS20021304      	1	20021107	G	2810		FUEL TANK       	            	            	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	FUEL STORAGE	FOD             	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 	 									(AUS) MAIN AND AUXILIARY FUEL TANKS CONTAMINATED BY FOREIGN OBJECT. FOD WAS BLOCKING FUEL TRANSFER FROM RH AUXILIARY FUE	L TANK. PERSONNEL/MAINTENANCE ERROR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002120200159	20021202	00159	NM  	2002	12	2	AUS20021306      	1	20021114	G	7110	65255172	PANEL           	PWA         	JT8D15      	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  	 		            		ENGINE COWLING S	SEPARATED       	W			    	K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 	 									(AUS) NO2 ENGINE RH FORWARD COWL BLOWOUT PANEL MISSING. PANEL WAS FOUND ON RUNWAY.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002120200160	20021202	00160	CE  	2002	12	2	AUS20021307      	1	20021031	G	5751	512400098	AILERON         	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	AILERONS	OUT OF BALANCE  	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH AILERON OUT OF BALANCE. ACCESS PANELS (3OFF) IN LOWER SKIN AND A QUANTITY OF EPOXY RESIN IN THE TRAILING EDGE C	AUSED THE AILERON TO BE APPROXIMATELY 700 GRAMS OUT OF BALANCE. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002120200161	20021202	00161	CE  	2002	12	2	AUS20021308      	1	20021031	G	3222	58420005	FORK            	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	NOSE/TAIL LANDIN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NOSE LANDING GEAR FORK CRACKED. FOUND USING EDDY CURRENTINSPECTION.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002120200162	20021202	00162	CE  	2002	12	2	AUS20021312      	1	20021031	G	5343		STRUCTURE       	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LANDING GEAR ATT	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR UPLOCK SUPPORT STRUCTURE CRACKED AND RIVETS LOOSE. BOLT HOLES ELONGATED. UPLOCK HOOK PIVOTS LOOS	E.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002120200163	20021202	00163	CE  	2002	12	2	AUS20021313      	1	20021031	G	5320	58130412	WEB             	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	FUSELAGE, MISCEL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUSELAGE WEB LOCATED IN AREA BEHIND THE NLG DRAG BRACE PIVOTFITTING CRACKED. CRACK HAD BEEN PREVIOUSLY STOP DRILLE	D.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002120200164	20021202	00164	SO  	2002	12	2	AUS20021314      	1	20021106	G	2150	10000029	ACTUATOR        	            	            	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	CABIN COOLING SY	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) LH AIRCONDITIONING SYSTEM RAM AIR ACTUATOR AFT MOUNT WORN THROUGH ALLOWING ACTUATOR TO DISCONNECT. RAM AIR VALVE P	ARTIALLY CLOSED RESTRICTING COOLING AIR FLOW THROUGH THE HEAT EXCHANGER AND CAUSING THE AIRCONDITIONING PACK TO SHUT DOW	N DUE TO OVERHEATING.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2002120500025	20021205	00025	SO  	2002	12	5	AUS20021315      	1	20021107	G	3230		PIN             			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	MLG XMSN	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR TRANSMISSION ASSEMBLY MOTOR RELEASE LINK PIN BROKEN AND JAMMING MECHANISM.						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2002120500026	20021205	00026	SO  	2002	12	5	AUS20021316      	1	20021112	G	5753	6232300	BRACKET         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  	SNSNCH	74DM	M74DM       	EA  	TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP CENTER HINGE BRACKETS SEVERELY CORRODED. LT AND RT ATTACHMENT RIBS DESTROYED BY CORROSION.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002120500029	20021205	00029	GL  	2002	12	5	AUS20021319      	3	20021108	G	6114	727672	HUB             													MCAULY	2A34C	D2AF34C30   	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROP HUB CRACKED IN BLADE SOCKET. FOUND DURING EDDY CURRENT INSP. VISUAL INSP IFRETENTION NUT FOUND CRACK IN THREA	DS. INSP CARRIED OUT FOLLOWING LONG TERM STORAGE. PROP HAD NO HRS  SINCE OVERHAUL.															5	C	P5EA	 
2002120500030	20021205	00030	GL  	2002	12	5	AUS20021320      	3	20021108	G	6114	702987	HUB             													MCAULY	2A34C	D2AF34C30   	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CRACKED IN BLADE SOCKET. FOUND DURING EDDY CURRENT INSPECTION IAW AD/PMC/41. PROPELLER WAS BEING INS	PECTED FOLLOWING LONG TERM STORAGE AND HAD NO HOURS OPERATION SINCE OVERHAUL.															5	C	P5EA	 
2002120200165	20021202	00165	NM  	2002	12	2	AUS20021321      	1	20021022	G	5320	693535214	CONNECTOR       	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUSELAGE, MISCEL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CABIN UPPER LOBE STRUCTURE FRAME TO STRINGER TIES CRACKED AND FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002120500031	20021205	00031		2002	12	5	AUS20021322      	4	20021115	G	2562	VARIOUS	SPRING          			GROB  	G115  	G115C       	1660303	EU  										ELT BATT CASE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELT BATTERY CASE COIL CONTACT SPRINGS CORRODED.						1	L	7	1 	3O			NT	A57EU   					 
2002120500032	20021205	00032	CE  	2002	12	5	AUS20021323      	2	20021104	G	7414		PIN             			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					MAGNETO	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAGNETO HARD TO TIME. INVESTIGATION FOUND THE SPLIT PIN SECURING THE MAGNETO COUPLING NUT WAS CONTACTING THE END O	F THE DRIVE CUSHION BEARING STUD ON THE CRANKCASE. MAGNETO WAS A NEWLY FITTED UNIT.  FURTHER INVESTIGATION FOUND OTHER S	IMILAR MAGNETOS. THE STUDS WERE FOUND TO BE THE CORRECT LENGTH AND THE SPLIT PINS WERE INSTALLED CORRECTLY.  SUSPECT CAU	SED BY INSUFFICIENT CLEARANCE BETWEEN THE END OF THE MAGNETO SHAFT AND THE SUPPORT STUD IN THECRANKCASE (CLEARANCE IS AP	PROXIMATELY 2MM (0.078IN).		1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002120500034	20021205	00034	NM  	2002	12	5	AUS20021325      	1	20021117	G	3210		LANDING GEAR    			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					MAINS	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR FAILED TO RETRACT. THE GROUND SENSING RELAY AND GROUND SENSING MODULE WERE CHANGED BUT THE DEFECT REM	AINED. DURING TROUBLESHOOTING THE DEFECT DISAPPEARED. A THOROUGH SERVICEABILITY CHECK WAS CARRIED OUT AND THE AIRCRAFT R	ETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002120200166	20021202	00166	WP  	2002	12	2	AUS20021327      	1	20021108	G	6310	A1851	BRACKET         	ROBSIN      	R44ASTRO    	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  	 		            		ENGINE/TRANSMISS	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LOWER ACTUATOR BRACKET CRACKED.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002120500035	20021205	00035	SO  	2002	12	5	AUS20021328      	1	20021021	G	2622	V825320	O-RING          			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	AMTR	C8289	C8289       	GL  	FIRE BOTTLE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) HAND HELD FIRE EXTINGUISHER CYLINDER TO DISCHARGE HEAD O-RING SEAL FAILED. LOSS OF FIRE EXTINGUISHING FLUID.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	EXPP5N	 
2002120500036	20021205	00036	GL  	2002	12	5	AUS20021329      	3	20021106	G	6114	107967	HUB             			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5107 							(AUS) PROPELLER HUB SUSPECT CRACKED IN TWO ADJACENT MOUNTING BOLT HOLES. FOUND DURING INSPECTION IAW DOWTY ROTOL SB/61/1	125.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2002120500037	20021205	00037	CE  	2002	12	5	AUS20021330      	1	20021106	G	5312		BULKHEAD        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD DAMAGED. PUNCTURE HOLE IN BULKHEAD WEB LOCATED IN AREA BETWEEN THE CENTRELINE AND INBOARD O	F THE OVERPRESSURE AND OUTFLOW VALVE CUTOUT. FOUND DURING INSPECTIONIAW RAYTHEON SB/53/3513 REV1. DAMAGE CAUSED DUE TO I	MPACT BYTRIM.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002120500038	20021205	00038	NM  	2002	12	5	AUS20021331      	1	20021108	G	1430		FASTENER        			BOEING	747   	747400      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					NACELLE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRUT INBOARD MIDSPAR FITTING HORIZONTAL AND VERTICAL TANGS HAD SEVERAL LOOSE FASTENERS.						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2002120200167	20021202	00167	SW  	2002	12	2	AUS20021333      	1	20021115	G	2710	500004267	CABLE           	            	            	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	AILERON CONTROL	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AILERON CABLE FRAYED IN AREA OF FAIRLEAD LOCATED OUTBOARD OF LH NACELLE.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2002120200168	20021202	00168	SO  	2002	12	2	AUS20021335      	1	20021113	G	5711		SPAR            	            	            	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING SPAR CONTAINED LIGHT CORROSION AND MINOR PITTING LOCATEDIN AREA JUST ABOVE LOWER SPAR CAP RADIUS. AREA OF 	CORROSION APPROXIMATELY 25MM (1IN) LONG BY 6MM (0.236IN) WIDE. FOUND DURING INSPECTION IAW AWB51-4.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2002120500042	20021205	00042	GL  	2002	12	5	AUS20021337      	2	20021121	G	7321	252465426H	FCU             								ALLSN 	250B  	250B17      	03012	GL  					ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			238  							(AUS) FUEL CONTROL UNIT FLYWEIGHT CLIP FAULTY. LIMITED INFORMATIONPROVIDED.											3	T			E10CE				 
2002120500046	20021205	00046	CE  	2002	12	5	AUS20021341      	1	20021115	G	5312	805	FITTING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD STIFFENER CLEAT CRACKED. CLEAT IS FITTED AS PART OF CARGO DOOR MODIFICATION. FOUND DURING I	NSPECTION IAW AD/BEECH200/55 (SB/2472).					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002120500047	20021205	00047	EU  	2002	12	5	AUS20021342      	1	20021121	G	7120	115C6100	MOUNT           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			995  							(AUS) ENGINE MOUNT FRAME CRACKED IN TUBE SEGMENT ADJACENT TO THE RT LOWER AFT LORD MOUNT.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2002120200169	20021202	00169	CE  	2002	12	2	AUS20021343      	1	20021122	G	3213	169810000113	ROD             	            	            	BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	MAIN LANDING GEA	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH MAIN LANDING GEAR SHOCK ABSORBER RODS SEVERELY WORN. LH MLG RODS WORN APPROXIMATELY 0.863MM (0.034IN). R	H MLG RODS WORN APPROXIMATELY 0.457MM (0.018IN). FOUND DURING INSPECTION IAWAD/BEECH23/13. AIRCRAFT HAD OPERATED FOR 20.	7 HOURS SINCE LASTPERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR.				1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120500048	20021205	00048	CE  	2002	12	5	AUS20021344      	1	20021122	G	3213	169810000119	WASHER          			BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	MLG STRUT	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR SHOCK ABSORBERS FITTED WITH PLASTIC AUTOMOTIVE TYPE BUSHES ALONG WITH PNO 169-810000-1	19 WASHERS. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120500049	20021205	00049	CE  	2002	12	5	AUS20021345      	1	20021122	G	3213	169810000609	LANDING GEAR    			BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	LT & RT	TRANSPOSED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR AND RT MAIN LANDING GEAR TRANSPOSED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2002120500051	20021205	00051	EA  	2002	12	5	AUS20021347      	2	20021121	G	8530	05K21232	CYLINDER        			GROB  	G115  	G115        	       	EU  	LYC   	O235  	O235H2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 CYLINDER CRACKED IN AREA ADJACENT TO THE ATTACHMENT FLANGE. CRACK LENGTH APPROXIMATELY 100MM (3.93IN).						1	L	7	1 	3O	3	O	NT	A57EU   	E223	5	N	P9045	 
2002120200170	20021202	00170	SO  	2002	12	2	AUS20021348      	1	20021119	G	2150	490150	SLEEVE          	HONEYWELL   	22045402    	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	CABIN COOLING SY	DAMAGED         	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 	 		8135 		89909214					(AUS) LH AIRCONDITIONING PACK ASSEMBLY LEAKING. INVESTIGATION FOUND THREE PIPELINE SLEEVE CONNECTORS SUSPECT FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2002120200171	20021202	00171	CE  	2002	12	2	AUS20021349      	1	20021101	G	2730	05341221	BELLCRANK       	            	            	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	AMTR	C8289	C8289       	GL  	ELEVATOR CONTROL	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ELEVATOR BELLCRANK CONTAINED SEVERE EXFOLIATION CORROSION. SIGNSOF CORROSION ALSO FOUND ON RUDDER HINGES.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	EXPP5N	 
2002120200172	20021202	00172	EU  	2002	12	2	AUS20021351      	1	20021124	G	5230	HC523B0018000	DOOR            	            	            	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		CARGO/BAGGAGE DO	FAULTY          	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			AU	S 	 									(AUS) FORWARD CARGO DOOR HANDLE AJAR. SUSPECT HANDLE HAD NOT BEEN FULLY CLOSED. PERSONNEL/MAINTENANCE ERROR.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2002120500053	20021205	00053	NM  	2002	12	5	AUS20021352      	1	20021124	G	2822	433092032	MODULE          			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					BOOST PUMP	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) BOOST PUMP SWITCH MODULE FAULTY.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2002120200173	20021202	00173	NM  	2002	12	2	AUS20021353      	1	20021122	G	5210		PUSHROD         	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		PASSENGER/CREW D	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CABIN DOOR R2 JAMMED CLOSED. INVESTIGATION FOUND THE LOWER DOOR PUSHROD BROKEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002120500055	20021205	00055	GL  	2002	12	5	AUS20021355      	3	20021120	G	6114	D2483	HUB             													HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB HAD UNAPPROVED MODIFICATION CARRIED OUT TO THE SIX MOUNTING FLANGE COUNTER BORES. HUB EXHIBITS EVIDE	NCE OF DAMAGE TO THE PRELOAD PLATE SHELF AREA SUSPECT DUE TO GROUND STRIKE. SUSPECT HUB HAD NOT BEEN STRIPPED OF ANODIZI	NG AND ETCHED AND PAINTED AS REQUIRED BY MANUAL 202A. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED MODIFICATION.														5	C	P9EA	 
2002120500056	20021205	00056	NM  	2002	12	5	AUS20021357      	1	20021127	G	7500	MA20A10011	ACTUATOR        			BOEING	737   	73776N      	13844CH	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ENGINE BLEED AIR	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE SPAR VALVE ACTUATOR SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2002120200174	20021202	00174	NE  	2002	12	2	AUS20021358      	2	20021124	G	7321	114E6112G1	EEC             	RROYCE      	BR700715A130	BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  	 		            		FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 	 				LHBR0148					(AUS) LH ENGINE SPOOLED DOWN. ENGINE ELECTRONIC CONTROLLER (EEC) PNO114E6112G1 AND FUEL METERING UNIT (FMU) PNO 8061-965	 CHANGED ON ADVICE FROM MANUFACTURERS.					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2002120200175	20021202	00175	EU  	2002	12	2	AUS20021361      	1	20021102	G	5302	1053040212	FITTING         	            	            	BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  	 		            		ROTORCRAFT TAIL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TAIL ROTOR GEARBOX FITTING CRACKED.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2002120200176	20021202	00176	SO  	2002	12	2	AUS20021362      	1	20021120	G	5711	2029607	SPAR CAP        	            	            	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH WING MAIN LOWER SPAR CAP CORRODED. CORROSION IS LOCATED AT WS62 AS INDICATED IN AWB/51-4 ISSUE 1.						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2002120200177	20021202	00177	SO  	2002	12	2	AUS20021363      	1	20021120	G	5711	2029608	SPAR CAP        	            	            	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING MAIN LOWER SPAR CAP CORRODED. CORROSION IS LOCATED AT WS62 AS INDICATED IN AWB/51-4 ISSUE 1.						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2002120200178	20021202	00178	SO  	2002	12	2	AUS20021364      	2	20021122	G	8530	SA636242	VALVE GUIDE     	SUPAIRPART  	SA47000     	CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	RECIPROCATING EN	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 		277  		NA					(AUS) NO2 CYLINDER EXHAUST VALVE GUIDE CARBON BUILDUP. EXHAUST VALVESEIZED IN GUIDE CAUSING PUSHROD TO BEND AND SHROUD T	UBE TO BE BROKEN.					1	H	7	1 	3O	3	O	 	3A21    	3E1	5	C	P3EA	 
2003012100216	20030121	00216	GL  	2003	1	21	AUS20021367      	2	20020921	G	7230	CAC35460	SEAL            	ALLSN       	COMPRESSOR  	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  	 		            		TURBINE ENGINE C	SEIZED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				CAC35460					(AUS) ENGINE COMPRESSOR SEIZED. INVESTIGATION FOUND THE REAR LABYRINTHSEAL HAD PICKED UP IN THE SEAL HOUSING.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003012100217	20030121	00217	SW  	2003	1	21	AUS20021368      	1	20021025	G	2931		INDICATOR       			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HYDRAULIC FILTER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC FILTER DIFFERENTIAL PRESSURE INDICATOR FAULTY.  INDICATOR APPEARED TO BE STUCK DUE TO CORROSION AND DIRT	.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2003012100218	20030121	00218	SW  	2003	1	21	AUS20021371      	1	20021125	G	5553	301971	PLATE           	            	            	AIRTRC	AT500 	AT502B      	0390307	SW  	PWA   	PT6   	PT6A15AG    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	VERTICAL STABILI	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) VERTICAL FIN FRONT SPAR ATTACHMENT FITTING FAILED. REAR SPARCRACKED.						1	L	7	1 	3T	4	T	NC	A17SW   	E4EA	6	C	P15EA	 
2003012100219	20030121	00219	CE  	2003	1	21	AUS20021377      	1	20021119	G	5520		TORQUE TUBE     	            	            	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELEVATOR STRUCTU	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH ELEVATOR TORQUE TUBE ASSEMBLIES SEVERELY CORRODED PARTICULARLY FITTINGS PNO 0734102-4 AND PNO 0734102-3.	 LOWER LEFT HAND SKIN PNO 0532001-91 ALSO CORRODED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003012100220	20030121	00220	CE  	2003	1	21	AUS20021378      	1	20021122	G	5347	121040821	SEAT TRACK      	            	            	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	SEAT/CARGO ATTAC	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) SEAT TRACK CRACKED ACROSS LOCK PIN HOLES.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003012100221	20030121	00221	CE  	2003	1	21	AUS20021379      	1	20021126	G	3233	12810013	HOUSING         	CESSNA      	98820152    	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR ACT	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 				5822					(AUS) LH MAIN LANDING GEAR ACTUATOR HOUSING CRACKED. ACTUATOR RACKSEPARATED FROM SECTOR GEAR.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003012100222	20030121	00222	SO  	2003	1	21	AUS20021380      	2	20021014	G	8550	632062	DIPSTICK        	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	RECIPROCATING EN	DISTORTED       	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		DE	DESCENT        	1			AU	S 	 		616  							(AUS) ENGINE OIL DIPSTICK BENT, GIVING AN INCORRECT READING OF OILQUANTITY. SUSPECT CAUSED BY BENDING THE DIPSTICK WHILE	 WIPING OFF THE OIL. BENT DIPSTICK CAN ALSO WEAR ON THE BOTTOM OF THE SUMP.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003012100223	20030121	00223	EU  	2003	1	21	AUS20021384      	1	20021203	G	2931	523250	INDICATOR       	            	            	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	HYDRAULIC PRESSU	FAILED          	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			TO	TAKEOFF        	1			AU	S 	 									(AUS) MAIN HYDRAULIC SYSTEM PRESSURE INDICATOR FAILED.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2003012100224	20030121	00224	CE  	2003	1	21	AUS20021388      	1	20021203	G	2710	276455A	BEARING         	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	AILERON CONTROL	COLLAPSED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AILERON YOKE BEARING COLLAPSED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003012100225	20030121	00225	EU  	2003	1	21	AUS20021389      	1	20021204	G	3240	HTE90821	ACTUATOR        	            	            	BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		LANDING GEAR BRA	FAULTY          	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 	 									(AUS) PARK BRAKE ACTUATOR FAULTY. ACTUATOR WAS CONSISTENTLY MOTORING.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003012100227	20030121	00227	EA  	2003	1	21	AUS20021397      	1	20021128	G	5751	CZW151A	BRACKET         	            	            	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	AILERONS	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AILERON CENTRE HINGE BEARING SUPPORT BRACKET CONTAINED EXFOLIATION CORROSION. AREA OF CORROSION APPROXIMATELY 2	0MM (0.78IN) BY 5MM (0.196IN) AND 0.5MM (0.019IN) DEEP. AIRCRAFT IS A FLOATPLANE.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2003012100228	20030121	00228	EU  	2003	1	21	AUS20021404      	1	20021209	G	2910	4204001	PTU             	            	            	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		HYDRAULIC SYSTEM	FAULTY          	W			    	K	 	 	 	NONE                    				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 	 									(AUS) YELLOW HYDRAULIC SYSTEM POWER TRANSFER UNIT (PTU) FAULTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003012100229	20030121	00229	SW  	2003	1	21	AUS20021407      	1	20021203	G	2460		CABLE           	            	            	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	DC POWER DISTRIB	FAULTY          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 	 									(AUS) ALTERNATOR MAIN POWER CABLE FAULTY. CABLE WAS SPLICED CAUSING HIGH RESISTANCE. PERSONNEL/MAINTENANCE ERROR.						1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2003013000014	20030130	00014	EA  	2003	1	30	AUS20021408      	2	20021205	G	8530		GASKET          			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	NR 1 CYLINDER	LEAKING         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 			842  							(AUS) NR 1 CYLINDER LEAKING AT EXHAUST GASKET. DAMAGE TO COOLING FINS AND BAFFLE.						1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2003012100230	20030121	00230	CE  	2003	1	21	AUS20021412      	1	20021209	G	5553	513102057	BRACKET         	CESSNA      	402C        	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	VERTICAL STABILI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				513102057					(AUS) VERTICAL FIN FORWARD MOUNT BRACKET EXCESSIVELY CORRODED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003013000019	20030130	00019	CE  	2003	1	30	AUS20021415      	1	20021212	G	5710		STRUCTURE       			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING COMPONENTS CRACKED. COMPONENTS AFFECTED INCLUDE:  TRAILING EDGE RIB LOCATED AT STA 23.625.  WING ROOT RT R	IB ASSY LOCATED AT STA 23.625,  WING SPAR REINFORCEMENT FITTING,  WHEN CHANGING TRAILING EDGE RIB LOCATED AT WS 23.625, 	 IT WAS NOTED THAT RIVETING HAD BEEN INCORRECTLY  CARRIED OUT WITH 1/8 IN RIVETS IN 5/32 IN HOLES (SOME NOT ALL). WHEN S	EALER WAS REMOVED FROM THE WING ROOT AT STA 23.625,  THREE CRACKS WERE FOUND IN THE PART (RIB ASSEMBLY - WING ROOT). SUS	PECT REPAIRS CARRIED OUT IN USA PRIOR TO AIRCRAFT ARRIVAL IN AUSTRALIA. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.		1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003012100231	20030121	00231	SW  	2003	1	21	AUS20021416      	1	20021210	G	2820	476822241	VALVE           	            	            	BELL  	47    	47G5A       	1181034	SW  	LYC   	O435  	VO435B1A    	41516	EA  	 		            		AIRCRAFT FUEL DI	SEPARATED       	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 	 									(AUS) AIRCRAFT SUFFERED INFLIGHT POWER LOSS. INVESTIGATION FOUND LH FUEL TANK CRASHWORTHY SYSTEM BREAKAWAY FUEL VALVE BE	GINNING TOSEPARATE WHICH RESTRICTED FUEL FLOW FROM THE LH TANK. SUSPECT CAUSED BY UNKNOWN PERSON STANDING ON VALVE DURIN	G MAINTENANCE ORPREFLIGHT. PERSONNEL/MAINTENANCE ERROR.				1	G	7	1 	3O	3	O	 	2H3     	E279				 
2003012100232	20030121	00232	EU  	2003	1	21	AUS20021420      	1	20021207	G	5610	D20543406	WINDSHIELD      	PPG         	D20543406   	FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  	 		            		FLIGHT COMPARTME	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 				95317H8198					(AUS) RH WINDSHIELD CRACKED. SIGNS OF ELECTRICAL FAILURE. MANUFACTURERSUGGESTS PROBLEM COULD BE DUE TO MOISTURE INGRESS.	 SEE MDR02/1419 FOR FURTHER INFORMATION.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2003013000020	20030130	00020	EU  	2003	1	30	AUS20021422      	1	20021211	G	2910	9738114306	PRESSURE SWITCH 			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) HYDRAULIC POWERPACK LOW PRESSURE SWITCH FAILED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003013000021	20030130	00021		2003	1	30	AUS20021423      	4	20021212	G	3418	9754421422	TRANSMITTER     	ROSEMOUNT   		PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STALL WARNING	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0221					(AUS) RT ANGLE OF ATTACK TRANSMITTER SEIZED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003012100233	20030121	00233	SW  	2003	1	21	AUS20021424      	1	20021212	G	3242	212033	BRAKE           	            	            	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	BRAKE	FIRE            	W			    	K	 	 	 	NONE                    				O	B	 	OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			AU	S 	 				2389AND5143					(AUS) LH MAIN LANDING GEAR BRAKE FIRE. BRAKES WERE BEING BURNED INFOLLOWING BRAKE REPLACEMENT. ON ARRIVING BACK AT THE M	AINTENANCEFACILITY AND AFTER SHUTTING DOWN THE ENGINEERS SAW FLAMES FROMTHE LEFT HAND BRAKE PACK AND EXTINGUISHED THE FI	RE. HYDRAULIC FLUID WAS LEAKING FROM ALL FOUR BRAKE ASSEMBLIES. DUE TO THE HEAT GENERATED FROM THREE HEAVY BRAKE APPLICA	TIONS THE SEALS IN THEBRAKES LET GO CAUSING THE BRAKES TO BECOME SPONGY AND ALLOWINGFLUID ONTO THE HOT DISCS WHICH THEN 	IGNITED AFTER SHUTDOWN. TWO TYRES WERE ALSO FLAT SPOTTED AND BURST ON TAXI BACK.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2003012100234	20030121	00234	NM  	2003	1	21	AUS20021427      	1	20021212	G	2822	5006003C	PUMP            	            	            	BOEING	767   	767277      	1385128	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		FUEL BOOST PUMP	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN FUEL TANK BOOST PUMPS (3OFF) DEFECTIVE. FOUND DURING INSPECTION IAW AAES ER B76-28-20-37 AND HAMILTON SUNDSTR	AND SB5006003-28-2.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2003012100235	20030121	00235	NM  	2003	1	21	AUS20021442      	1	20021114	G	5310		DOUBLER         	            	            	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		FUSELAGE MAIN, S	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FORWARD GALLEY DOORWAY FORWARD UPPER CORNER CRACKED AT FOUR FASTENER HOLES. ONE CRACK IN BEARSTRAP DOUBLER AND THR	EE CRACKS IN EXTRA INTERNAL DOUBLER. FOUND DURING EDDY CURRENT INSPECTION IAW AD/B737/24 AND EI 733-53-14R4.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003012100236	20030121	00236	NM  	2003	1	21	AUS20021443      	1	20021122	G	5230		DOOR            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		CARGO/BAGGAGE DO	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FORWARD CARGO DOOR CRACKED IN FORWARD AND AFT LOWER CORNERS ASWELL AS THE LOWER CORNER OUTER T' CHORD. FOUND DURIN	G EDDY CURRENT INSPECTION IAW AD/B737/142 AND EI 737-52-3.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003021000060	20030210	00060	EA  	2003	2	10	AUS20021446      	2	20021215	G	8550	77852	HOUSING         	LYC         	IO540C4B5   	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	AMTR	C8289	C8289       	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 		405  							(AUS) ENGINE OIL FILTER HOUSING CRACKED FROM BOLT HOLE. SUSPECT CAUSEDBY OVERTORQUING.						1	L	7	2 	3O	3	O	 	1A10    	1E4	5	N	EXPP5N	 
2003021000061	20030210	00061	SO  	2003	2	10	AUS20021450      	1	20021218	G	7603	455350	CABLE           	LYC         	O320D3G     	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	POWER LEVER	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 									(AUS) ENGINE THROTTLE CABLE FAILED.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003021000062	20030210	00062	EU  	2003	2	10	AUS20021455      	1	20021223	G	2460	L56225	FUSE            	            	            	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	DC POWER DISTRIB	CORRODED        	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 	 									(AUS) BUSBAR UNDERVOLTAGE FUSE F86 CORRODED AND BROKEN.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2003021000063	20030210	00063	EA  	2003	2	10	AUS20021467      	1	20020524	G	5751		ARM             	            	            	DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AILERONS	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH OUTBOARD AILERON HINGE ARM CONTAINED EXFOLIATION CORROSION AROUND BOLT HOLE.						1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003021000064	20030210	00064	NM  	2003	2	10	AUS20021470      	1	20021215	G	2612	894120	FIRE DETECTOR   	            	            	BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		FIRE DETECTION	FAULTY          	W			    	K	 	 	 	NONE                    				E	B	N	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             	CL	CLIMB          	1			AU	S 	 									(AUS) NO2 ENGINE FIRE WARNING ALERT. ENGINE WAS SHUTDOWN AND BOTTLESFIRED. FIRE WARNING LIGHT REMAINED ON' FOR A SHORT P	ERIOD, THEN  WENT OUT. THE DETECTOR LIGHT REMAINED ON'. INVESTIGATION FOUND THE FIRE LOOP DETECTORS LOOSE AND DIRTY.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003021200010	20030212	00010	EA  	2003	2	12	AUS20021471      	2	20021222	G	7414	M3548	SHAFT           	SLICK       		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O320  	O320*       	41508	EA  	SNSNCH	76E	76EM8       	EA  	MAGNETO	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					98040595					(AUS) MAGNETO ROTOR SHAFT BROKEN AT THE PRIMARY GEAR & CAM FORK SECTION.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P4EA	 
2003021000065	20030210	00065	GL  	2003	2	10	AUS20021482      	3	20021214	G	6114	660709201	HUB             	ROTOL       	R321482F8   	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	PROPELLER HUB SE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1399 		DR1DRS139681					(AUS) FOLLOWING PILOT REPORTS OF PROPELLER VIBRATION, AN ULTRASONIC EXAMINATION WAS CARRIED OUT ON THE PROPELLER HUB. ON	E CRACK LIKEDEFECT WAS DETECTED ADJACENT TO A THREADED INSERT HOLE. THE CRACK WAS LOCATED AT A DEPTH OF 13MM (0.512IN) A	ND HAD A LENGTH OFAPPROXIMATELY 13MM (0.512IN).				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2003021000066	20030210	00066	NM  	2003	2	10	AUS20021484      	1	20021230	G	3240	DSC252A40230	HOSE            	            	            	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	LANDING GEAR BRA	RUPTURED        	W			    	K	E	 	 	NONE                    	ENGINE SHUTDOWN         			K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 	 									(AUS) NO3 BRAKE PACK HYDRAULIC HOSE RUPTURED. LOSS OF NO2 SYSTEMHYDRAULIC FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002012800064	20020128	00064	CE  	2002	1	28	B3OR20020001     	1	20020122	G	2910	99121943	SWITCH          			CESSNA	500   	550         	2076604	CE  										HYD SYSTEM	STUCK           	B			B3OR	D				RETURN TO BLOCK         				P			NO WARNING INDICATION     			TX	TAXI/GRND HDL  	1			SW	03	26494	550  	130  			5500605				A GROUND RUN WAS PERFORMED ON THE AIRCRAFT PRIOR TO A SCHEDULED LAUNCH.UPON ENGINE SHUTDOWN THE MECHANIC NOTICED THAT TH	E "HYDRAULIC PRESSURE LOW" LIGHT ON THE RIGHT HAND ENGINE DID NOT ILLUMINATE.DURING TROUBLE-SHOOTING, IT WAS DICOVERED T	HAT THE RIGHT HAND HYDRAULIC FLOW SWITCH WAS STICKING, AND CAUSING AN INTERMITTENT INDICATION ON THE CAUTION PANEL.THE F	LOW SWITCH WAS REPLACED AND THE AIRCRAFT PUT BACK INTO SERVICE.			1	L	7	2 	4F			 	A22CE   					 
2002020500047	20020205	00047	CE  	2002	2	5	B3OR20020002     	1	20020201	G	7170	555501125	DRAIN VALVE     			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	CRACKED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26494					5500605				DURING A PHASE 1 & 2 INSPECTION, THE ENGINES WERE DE-COWLED FOR THE OIL FILTER CLEANING ITEM. A MECHANIC NOTICED SOME FU	EL RESIDUE AROUND THE FUEL DRAIN "EPA" CAN. UPON INSPECTION THE CAN WAS FOUND TO HAVE A MOUNTING BRACKET BROKEN OFF OF I	T. THE BREAK WAS WHERE THE BRACKET WAS WELDED TO THE CAN AND IT ACTUALLY WAS THE CAN ITSELF THAT HAD BROKEN, NOT THE BRA	CKET. THE OPPOSITE ENGINE WAS INSPECTED AND IT HAD A SIMILAR CRACK. IN RESEARCHING THIS PART, IT WAS FOUND THAT IN THE P	AST YEAR, THIS PART HAD BEEN REPLACED ON 6 OTHER ENGINES FOR THE SAME REASON AT THIS LOCATION. THIS DEFINITELY SEEMS TO 	BE AN ITEM THAT DESERVES MORE ATTENTION WHEN INSPECTING THE ENGINES.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002020800027	20020208	00027	CE  	2002	2	8	B3OR20020003     	1	20020205	G	3242	215286	STATOR          			CESSNA	500   	550         	2076604	CE  										BRAKE	CRACKED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26494					5500605				ACFT WAS INDUCTED INTO A 1 & 2 AND 5 A&B INSPECTION.  DURING INSPECTION DISCOVERED THE LT MLG BRAKE ASSY HAD A CRACK IN 	ONE OF THE STATOR DISCS.  BRAKE ASSY WAS RECEIVED FROM OUR PARTS DEPT HAD ABNORMAL WEAR ON THE WEAR PLATES & LININGS.  B	RAKE ASSY WAS REPAIRED AT AN OVERHAUL SHOP FOR A DAMAGED HOUSING.  HOUSING WAS NOT STAMPED WITH S/B, THE FORM 8130 HAS N	O RECORD OF LANDINGS/TIME IN SERVICE OF BRAKE ASSY OR A RECORD OF COMPLIANCE WITH BF GOODRICH S/B 2-1528-32-2, LANDING G	EAR BRAKE ASSEMBLY POSSIBLE CRACKED STATOR DISKS.		1	L	7	2 	4F			 	A22CE   					 
2002031300063	20020313	00063	NE  	2002	3	13	B3OR20020005     	2	20020202	G	7270	310863201	DUCT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENG BYPASS	CRACKED         	B			B3OR	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	03	26494	8237 	1390 			5500605	PCE71394			AIRCRAFT WAS INDUCTED INTO A PHASE1,2,5A & B INSPECTION.DURING THE INSPECTION OF THE NUMBER 2 ENGINE, THE FRONT BY-PASS 	DUCT WAS FOUND CRACKED AND A PIECE MISSING FROM IT. THE DUCT WAS REMOVED AND REPLACED WITH A SERVICEABLE DUCT.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002071900142	20020719	00142	EU  	2002	7	19	B3OR20020010     	1	20020528	G	6220	707A33640046	FREQ ADAPTER    			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204X	985  				3099				DURING A 500 HOUR INSPECTION, THE M/R HEAD WAS DISSASSEMBLED. THE FREQUENCY ADAPTERS WERE REMOVED FOR INSPECTION.  ATTEM	PTS TO REMOVE THE BEARING BY PUSHING OR TAPPING LIGHTLY FAILED. THE DECISION WAS MADE TO CHANGE THE ADAPTER AND BEARING.	   THE BEARING WAS FINALLY REMOVED BY CUTTING THE FREQUENCY ADAPTER IN HALF. UPON REMOVAL OF THE BEARING, CORROSION WAS 	FOUND ON ALL OF THE MATING SURFACES. ALL THREE ADAPTERS WERE IN THE SAME CONDITION.			1	G	7	1 	3U			 	H9EU    					 
2002081300073	20020813	00073	EU  	2002	8	13	B3OR20020011     	1	20020710	G	6420	355A09103601	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	CRACKED         	B			U0SM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J	483  				3118				THE TAIL ROTOR WAS REMOVED FOR THE 500 HOUR INSPECTION AND DURING INSPECTION, THE LAMINATED HALF BEARINGS WERE FOUND TO 	BE CRACKED.  THE RUBBER IN THE BEARINGS WAS SPLIT BEYOND LIMITS. IT IS TO BE NOTED THAT THIS AIRCRAFT SPENDS MOST OF IT'	S TIME OUTSIDE ON THE RAMP AND THE DETERIORATION IS PROBABLY DUE TO WEATHER EFFECTS.				1	G	7	1 	3U			 	H9EU    					 
2002081300077	20020813	00077	EU  	2002	8	13	B3OR20020014     	1	20020529	G	6310	350A35110205	HOUSING         			SNIAS 	350   	AS350B2     	8680813	EU  										MGB COUPLING	WORN            	B			U0SM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204X	986  				3099				THE ENGINE TO MAIN GEAR BOX GIMBAL JOINT , WHICH HOUSES THE DRIVE SHAFT, HAD EXCESSIVE PLAY. UPON INSPECTION AT THE 500 	HOUR, THE GIMBAL RING AND HOUSING WERE MEASURED AND FOUND TO BE OUT OF LIMITS AT THE GIMBAL PINS.  A TECH REP WAS CONTAC	TED AND  SUGGESTED THAT WE LOOK AT THE LEFT FOWARD MAIN GEAR BOX CROSSBEAM SUPPORT SHOCK MOUNT FOR THE CAUSE OF THIS PRO	BLEM. HE WAS CORRECT. THE LAMINATED MOUNT WAS DETERIORATED. WHEN THE CROSSBEAM WAS REMOVED, FOUND THE LAMINATED MOUNT HA	D BEEN MOVING AND CAUSED CORROSION ON THE BEAM. THE RUBBER PORTION OF THE MOUNT APPEARS TO HAVE BEEN DAMAGED BY OILS.		1	G	7	1 	3U			 	H9EU    					 
2003070700198	20030707	00198	EU  	2003	7	7	B3OR20020019     	1	20020906	G	2170	900A4031	EVAPORATOR      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ZONE 100	BROKEN          	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204X					3099	9570			CRACKED HOUSINGS THAT CAUSE BLOWER MOTORS TO BECOME DISLODGED IN THE HOUSING, CAUSING BLOWER CAGES TO RUB ON THE HOUSING	 AND HOUSINGS TO BREAK APART.  EVENTUAL FAILURE OF ENTIRE ASSEMBLY AND BLOWER MOTOR RENDERING THE AIRCONDITIONING SYSTEM	 INOPERATIVE. ONE OF HOUSING PARTS OR BLOWER CAGE PIECES COULD FALL OFF AND BECOME LODGED IN LT TAIL ROTOR CONTROL PEDDL	ES. THIS IS POSSIBLE DUE TO LOCATION OF EVAPORATOR ASSY,  IT IS ALMOST DIRECTLY OVER TAIL ROTOR CONTROL PEDDLES ON L/H S	IDE OF COCKPIT.  THIS HAS TO BE PAID EVERYTIME ONE BREAKS BECAUSE UNITS ARE NOT FIELD REPAIRABLE, THEY HAVE TO BE RETURN	ED TO MANUFACTURER FOR REPAIR OR REPLACEMENT.  WE WOULD LIKE TO RECOMEND THAT EVAPORATOR ASSY.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003070700199	20030707	00199	CE  	2003	7	7	B3OR20020020     	1	20021009	G	3230	NAS464P4A10	BOLT            	CESSNA      		CESSNA	500   	550         	2076604	CE  										TORQUE TUBE	BROKEN          	B			B3OR	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			SW	03	26494	8533 			NA	5500605				AFTER TAKEOFF, PILOT NOTICED NOISE IN NOSE AREA, WIND NOISE IN COCKPIT.  CREW WAS ABLE TO SEE NOSE GEAR DOORS WERE OPEN 	AND STEADY. REDUCED SPEED AND LOWERED LANDING GEAR WITH NO PROBLEMS.  DOORS REMAINED OPEN AND STEADY.  A/C LANDED WITHOU	T MISHAP. FOUND THAT BOLT HAD BROKEN THAT HOLDS DOOR BELLCRANK/TORQUE TUBE IN POSITION. BOLT IS AT PIVOT POINT ON RT SID	E OF A/C.  WHEN TORQUE TUBE WAS REMOVED, CRACK WAS FOUND BUT DETERMINED THAT THIS WAS NOT RELATED AND HAD BEEN THERE A L	ONG TIME.  BOLT FOUND BREAK WAS TYPICAL OF OVER TORQUEING. BREAK WAS AT FIRST THREAD, HAD NO STRESS INDICATIONS. BOLT IS	 CLOSE TOLERANCE BOLT, NORMALLY HAS SHEARING LOAD IN  INSTALLATION.  BOLT WAS NOT SHEARED. REPLACED BOTH BOLTS AND TORQU	1	L	7	2 	4F			 	A22CE   					 
2003052900068	20030529	00068	EU  	2003	5	29	BAQA081077       	1	20020927	G	6330	L633M2001105	MOUNT           			UROCOP	EC135 	EC135T1     	5620026	EU  										MAIN ROTOR	DAMAGED         	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	575ME	1655 				0157				TRANSMISSION MOUNT BAD. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H88EU   					 
2002121700070	20021217	00070		2002	12	17	BAQA081596       	4	20021209	G	3421	4021541791	INDICATOR       			BOLKMS	117   	BK117A1     	5626010	EU  										ART HORIZON	CONTAMINATED    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	955ME	2118 				7243				ARTIFICIAL HORIZON INDICATOR GLASS FOGGED. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H13EU   					 
2003010300011	20030103	00011	EU  	2003	1	3	BAQA082149       	1	20021220	G	6240	117945641	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										MAST MOMENT	MALFUNCTIONED   	H			BAQA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	952CJ	574  				7052				MAST MOMENT INDICATOR POPS CIRCUIT BREAKER. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H13EU   					 
2002102300129	20021023	00129	CE  	2002	10	23	BN001            	1	20021017	G	5311	50420013944	STRAP           	BEECH       		BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FRAME	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	7232R	7917 				BL69				UPON REMOVAL OF AIRCRAFT INTERIOR TO TROUBLESHOOT WIRING PROBLEMS, TWO STRAP ASSEMBLIES ON THE RT SIDE OF THE FUSELAGE A	T F.S. 227.0 AND 246.0, BUTTOCK LINE 119.0 WERE FOUND COMPLETELY CRACKED THROUGH.   THE STRAP ASSEMBLY AT F.S. 246.0.  T	HESE AREAS WOULD NOT NORMALLY BE INSPECTED UNTIL 10,000 CYCLES.  RAYTHEON HAS CONFIRMED ONE OTHER SIMILAR INCIDENT ON TH	E BL MODEL AIRCRAFT EQUIPPED WITH A CARGO DOOR.  THERE IS NO EVIDENCE OF PREVIOUS DAMAGE OR ABNORMAL OPERATION IN THE AI	RCRAFT LOGBOOK.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002091000164	20020910	00164	SO  	2002	9	10	C41346022160     	1	20020909	G	3320		BULB            			GULSTM	G1159 	GIV         	3980115	SO  										CABIN HEADLINER	DAMAGED         	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	11	104AR					1346				OUT OF 8 BAD CABIN LIGHT BULBS, THREE WERE BURNT THROUGH OR SHOWING SIGNS OF BURNING THROUGH THE BULB CASE. TECHNICIAN S	TATED AN OPERATING VOLTAGE OF 600 VAC AND CONSIDERS THIS A SIGNIFICANT PROBLEM.					2	L	7	2 	4F			RT	A12EA   					 
2002021400015	20020214	00015	CE  	2002	2	14	CA020102002      	1	20020102	G	3240		STATOR          	BFGOODRICH  	215286      	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1411					(CAN) DISASSEMBLED BRAKE UNIT AND FOUND STATOR DISC P/N 133-89302 CHG "B" BROKEN.  (SEE ATTACHED PHOTO'S).						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002021400051	20020214	00051	NM  	2002	2	14	CA020104006      	1	20020102	G	3213		COLLAR          			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1F5   	41532	EA  					MLG	CRACKED         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA											(CAN) PILOT LANDED NORMAL: WHILE ROLLING ON RUNWAY AIRCRAF WENT RIGHT AND PILOT HAS A HARD TIME CONTROLLING AIRCRAFT BUT	 MANAGED TO GET AIRCRAFT STOPPED. SHUT DOWN ENGINES AND GOT OUT TO INVESTIGATE; NOTICED RIGHT MAIN GEAR TIRE 90 DEGREES 	FROM NORMAL WITH HELP GOT AIRCRAFT TO TARMAC.UNABLE TO GIVE PART NUMBER AS THERE IS NO FURTHER BREAKDOWN IN PARTS MANUAL	.			1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2002021500017	20020215	00017	SW  	2002	2	15	CA020104019      	1	20020104	G	5310	0354130	TUBE            			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C212   	GL  	FUSELAGE	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   WHEN INTERIOR OF THE A/C WAS REMOVED IT WAS NOTICED THAT THE TUBULAR STRUCTURE WELDED JOINT ON THE LT SIDE JUST 	FWD OF SPAR ON DIAGONAL BRACE BELOW THE FRONT OF REAR WINDOW IS MISSING A WELD.  IN THE SAME AREA NOTICED A CLUSTER GUSS	ETS WITH INCOMPLETE WELDS.				1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2002021500073	20020215	00073	CE  	2002	2	15	CA020111001      	1	20020110	G	3260	1003810061	SWITCH          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					NLG	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN)  PILOT SELECTED GEAR DOWN AND GOT NO NOSE GREEN LIGHT.  PILOT WAS READY TO DO A EMERGENCY EXTENTION WHEN THE GREEN	 LIGHT CAME ON.  MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002021500095	20020215	00095	SW  	2002	2	15	CA020114002      	1	20020108	G	6720	206010793101	PITCH LINK      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   FOUR CRACKS FOUND TWO ON EACH END OF PITCH LINK SIMILAR TO THOSE DESCRIBED IN ASB 206-87-39 AND OSN 206-99-36.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002022800003	20020228	00003		2002	2	28	CA020115001      	4	20020109	G	3425		SYMBOL GENERATOR	BENDIX      	0660402111  	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	INTERNAL	INOPERATIVE     	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA						4481					(CAN) WHEN A/C POWERED UP, LOWER PILOT'S EFIS DISPLAY REMAINED BLANK. LOWER CO-PILOTS EFIS DISPLAY SWITCHED FOR TROUBLE 	SHOOTING. DISPLAY ALSO REMAINED BLANK. WHEN DISPLAY RETURNED TO IT'S ORIG POSSITION, IT REMAINEDBLANK AS WELL. IT DETERM	INED THROUGH FURTHER TROUBLE SHOOTING THAT PILOT'S SG-465 SYMBOL GEN P/N 066-04021-11-11, S/N 4481, DEFECTIVE. IT CAUSED	 INTERNAL DAMAGE TO LOWER PILOT'S EFIS DISPLAY, P/N 066-03125-2500, S/N 3486. WHEN CO-PILOT'S EFIS DISPLAY INST IN POSSI	TION, IT TOO DAMAGED BY DEFECTIVE SYMBOL GEN. WHEN EFIS DISPLAY RETURNED TO IT'S ORIG POSSITION, IT IN TURN DAMAGED CO-P	ILOTS SYMBOL GEN,S/N 3354. PI LOT'S SYMBOL GEN&LOWER EFIS DISPLAY, AND	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021500103	20020215	00103	CE  	2002	2	15	CA020116002      	1	20020104	G	2710	05341251	BUSHING         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					BELLCRANK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13746								(CAN) BUSHING WAS FOUND TO BE ROTATING IN BELLCRANK ASSEMBLY.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002021500104	20020215	00104	CE  	2002	2	15	CA020116004      	1	20020104	G	5511	053200198	SPAR            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  CRACK WAS FOUND DURING A SCHEDULED INSPECTION OF THE AIRCRAFT, IN THE AREA OF THE FRONT SPAR OF THE STABILIZER. A	T THE LIGHTENING HOLE BETWEEN THE TWO NOSE RIBS.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002021500105	20020215	00105	SW  	2002	2	15	CA020116005      	1	20020108	G	3220	AN5C32A	BOLT            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  					TAIL WHEEL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING THE ANNUAL INSPECTION MAINTENANCE REMOVED BOLT AN5C-32A, AS PER INSPECTION SCHEDULE. THEY FOUND THAT THE B	OLT WAS BADLY WORN AND THAT THREADS WERE DAMAGED.					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2002021500107	20020215	00107	SO  	2002	2	15	CA020116008      	1	20020105	G	3244	09231500	TIRE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG	PUNCTURED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) NOSE WHEEL TIRE BECAME FLAT DURING LANDING, CAUSING A SHIMMY NOTICEABLE TO PILOTS.  AIRCRAFT WAS BROUGHT TO A STOP	 ON RUNWAY, WHERE IT WAS TOWED TO MAINTENANCE FACILITY.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002021500108	20020215	00108	SO  	2002	2	15	CA020117001      	1	20020114	G	3244	0923150	TIRE            			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					NLG	PUNCTURED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN)  NOSE WHEEL TIRE BECAME FLAT DURING LANDING, CAUSING A SHIMMY NOTICEABLE TO PILOTS.						1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2002021900070	20020219	00070	NE  	2002	2	19	CA020117012      	2	20020111	G	7412		EXCITER         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	IGNITION SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN)  PILOT WENT TO START ENGINE AND HAD NO LIGHT OFF.TRIED TWICE TO START ENGINE AND HAD NO LIGHT OFF.  IGNITION EXCIT	OR BOX WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.NOTE:  THIS IS TYPICAL FOR PILATUS IGNITOR BOX.  THE SAME BOX WILL 	LAST 2-3 TIMES LONGER ON A BEECH 99 OR A100.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021900124	20020219	00124	EU  	2002	2	19	CA020117016      	1	20020102	G	2700		CONTROL UNIT    			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					COCKPIT	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN)   AIRCRAFT RETURNED BACK TO GATE AFTER PUSH BACK. NO ECAM INDICATION OF RUDDER TRIM AND NO PEDESTAL INDICATION. TR	OUBLESHOOTING WAS CARRIED OUT PER CATTS ,					2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002021900131	20020219	00131	EU  	2002	2	19	CA020118006      	1	20020117	G	5230		HANDLE          			AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     	 	NE  					CARGO DOOR	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			24873	24873							(CAN) AT APPRXIMATELY 10,000 FT ALTITUDE THE FWD CARGO DOOR INDICATED UNSAFE ON ECAM. THE AIRCRAFT DIVERTED AND WAS INSP	ECTED BY A COMPANY ACA. THE DOOR HANDLE WAS FOUND TO BE OUT OF THE DETENT BY ABOUT 1/4 OF AN INCH. THE HANDLE ASSY AND D	OOR LOCKING MECHANISM WAS INSPECTED AND FOUND SERVICEABLE. THE INDICATING SYSTEM WAS CHECKED AND FOUND SERVICEABLE. AIRB	US HAS BEEN ADVISED AND IS UNDER INVESTAGATION.			2	L	7	2 	4F	4	F	RT	A28NM   	E311NE				 
2002021900133	20020219	00133	SW  	2002	2	19	CA020118009      	1	20020110	G	7910	2765030101	OIL TANK        			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AN OIL LEAK WAS NOTED DURING A BASE INSPECTION. ON INVESTIGATION A .75 INCH LONG CRACK WAS FOUND IN THE SIDE WALL 	OF THE OIL TANK BETWEEN THE FILLER NECK BOSS AND THE SIGHT GAUGE BOSS. THE TWO BOSSES ARE CLOSE TO EACH OTHER ON THE SID	E OF THE TANK. THE CRACK FOLLOWED THE CURVE OF THE SIGHT GAUGE BOSS WELD BAND JUST OUTSIDE OF THE EDGE OF THE WELD. THE 	TANK WAS REMOVED REPAIRED AND REINSTALLED.			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2002021900134	20020219	00134	SO  	2002	2	19	CA020118010      	1	20020102	G	7930	5581802	TRANSDUCER      			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					OIL PRESSURE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) OIL PRESSURE GAUGE UNRELIABLE ON RIGHT ENGINE. AIRCRAFT ON FLIGHT FROM YXU TO YTZ, WHEN RIGHT ENGINE OIL PRESSURE 	GAUGE STARTED TO INDICATE OIL PRESSURE LOSS. ALL OTHER ENGINE PARAMETERS NORMAL. PRECAUTIONARY ENGINE SHUTDOWN WAS CARRI	ED OUT AND AIRCRAFT CONTINUED TO YTZ. TROUBLESHOOTING CARRIED OUT IAW PT6 MM AND OIL PRESSURE TRANSDUCER WASFOUND UNSERV	ICEABLE.OIL PRESSURE TRANSMITTER REPLACED AND ENGINE RUN C/W. ALL INDICATION NORMAL.			1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2002021900135	20020219	00135	CE  	2002	2	19	CA020118011      	1	20020108	G	2731	26612151	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ELEVATOR TRIM	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF FROM YHM, THE AIRCRAFT LOST ELEVATOR TRIM ELECTRICAL AND MANUAL CONTROL AND THE AUTOPILOT FAILED. TH	E AIRCRAFT RETURNED TO THE AIRPORT. MAINTENANCE INVESTIGAITON FOUND ONE OF THE TWO RODS ON THE LT ELEVATOR TRIM ACTUATOR	 WAS BINDING A LITTLE WHEN THE ELEVATOR WAS IN THE NEUTRAL POSITION, BUT FREE WHEN THE ELEVATOR WAS DEFLECTED UP OR DOWN	. THE ONE ROD WAS ADJUSTED 1/14 OF A TURN - SYSTEM TESTED AND FOUND TO BE FREE THROUGH THE RANGE OF TRAVEL OF THE ELEVAT	OR.THE ACTUATOR HAD RECENTLY BEEN REMOVED FOR OVERHAULED AND REINSTALLED.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002021900136	20020219	00136	SW  	2002	2	19	CA020121001      	1	20020117	G	5311	71470101L	FRAME           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					FUSELAGE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) -TUBE FOUND BROKEN THROUGH NEAR WELD, AT FWD ENDOF LT LANDING GEAR FITTING.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021900137	20020219	00137	NM  	2002	2	19	CA020121003      	1	20020105	G	2781	Y35A	TRANSDUCER      			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					FLAP / SLATS	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN)   EICAS MESSAGE FOR FLAP / SLAT ELEC. DISPLAYED.REPLACED THE ROTARY DIFFERENTIAL TRANSDUCER  M603 AND ADJUSTED AS 	PER AMM 27-51-26-424-020. FOUND SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2002021900138	20020219	00138	EU  	2002	2	19	CA020121006      	1	20020102	G	3260		SENSOR          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					MLG	CONTAMINATED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) AIR TURN BACK TO MONTREAL DUE TO MAIN LANDING DOOR NOT SHOWING PROPERLY LATCHED.   AFTER VERIFICATION,  FOUND TO B	E THE SENSORS CONTAMINATED WITH GREASE AFTER AN OVERNIGHT CHECK (OVERGREASED).SENSORS CLEANED, GEAR SWING COMPLETED, SYS	TEMM FOUND SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002022000001	20020220	00001	EA  	2002	2	20	CA020121011      	2	20020107	G	7230		COMPRESSOR      								PWA   	PT6   	PT6A20      	52043	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE SENT FOR INVESTIGATION & REPAIR AFTER IT FOUND THAT ENGINE MAKING RUBBING NOISE COMING FROM COMPRESSOR SECT	ION WHILE SCHEDULE HSI BEING PERFORMED.  THE COMPRESSOR HAD SUFFERED EXTENSIVE DAMAGE.  DAMAGE STARTED WITH RUBBING AT 1	ST STAGE COMPRESSOR STATOR & DISK SPACER&CONTINUED DOWNSTREAM TO IMPELLER. 1ST & 2ND STAGE COMPRESSOR SPACERS HAD RUBBIN	G MARKS ON 180 DEG. OF SURFACE AREA. 3RD STAGE COMPRESSOR SPACER HAD SEVERE DAMAGE TO FRONT RIM. IT HAD HEAVY RUBBING MA	RKS & MISSING SUBSTANTIAL AMOUNT OF MATERIAL. COMPRESSOR 3RD STAGE BLADES & STATOR HAD EXTENSIVE DAMAGE. IMPELLER & IMPE	LLER HOUSING HAD RECD SECONDARY IMPACT DAMAGE FROM DEBRIS FROM THE  MATERIAL LOST FROM 3D STAGE COMPRESSOR SPAC						3	T			E4EA				 
2002022000003	20020220	00003	EA  	2002	2	20	CA020122001      	2	20020114	G	7414		GEAR            	BENDIX      		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAGNETO	STRIPPED        	W				E				ENGINE SHUTDOWN         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TX	TAXI/GRND HDL  	1			CA						K049802ER					(CAN) THE AIRCRAFT RAN ROUGH ON L/H MAGNETO (APPROXIMATELY 200 RPM MAGNETO DROP). LT MAG WAS REMOVED AND FOUND TO HAVE 8	-10 TEETH MISSING FROM GEAR (NYLON) WHEN VIEWED THROUGH TIMING WINDOW. MAG WAS REPLACED AND THE AIRCRAFT RETURNED TO SER	VICE.				1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002022000004	20020220	00004	SO  	2002	2	20	CA020122002      	1	20020116	G	2910		HYDRAULIC SYSTEM			PIPER 	PA44  	PA44180     	7104402	SO  										MAIN SYSTEM	CONTAMINATED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN)   DURING THE TRAINING FLIGHT THE PILOT NOTICED THE GEAR UNSAFE LIGHT WAS STILL ILLUMINATED.   NOTICED THE NOSE LAN	DING GEAR ONLY PARTIALLY RETRACTED,  HE SELECTED GEAR DOWN AND THE 3 GEAR DOWN INDICATION LIGHTS ILLUMINATED WITH GEAR U	NSAFE LIGHT EXTINGUISHED. PILOT LANDED THE AIRCRAFT WITHOUT INCIDENT.  A VISUAL CHECK OF THE HYDRAULIC FLUID LEVEL IN TH	E UNDERCARRIAGE HYDRAULIC PUMP RESERVOIR SHOWED THAT THE QUANTITY LEVEL BELOW LIMITS AND THE FLUID WAS VERY DARK IN COLO	UR.  THE HYDRAULIC PUMP AND MOTOR ASSEMBLY WERE DRAINED,  FLUSHED WITH CLEAN NEW FLUID.  THE HYDRAULIC PUMP AND MOTOR AS	SEMBLY WERE REINSTALLED AND FLUID LEVEL TOPPED UP AND TEST CHECKED WITHOUT INCIDENT AND AIRCRAFT RETURNED TO SERVICE.	1	L	7	2 	3O			 	A19S0   					 
2002022000006	20020220	00006	WP  	2002	2	20	CA020122005      	1	20020121	G	6310	C1683	RETAINER        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					M/R CLUTCH	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)  CLUTCH WAS REMOVED FROM SERVICE DUE TO OIL LEAK.INVESTIGATION REVEALED THAT SEAL RETAINER PLATE EAR APPEARRED TO 	BE CRACKED.  RETAINER WAS REMOVED AND EAR WAS FOUND TO BE NO LONGER ATTACHED TO RETAINER PLATE.NO OTHER CRACKS COULD BE 	FOUND IN RETAINER PLATE OR ON OPPOSITE RETAINER. RETAINER PLATE WILL BE REPLACED WITH NEW.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002022000007	20020220	00007	WP  	2002	2	20	CA020122006      	1	20020121	G	6310	C1883	SPRAG CLUTCH    			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CLUTCH WAS REMOVED FROM SERVICE DUE TO AN OIL LEAK.  UPON DISSASSEMBLY THE SPRAG WAS INSPECTED AND THE CAGE FOUND 	CRACKED.THE CRACK WAS BETWEEN TWO WINDOWS RUNNING FROM THE CORNERS. SPRAG WILL BE REPLACED WITH NEW.					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002022000008	20020220	00008	EA  	2002	2	20	CA020123001      	1	20020123	G	2897	601R571351	WIRE HARNESS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					WING FUEL CELL	CHAFED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN)    WHILE IN FLIGHT, CREW REPORTED THAT THE LEFT FUEL QTY INDICATION AND TOTAL FUEL QTY INDICATION WENT TO DASHES. 	 FUEL QTY INDICATION WAS DEFERRED PER MEL AND MLIS WRE USED TO CHECK FUEL QUANTITY BEFORE EACH FLIGHT.  UPON FURTHER INV	ESTIGATION,  MAINTENANCE DISCOVERED THAT THE WIRE HARNESS FOR THE NR 3 FUEL QTY PROBE WAS CHAFING ON THE FUEL DAM LOCATE	D INSIDE THE LEFT TANK. INSPECTION OF THE RT TANK ALSO DISCOVERED THAT THIS SAME CHAFING WAS PRESENT.  BOTH LEFT AND RIG	HT HARNESSES WERE REPLACED. THE HARNESS WAS REPOSITIONED SO AS NOT TO COME IN CONTACT WITH THE FUEL TANK.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002022000009	20020220	00009	SO  	2002	2	20	CA020123002      	1	20020122	G	3245		TIRE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG	PUNCTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOTS VISUALLY NOTICED THAT THE NOSE WHEEL TIRE WAS FLAT AFTER THE AIRCRAFT WAS LANDED AND THE ENGINES WERE SHUT-	DOWN.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002022000010	20020220	00010	EA  	2002	2	20	CA020123003      	2	20020116	G	7210		GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					REDUCTION GEAR	CONTAMINATED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			14924								(CAN)   IN CRUISE FLIGHT THE PILOT THE PILOT NOTED THE C-BOX CHIP LIGHT FLICKER FAINTLY FOLLOWED SHORTLY BY THE C-BOX OI	L PRESSURE CAUTION LIGHT ILLUMINATING.C-BOX OIL PRESSURE WAS OBSERVED DROPPING AND AN UNSCHEDULED BUT NORMAL LANDING PRO	CEDURE WAS CARRIED OUT.  AFTER LANDING THE C-BOX OIL PRESSURE WAS OBSERVED TO DROP TO ZERO AND THE ENGINES WERE SHUT DOW	N. NO EXTERNAL LEAKS WERE FOUND.  AN ACCUMULATION OF METAL WAS FOUND ON THE REDUCTION (C-BOX) CHIP DETECTOR AND IN THE R	EDUCTION GEARBOX OIL FILTER.		1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002022000011	20020220	00011	NE  	2002	2	20	CA020123004      	1	20020122	G	2913		SHAFT           	ABEX        		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					HYD PUMP	SHEARED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						195853					(CAN) INFLIGHT INDICATION OF PRESSURE LOSS NR 1 SYSTEM. INSPECTION REVEALED PUMP SHAFT SHEARED AND BRASS PARTICLES IN FI	LTER.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002022000012	20020220	00012	EA  	2002	2	20	CA020124002      	1	20020123	G	3040	M7A16	WIRE            			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  					WINDSHIELD WIPER	SHORTED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) WIRE INSULATION WAS FOUND BURNED AND APPEARED TO HAVE SHORTED OUT ON OVERHEAD SWITCH PANEL IN FLIGHT COMPARTMENT, 	WHICH CAUSED ELECTRICAL BURNING ODOR IN THE FLIGHT DECK.					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2002022000014	20020220	00014	EA  	2002	2	20	CA020124004      	1	20020115	G	2161	8161014	CONTROLLER      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					CABIN TEMP	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) SMOKE IN CABIN DUE TO RT PACK OVER TEMP IN AUTO, REVERTED TO MANUAL TEMPERATURE CONTROL. FOUND TO BE THE TEMP CONT	ROLLER AT FAULT. REPLACED THE TEMPERATURE CONTROLLER.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002022000015	20020220	00015	EA  	2002	2	20	CA020124005      	1	20020114	G	3234	7179015	CONTROL HANDLE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) GEAR DISAGREE LIGHT ON APPROACH INTO WASHINGTON. CREW CONDUCTED A GO AROUND THEN CARRIED OUT A MANUAL EXTENSION. A	FTER LANDING THE NOSE STEERING WAS INOPERATIVE. FOUND TO BE THE LANDING CONTROL LEVER AT FAULT. REPLACED LANDNG CONTROL 	LEVER, OPERATIONAL CHECK CARRIED OUT, SYSTEM FOUND SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002022000016	20020220	00016	NM  	2002	2	20	CA020124006      	1	20020106	G	2821	AC92272080D2A	FILTER          			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					FUEL SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) FLIGHT CREW REPORT THAT THEY HAD A FUEL FILTER LIGHT ON EICAS FOR BOTH ENGINES. FOUND TO BE FINE MANUFACTURING DEB	RIS (NEW AIRCRAFT). REPLACED TWO FILTERS AND DRAIN ALL RESERVOIRS, GROUND RUN AND LEAK CHECK CARRIED OUT. FLEET MANAGEME	NT REQUEST TO HAVE BOTH FILTERS REPLACED AFTER 5 FLIGHT CYCLES.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2002022000017	20020220	00017	NM  	2002	2	20	CA020124007      	1	20020111	G	2910	AE83580K	COUPLING        			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					HYD LINE	BROKEN          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF FROM TORONTO AS FLAPS WERE RETRACTING FROM 1 TO UP, CENTRE HYDRAULIC QUANTITY AND C HYDRAULIC SYSTEM	 PRESSURE DISPLAYED EICAS MESSAGES / CAUTIONS AND HYDRAULIC PRESS LIGHTS ANNUNCIATED, THE AIRCRAFT RETURNED TO TORONTO U	SING ALTERNATE FLAPS/GEAR EXTENSION.FOUND AIR DRIVEN PUMP PRESSURE LINE COUPLING BROKEN.REPLACED ADP PRESSURE LINE COUPL	ING, CASE DRAIN FILTER CHECKED FOR CONTAMINATION AND FOUND CLEAN. SYSTEM LEAK CHECKED AND OPERATIONAL CHECK ALSO CARRIED	 OUT, AIRCRAFT FOUND SERVICEABLE.		2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2002022000018	20020220	00018		2002	2	20	CA020124008      	4	20020118	G	2330	9700029005	CONTROL UNIT    			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					SMU	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B	A		SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		NR	NOT REPORTED   	1			CA											(CAN) ON THE PRE-DEPARTURE CHECK THE SMU (SYSTEM MANAGEMENT UNIT) CAUGHT ON FIRE NO EXTERNAL FLAME BUT FLAME AND WITHIN 	THE UNIT AND SMOKE COMING OUT OF THE UNIT.THE UNIT WILL HAVE A STRIP REPORT DONE AT THE MANUFACTURER FOR ANALYSIS. UNIT 	REPLACED.				1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002022000019	20020220	00019	SW  	2002	2	20	CA020124009      	1	20020123	G	1400	AN313	BOLT            			SWRNGN	SA226 	SA226TC     	8780404	SW  										MLG	WORN            	W				L				ABORTED APPROACH        				W	J		INADEQUATE Q C            	WARNING INDICATION        		AP	APPROACH       	1			CA			15000	15000							(CAN) DURING APPROACH FOR LDG, CREW SELECTED GEAR DOWN&GOT 2 MAIN GEAR RED IND.S, THEN 2 MAIN GEAR GREEN IND.S WITH NO N	OSEGEAR IND.. CREW BROKE OFF APPROACH & CYCLED GEAR COUPLE OF TIMES WITH NO IMPROVEMENT.AS SOON AS EMERG EXTENSION PERFO	RMED, GEAR CAME DOWN NORMALLY,&NORMAL LDG MADE. INVEST. REVEALED THAT SLIGHT WEAR IN DIAMETER OF BOLT, P/N AN3-13 INST I	N UPLOCK HOOK ASSY P/N 27-52004-017, (TOR QUE TUBE) ALLOWED SEVERAL DEGS ANGULAR PLAY BETWEEN HOOK ASSY&ACTUATION ARM AS	SY P/N 27-52000-015. PLAY PREVENTED SUFFICIENT RETRACTION OF NOSEGEAR UPLOCK HOOK TO ALLOW NOSEGEAR TO RELEASE. MANUAL E	XTENSION SYSTEM BYPASSED ASSY. BOLT REPLA	2	L	7	2 	4T			RT	A8SW    					 
2002022000023	20020220	00023	SO  	2002	2	20	CA020125001      	1	20020123	G	2910	41	HYDRAULIC SYSTEM	CLEVELANDXXX	30142       	PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					FLUID	CONTAMINATED    	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) LEFT BRAKE WAS DRAGGING DURING AIRCRAFT TAXIING. THE AIRCRAFT WAS TOWED TO HANGAR WHERE THE BRAKE SYSTEM WAS FOUND	 WORKING NORMALLY.  THE BRAKE SYSTEM (CALIPER & MASTER CYLINDER) WAS DISASSEMBLED AND WATER CONTAMINATION WAS FOUND PRES	ENT IN THE HYDRAULIC FLUID. SYTEM WAS DRAINED, CLEANED AND REPLENISHED WITH NEW HYDRAULIC FLUID. NEW O-RINGS WERE INSTAL	LED. THE BRAKE SYSTEM WAS BLED AND TESTED OK.			1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2002022000024	20020220	00024	GL  	2002	2	20	CA020125002      	2	20020104	G	7210	6890493	BEARING         	ALLSN       	6894171     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	CRACKED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						CAG35537					(CAN) THIS AIRCRAFT RUNNING NORMAL. PILOT ON START HEARD A LOUD SQUEELING NOISE, THEN GOT A CHIP LITE. MAINTENANCE FOUND	 HUGE AMOUNTS OF METAL ON BOTH PLUGS. PROBLEM FOUND TO BE 2 1/2 BEARING FAILURE. 2 1/2 BEARNING ON SPUR ADAPTER, REPLACE	D. PROBLEM SEEMS TO BE FROM A HIGH N1 GEAR TRAIN VIBRATION. POSSIBLE OUT OF BALANCE COMPRESSOR.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002022000025	20020220	00025	GL  	2002	2	20	CA020125003      	3	20020114	G	6114	A2202	BEARING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BALLS HAD SEVERELY DENTED BEARING RACE (INBOARD). REPLACED. FORK HAD SEVERE WEAR FROM PITCH CHANGE BLOCKS.BEARING 	P/N A2202 FORK P/N B2457-7					1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2002022000027	20020220	00027	CE  	2002	2	20	CA020125004      	1	20020114	G	5310	05132831	DOOR FRAME      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  ON A 200 HOUR INSPECTION WHILE INSTALLING LT HEATING DUCT LOOKING THROUGH LIGHTNING HOLE AT BOTTOM LT DOOR POST. 	 FOUND AN 1 1/2 INCH CRACK AT DOOR HINGE SCREWS.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002022000028	20020220	00028	SO  	2002	2	20	CA020125005      	1	20020114	G	5310	76467003	DOOR FRAME      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11790								(CAN) THE INNER DOOR FRAME WAS FOUND CRACKED ALSO THE OUTER FRAME OF FUSELAGE SKIN WAS CRACKED. THE INNER FRAME WAS REPL	ACED. THE OUTER FRAME WAS CLEANED OF CORROSION TREATED AND ZING CHROMATED. THE OUTER CRACK WAS STOP DRILLED USING 7/64 I	NCH DIA STOP DRILL HOLE.NOTE: THE OUTER SKIN CRACK WILL BE MONITORED IF IT EXTENDS BEYOND STOP DRILL HOLES IT WILL HAVE 	TO BE REPLACED. NOTE: P/N & DESCRIPTION FOUND IN PARTS MANUAL FIGURE 10-31.			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002022000029	20020220	00029	EA  	2002	2	20	CA020125006      	1	20020110	G	2720	C3CF1985	CONTROL CABLE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE FOUND WORN DURING 800 HOUR INSPECTION.  CABLE INSTALLATION WAS NORMAL.  CABLE WAS WORN INSIDE C3CF383-7 FAIR	LEAD. THE FAIRLEAD CONDITION AND INSTALLATION WAS NORMAL.					1	H	7	1 	3R	3	R	 	A815    	E142				 
2002022000045	20020220	00045	EU  	2002	2	20	CA020125007      	1	20020125	G	6720		ADJUSTER        			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					ANTITORQUE PEDAL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PEDAL ADJUSTER LOCATION PIN SUPPORT CRACKED CAUSING THE PEDAL ADJUSTER LEVER TO BE UNMOVEABLE AND THE PEDALS UNADJ	USTABLE.					2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2002022000046	20020220	00046	NE  	2002	2	20	CA020125008      	2	20020121	G	7314		SEAL            			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUEL PUMP	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) NR 2 ENGINE LOW OIL PRESS AND QUANTITY IN CRUISE YHM-YWG.ENGINE SHUT DOWN AND AIRCRAFT RETURNED TO YHM.ENGINE INSP	ECTED I.A.W. PW M.M. 72-00 PAGE 664 AND FUEL PUMP MAIN CARBON SEAL REPLACED.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002022000047	20020220	00047	SW  	2002	2	20	CA020128001      	1	20020118	G	3246	16212401	WHEEL           			AIRTRC	AT802 	AT802       	0390305	SW  										MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2027					(CAN)   DURING ANNUAL INSPECTION THE MAIN WHEELS WERE REMOVED FOR BEARING LUBRICATION AND INSPECTION. THE BEARING RACES 	REQUIRED REPLACEMENT. UPON REMOVAL OF THE RACES THE WHEEL WAS FOUND CORRODED BEYOND LIMITS. BOTH WHEEL ASSEMBLIES HAVE B	EEN REMOVED FROM SERVICE ANAD WERE REPLACED WITH SERVICEABLE MAIN WHEEL ASSEMBLIES. NOTE THE MAIN WHEEL ASSEMBLIES ARE M	AGNESIUM.			1	L	7	1 	3T			NC	A19SW   					 
2002022000048	20020220	00048	EU  	2002	2	20	CA020128002      	1	20020118	G	5230	D21761	DOOR            			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					CARGO	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT LT BAGGAGE DOOR DEPARTED THE AIRCRAFT, HITTING THE LT ENGINE COWL. THE AIRCRAFT WAS INSPECTED BY 	A QUALIFIED AME, BAGGAGE DOOR REPLACED, ENGINE COWL REPAIRED AND THE AIRCRAFT WAS RETURNED TO SERVICE.					1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2002022000052	20020220	00052	CE  	2002	2	20	CA020128004      	1	20020115	G	5412	26530351	DOUBLER         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FIREWALL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LOWER FWD DOUBLER IS SITUATED ON BOTTOM OF FIREWALL & SUPPORTS NOSEGEAR SPRING ATTACH. DOUBLER FOUND CRACKED O	N ITS LT WEB NEAR BOTTOM.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002022000058	20020220	00058	EA  	2002	2	20	CA020129001      	1	20020129	G	2840	TJ13	TRANSMITTER     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL CELL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) TWO FUEL TRANSMITTERS WERE FOUND TO BE LEAKING DURING ROUTINE MAINTENANCE.REFER TO FIQURE 42 OF THE DHC 2 PARTS MA	NUAL FOR CLARIFICATION.THE GASKET ITEM 42 WAS FOUND TO BE LEAKING BETWEEN ITEM 43(FLANGE) AND ITEM 3(CASE). THE GASKET T	HAT SEPERATED THE ITEMS APPEARED TO BE SWOLLEN AND DISTORTED,				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002022000059	20020220	00059	EA  	2002	2	20	CA020129002      	1	20020128	G	2701	C2CF1977	STRUCTURE       	DHAV        	C2CF833A    	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					CONTROL COLUMN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			26981			391					(CAN) DURING INSPECTION OF CONTROL COLUMN BASE AS PER CF-84-01-R1 A CRACK WAS NOTED ON THE REAR FACING WELD FILLET. WHER	E THE VERTICAL TUBE IS WELDED TO THE HORIZONTAL TUBE.THE ASSEMBLY WAS REMOVED FOR REPAIR AND A SERVICABLE UNIT WAS REINS	TALLED.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002022000060	20020220	00060	EA  	2002	2	20	CA020129003      	2	20020108	G	7230	3039901	BLADE           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A28      	 	EA  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT A POST LEASE INSPECTION ON THE AIRCRAFT BOTH ENGINES ARE SPLIT AT THE "C" FLANGE FOR HOT SECTIO	N INSPECTION. DURING THE RIGHT H.S.I. THE ENGINEER NOTICED "LINES" ON SOME OF THE C.T. BLADES. NINE BLADES SEEM TO BE CR	ACKED. SEVEN BLADES CRACKED FROM TIP HEADING TOWARDS ROOT. TWO SEEM CRACKED ACROSS THE BLADE FROM LEADING EDGE TO TRAILI	NG EDGE.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002022000062	20020220	00062	EA  	2002	2	20	CA020129005      	2	20020118	G	7320	3031448	TUBE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					FUEL CONTROL	CRACKED         	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA			14606								(CAN) LEFT ENGINE WOULD NOT ACCELERATE ON INITIAL TAKEOFF. NG AT 44 PERCENT. NO RESPONSE FROM POWER LEVER, REJECTED TAKE	OFF AND RETURNED TO RAMP.					1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2002022000063	20020220	00063	GL  	2002	2	20	CA020129006      	2	20020123	G	7260	23039794	PUMP            	RROYCE      	250C30P     	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					GEAR OIL	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAG95735					(CAN) DURING REINSTALLATION OF ENGINE BY OPERATOR.  ENGINE HAD NO OIL PRESSURE: OPERATOR NOTED UNUSUAL NOISE HEARD COMIN	G FROM GEARBOX WHEN N1 GEAR TRAIN SPUN. GEARBOX RETURNED FOR REPAIR.   UPON INSPECTION FUEL CONTROL / OIL PUMP FLEXIBLE 	COUPLING SHAFT FOUND FRACTURED.  WHEN TURNED BY HAND N1 GEAR TRAIN ROTATED NORMALLY. OIL PUMP COULD NOT BE TURNED BY HAN	D. OIL PUMP REMOVED & DISASSEMBLED. ONEOF IDLER GEARS HAD METAL BUILD-UP ON END FACE. ADJACENT FACES ON GEAR POCKET & SE	PARATOR WERE ALSO HEAVILY SCORED. GEAR END CLEARANCES WERE MEASURED&FOUND TO BE .0005 TO .0075, WHICH IS WITHIN ROLLS RO	YCE OVERHAUL LIMITS. IT W AS CONCLUDED OIL PUMP HAD SEIZED DUE T	1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002022000064	20020220	00064	EA  	2002	2	20	CA020130001      	1	20020110	G	2710		CONTROL CABLE   			CNDAIR	CL215 	CL2156B11415	       	EA  										AILERONS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)    AILERON CABLE WORN  BEYOND LIMITS.						2	H	7	2 	4T			RT	A14EA   					 
2002022000066	20020220	00066	SO  	2002	2	20	CA020130004      	1	20020124	G	7810	9904404	EXHAUST STACK   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED EXHAUST STACK FROM CYLINDER NR 3 MELTED THE CARB HEAT CABLE INTERIOR LINING CAUSING THE CABLE TO BE VERY S	TIFF. CABLE.  CRACK LOCATED INSIDE THE CARB HEAT SHROUD AT THE MOST FORWARD POINT WHICH IS VERY DIFFICULT TO INSPECT. RE	COMMEND REMOVE SHROUD PERIODICALLY FOR BETTER INSPECTION. EXHAUST STACK WALL EROSION IS DIFFICULT TO DETECT.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002020500148	20020205	00148	SW  	2002	2	5	CA020130005      	1	20020122	G	6220	206011118001	BEARING         	BELL        	206011132113	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  	 		            		CAGE	FAILED          	W			    	O	 	 	 	OTHER                   				I	 	 	FLT. ATTITUDE INST.       			CR	CRUISE         	1			CA		 				A5828					(CAN) PILOT REPORTED A "SPRINGY" FEELING IN CYCLIC ALONG WITH THE NECESSITY OF APPLYING CONSTANT FORWARD CYCLIC INPUT FO	R CRUISE FLIGHT. NO PROBLEMS WERE FOUND IN THE FLIGHT CONTROLS. THE ROTOR HEAD WAS REMOVED AND DISASSEMBLED AND AT THIS 	TIME THE DAMAGED BEARING WAS NOTED. NO OTHER PARTS WERE FOUND DAMAGED. THE ROTOR HEAD, HAVING ONLY 80 HOURS REMAINING UN	TIL OVERHAUL, HAS BEEN SENT FOR FURTHER EVALUATION AND OVERHAUL. THE FAILED BEARING IS BEING KEPT IN QUARANTINE FOR INSP	ECTION, IF REQUIRED.		1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002032100090	20020321	00090	CE  	2002	3	21	CA020130008      	1	20020119	G	5347	12139902	BRACKET         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13347								(CAN) DURING THIRD INSPECTION WE FOUND NINE SEAT BRACKET CRACKED.  THE CRACK WAS GENERATED FROM THE REAR THRU THE HOLE A	DJACENT TO THE BEND.AFTER FLEET INVESTIGATION WE FOUND 33 BRACKET CRACKED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002032100091	20020321	00091	CE  	2002	3	21	CA020130009      	1	20020114	G	3340	9003312	LIGHT           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	STROBE	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) AFTER SELECTING THE BEACON SWITCH TO ON,  FOUND THAT THE TAIL BEACON LIGHT WAS NOT FLASHING.  THE LIGHT WAS REPLAC	ED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002022000071	20020220	00071	SW  	2002	2	20	CA020131002      	1	20020118	G	5302	222035231105	FITTING         			BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					VERTICAL FIN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERTICAL LOWER FIN FITTING FOUND ATTACHMENT LUG BROKEN OFF ON A PRE FLIGHT.						1	G	7	2 	3U	3	U	 	H9SW    	E5NE				 
2002022000073	20020220	00073	SW  	2002	2	20	CA020131003      	1	20020129	G	2910	212076301001	LINE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR 1 HYD SYSTEM	BROKEN          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) HE AIRCRAFT NR 1 HYDRAULIC SYSTEM LOST SYSTEM PRESSURE(FLUID LOSS). THE ENGINEER FOUND A HYDRAULIC TUBE BROKEN IN 	THE MID POINT.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002020500149	20020205	00149	SW  	2002	2	5	CA020131004      	1	20020129	G	6340	204001736005	CHAIN           	BELL        	204040806011	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  	 		            		HYD DRIVE OIL	BROKEN          	W			    	A	O	 	 	UNSCHED LANDING         	OTHER                   			J	O	 	WARNING INDICATION        	OTHER                     		CR	CRUISE         	1			CA		 				A1214562					(CAN) THE HELICOPTER WAS IN CRUISE WHEN ALL OF A SUDDEN THE ROTOR TACH GENERATOR INDICATOR WENT TO ZERO.BACK AT THE BASE	 AN ENGINEER TROUBLE SHOOTED THE PROBLEM AND FOUND THE TACH. GEN DRIVE WAS DISCONNECTED. THE ROTOR TACH GENERATOR DRIVE 	IS LOCATED IN THE #1 HYDRAULIC QUILL ASSEMBLY OF THE MAIN ROTOR TRANSMISSION. SUSPECT THE CHAIN HAS FAILED INSIDE THE HY	DRAULIC/TACH GEN DRIVE QUILL.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002030800033	20020308	00033	GL  	2002	3	8	CA020131005      	3	20020124	G	6110	B2256	THRUST PLATE    													HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND AROUND THIN LIP OF THRUST PLATE.																5	C	P33EA	 
2002030800036	20020308	00036	EA  	2002	3	8	CA020131006      	1	20020120	G	2120	600953373	CONNECTOR       			CNDAIR	CL600 	CL600*      	       	EA  										CABIN HEAT	MISREPAIRED     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) 1) ENROUTE LOSS OF CABIN HEAT & TEMP CONTROL. 2) AFTER LANDING FOUND DAMAGED CONNECTORS FROM DUCT AT RT ACU. 3) TH	IS DUCT INSTALLATION IS PART OF SB 600-0476. THE CONNECTORS ARE RTV SECURED AT ONE END OF THE DUCT. ASSEMBLY OF COUPLING	S TO DUCT ENDS WERE CARRIED OUT IMPROPERLY CAUSING SEPARATION. P/N 600-95337-3/600-95337-1				2	L	7	2 	4F			RT	A21EA   					 
2002032100093	20020321	00093	NM  	2002	3	21	CA020131009      	1	20020114	G	5523	85520271003	STOP            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ELEVATOR	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING CREW WALKAROUND, THEY NOTICED DAMAGE TO LT TRAILING EDGE OF THE ELEVATOR SPRING TAB. THE DAMAGE TO THE TAB 	WAS INBOARD, ADJACENT TO THE RUDDER. THE TRAILING RUDDER WAS ALSO DAMAGED FROM CONTACT WITH ELEVATOR SPRING TAB. THE LT 	ELEVATOR SPRING TAB REPLACED. RD 8-55-1214 ISSUED FOR 200 HOURS ALLOWANCE FOR DAMAGE TO LT SIDE OF THE TRAILING RUDDER. 	THE ELEVATOR BUMPER STOP WAS REPLACED, AS IT WAS DETERIORATED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002022000080	20020220	00080	NM  	2002	2	20	CA020201003      	1	20020118	G	6120	78249047	PCU             			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER	FAILED          	W				C				ABORTED TAKEOFF         				R	E	J	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          	WARNING INDICATION        	TO	TAKEOFF        	1			CA											(CAN) JOURNEY LOG:  TAKEOFF ABORTED DUE TO ENGINE NR 2 TORQUE NOT PASSING 60 PERCENT. ON SHUTDOWN PROP NR 2 WOULD NOT FE	ATHER. AIRCRAFT RETURNED TO GATE DUE TO NR 2 ENGINE SLUGGISH TO ACCELERATE, PROP FOUND NOT TO BE FEATHERING AUTOMATICALL	Y OR MANUALLY.  INSPECTION ON PROP HUB ASSEMBLY, PCU REPLACED AS PER MM, ENGINE RUNS CARRIED OUT, OK. REPLACEMENT OF THE	 PCU WAS THE FINAL FIX.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002022000081	20020220	00081	NM  	2002	2	20	CA020201004      	1	20020122	G	3297	471515	WIRE HARNESS    			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG SQUAT SWITCH	SHORTED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WEIGHT ON WHEELS CAUTION LIGHT ILLUMINATED IN FLIGHT. RELANDING DUE TO CAUTION LIGHT "WT ON WHEEL" INTERMITTENTLY 	ON. UNEVENTFUL RE-LANDING.FOUND SENSORS WIRING, TWISTED SHIELDED PAIR, SHORTED TO SHIELD. SENSOR REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002032100097	20020321	00097	NM  	2002	3	21	CA020201007      	1	20020121	G	3260	854144465101	BRACKET         			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IT WAS NOTICED DURING ROUTINE MAINTENANCE THAT THE LT UPLOCK ACTUATOR SUPPORT BRACKETS  WERE MISSING THE ATTACH HI	-LITES (QTY 6) THRU AFT FRAME  (THIS HAS INITIATED A FLEET WIDE INSPECTION AS DIRECTED BY DASH-8-400 AOM 050) AC SN 4033	 HAS SUFFERED A STRUCTURAL DAMAGE DUE TO MISSING FASTENERS IN AFT END OF THE BRACKETS FOR THE LT MAIN LANDING GEAR. UPLO	CK.  MAINTENANCE WILL CHANGE THE ENTIRE SHEAR DIAPHRAGM , THE SUPPORT BRACKET DOUBLER , SUPPORT BRACKET SHIM , ATTACHMEN	T CLEATS  AND REMOVE AND REPLACE BOTH UPLOCK BRACKETS.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002032100098	20020321	00098	NM  	2002	3	21	CA020201008      	1	20020124	G	3320	404820	SOCKET          			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					LIGHTS	OVERHEATED      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) BURNING SMELL FROM TOILET OBSERVED BY CABIN CREW. RIGHTHAND GENERATOR SWITCHED OFF. EMERGENCY DECLARED. AIRCRAFT L	ANDED SAFELY AND PASSENGERS DISEMBARKED ON RUNWAY AND TAKEN BY BUS TO TERMINAL. TOILET AND PANELS CHECKED BY FIREFIGHTER	S. NO TRACE OF FIRE FOUND. AIRCRAFT TOWED TO GATE AND PASSENGERS BRIEFED BY COMMANDER.INVESTIGATION OF THE AIRCRAFT SHOW	ED A BURNED AND MELTED HOLDER FOR THE FLUORESCENT TUBE IN THE LAVATORY THAT HAD CAUSED THE SMOKE/SMELL.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002022000082	20020220	00082	EU  	2002	2	20	CA020201010      	1	20020121	G	2435		WIRE            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					STARTER GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT ENGINE STARTER GENERATOR WIRING WORN AT SUPPORT BRACKET.						2	L	7	2 	4F	4	F	 	A3EU    	E6WE				 
2002022000084	20020220	00084	EU  	2002	2	20	CA020201012      	1	20020121	G	2435	257ES2873	FAIRLEAD        			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					STARTER GEN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT ENGINE STARTER GENERATOR WIRING WORN AT SUPPORT BRACKET AND PHENOLIC FAIRLEAD BROKEN.						2	L	7	2 	4F	4	F	 	A3EU    	E6WE				 
2002032100102	20020321	00102	NE  	2002	3	21	CA020201013      	2	20020122	G	7314	9234A8	PUMP            			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER COMPLETION OF UNLOADING FREIGHT, OUR AIRCRAFT WAS REPOSITIONING TO THE MAINTENANCE FACILITY AT FBO. DURING E	NGINE SHUTDOWN, AN ENGINEER FROM OUR CONTRACTED AMO NOTICED FUEL LEAKING FROM THE RIGHT ENGINE LOWER COWLING. IN ORDER T	O STOP THE FUEL FROM LEAKING, THE RIGHT ENGINE EMERGENCY SHUT DOWN LEVER WAS PULLED.AFTER VISUAL INSPECTION, A SMALL HOL	E ON THE FCU BOOST PUMP CASTING WAS OBSERVED.THE SMALL HOLE SEEMS TO ORIGINATE FROM A DEFECT IN THE CASTING.			2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2002022000087	20020220	00087	EA  	2002	2	20	CA020201014      	1	20020128	G	2720	MS178264	NUT             			CNDAIR	CL604 	CL604       	1900301	EA  										RUDDER CONTROL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING A PRE-DELIVERY INSPECTION A NUT  WAS DISCOVERED MISSING ON BOLT  ON CONTROL ROD ASSEMBLY  AND TORQUE TUBE 	AFFECTING THE PCU RUDDER TORQUE TUBE ASSEMBLY. A FLEET INSPECTION WAS CARRIED OUT AND NO OTHER AIRCRAFT FOUND WITH SIMIL	AR PROBLEM.				2	L	7	2 	4F			RT	A21EA   					 
2002022000089	20020220	00089	EU  	2002	2	20	CA020201015      	1	20020119	G	2611		SMOKE DETECTOR  			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					E/E BAY	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, AVIONIC VENT SMOKE MESSAGE, NO APPARENT OF SMOKE OR SMELL. RAT DEPLOYED. SMOKE INDICATION DISAPPEAR	ED BEFORE LANDING.  FLIGHT RETURNED TO FORT LADERDALE.  AVIOINIC COMPARTMENT INSPECTED FOR EVIDENCE OF SMOKE,  BLOWN DUC	TS OR OVERHEATED EQUIPMENT.  NO FAULT FOUND. SUSPECT BAD SMOKE DETECTOR INSTALLED. RAT RETRACTED AND TESTED.  SMOKE DETE	CTION SYSTEM TESTED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002022000090	20020220	00090	EA  	2002	2	20	CA020201017      	1	20020119	G	5270		SENSOR          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON DEPARTURE THROUGH 4000 FT PAX OR LATCH.  CAUTION MSG ILLUMINATED. CHECKLIST CARRIED OUT WITH PRESSURIZATION NOR	MAL. DECIDED ATO CONTINUE THROUGH 10000 FT, PASSENGER DOOR WARNING MSG WITH NORMAL PRESSURIZATION.AIRCRAFT RETURNED TO T	ORONTO. ON ARRIVAL FOUND DOOR HANDLE LATCH LOCK ALMOST UNLATCHED. FOUND EXCESS GREASE ON SENSORS, SENSORS CLEANED. PSEU 	MEMORY RESET AND DOOR OPERATION AND INDICATION CHECKED OK.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002022000091	20020220	00091	EA  	2002	2	20	CA020201018      	1	20020120	G	5210		DOOR LATCH      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING FLIGHT, AIRCRAFT WAS DIVERTED DUE TO PASSENGER DOOR FAULT. FOUND PASSENGER DOOR LATCH RED HANDLE STICKING. 	CLEANED AND LUBED, OPERATED DOOR SEVERAL TIMES, DOOR OPERATION AND INDICATION OK.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002022000093	20020220	00093	EA  	2002	2	20	CA020201019      	1	20020106	G	4940	897889	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU BAY	FAILED          	W				F	O			ACTIVATE FIRE EXT.      	OTHER                   			J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) AT 10,000 FT  TRIED TO START THE APU,  NO LIGHT OFF.  APU SELECTED OFF.  2 MINUTES LATER,  ATTEMPTED ANOTHER START	,  START COMPLETED, FUEL TRANSFERRED WITH STRONG SMELL OF FUEL, EGT HIGHER THAN NORMAL WITH ONE FIRE DETECTOR LOOP INOP.	  APU SHUTDOWN AND FIRE BOTTLE DISCHARGED.  APU FIRE EXTINGUISHER BOTTLE AND SQUIB REPLACED. FIRE DETECTION LOOP REPLACE	D. SYSTEM TESTED SERVICEABLE. APU AND ENGINES RUN FOR 3 MINUTES, NO SMELL OF FUEL, ALL SYSTEMS OPERATE NORMAL. AIRCRAFT 	SERVICEABLE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002022000094	20020220	00094	EA  	2002	2	20	CA020201020      	1	20020110	G	3222	16050105	LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) GEAR DISAGREE WARNING AFTER LANDING GEAR SELECTED UP ON TAKEOFF (NOSE GEAR UNSAFE). AIRCRAFT RETURNED TO BASE.AFTE	R EXTENSIVE TROUBLE SHOOTING, NEW NOSE LANDING GEAR ASSEMBLY INSTALLED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002022000095	20020220	00095	EU  	2002	2	20	CA020201023      	1	20020123	G	3230	114079015	SELECTOR VALVE  			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN)  ON FINAL APPROACH TO VANCOUVER AT 1600 AGL "L/G NOT DOWNLOCKED"  WARNING CAME ON. GEARS CYCLED.  ALL EXTENDED NOR	MALLY THE SECOND TIME. THE GEAR AT FAULT WAS THE RT MAIN.  MAIN LANDING GEAR SELECTOR VALVE REPLACED AS PER AMM TASK 32-	31-12-400-001, LEAK CHECKED AND GEAR RETRACTED SEVERAL TIMES, NO FAULT FOUND.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002022000096	20020220	00096	EU  	2002	2	20	CA020201024      	1	20020124	G	3231	201122006	UPLOCK          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					LT MLG DOOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) CLIMBING THROUGH 16,000 FT AT 265 KTS ECAM L/G DOOR OPEN. SLOWED TO 215 KTS. GEARS RECYCLED AS PER MAINTENANCE REQ	UEST, NO CHANGE. AMBER DOOR LIGHT INDICATION REMAINS ON UNTIL GEAR SELECTED DOWN. AIRCRAFT RETURNED TO TORONTO. LT MAIN 	LANDING GEAR DOOR UPLOCK REPLACED AS PER AMM 32-31-33. DOOR OPERATION CHECK CARRIED OUT. NO FAULT FOUND. AIRCRAFT SERVIC	EABLE.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002022000097	20020220	00097	SW  	2002	2	20	CA020201025      	1	20020123	G	3246		BEARING         			AIRTRC	AT802 	AT802       	0390305	SW  										MLG WHEEL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE ANNUAL INSPECTION MAINTENANCE DISCOVERED SERIOUS CORROSION AT THE TOP AND BOTTOM OF OUTER BEARING RACE.						1	L	7	1 	3T			NC	A19SW   					 
2002022000099	20020220	00099	NE  	2002	2	20	CA020201026      	2	20020124	G	7200		ENGINE          			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					NR 2	VIBRATION       	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN)  VIBRATION ON  NR  2 ENGINE, (DURING CLIMB) INCREASING WITH ALTITUDE , ADVISORY 3.5 UNIT AT 22 000 FT AT 5.0 UNIT 	, FELT AIRFRAME VIBRATION.  THE AIRCRAFT MADE AN AIR TURN BACK. A BLADES OFF INSPECTION WAS CARRIED OUT I.A.W. ENGINEERI	NG ORDER 5-7231-001 ( BLADE ROOT INSP. C/OUT , NO FAULTS FOUND, BLADE ROOTS WERE CLEANED , LUBRICATED AND RE-INSTALLED) 	ENGINE RUN C/OUT SERVICEABLE.NOTE THE AIRCRAFT MADE AN OVERWEIGHT LANDING IN YMX AT 206 000 KGS , AUTOLAND PERFORMED , T	OUCH DOWN AT 200 FEET/MINUTE.NO INSP. FOR HARD/OVERWEIGHT LANDING REQUIRED I.A.W. AMM 05-51-11-200-801.		2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002022000100	20020220	00100	NE  	2002	2	20	CA020204002      	2	20020201	G	7200	658536916	BULLET          			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2 ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) FLT CREW RPTED DURING CLIMB AFTER TAKEOFF THEY EXPERIENCED SERIES OF LOUD BANGS FROM NR 2 ENGINE ACCOMPANIED BY AB	NORMAL HIGH EGT & LOW N 2 RPM. ALL IND.S WERE NORMAL PRIOR TO NOICE.  PROBLEM OCCURRED AFTER CLIMB THRUST SET. THE CREW 	REDUCED NR 2 THRUST TO ALMOST IDLE, AS PER ENGINE LIMITS / SURGE / STALL QUICK REF CHART (QRC) AND ENGINE OPERATED NORMA	LLY. A/C RETURNED&LANDED W/O INCID. - CFR WERE NOTIFIED&ON STANDBY.INIT MAINT INSPECTION FOUND NR 2 ENGINE NOSE CONE BUL	LET HAD SEPARATED FROM ITS ATTACHMENTS & JAMMED INTO ENGINE INLET GUIDEVANES. MAINT REPL ENGINE,		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002022000102	20020220	00102	EU  	2002	2	20	CA020205001      	2	20020127	G	8530	N854115	EXHAUST VALVE   			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	CHIPPED         	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER T/O,  A PARTIAL ENGINE POWER LOSS WAS EXPERIENCED WITH ASSOCIATED ENGINE VIBRATION AND REDUCED CLIMB	 PERFORMANCE.THE AIRCRAFT RETURNED TO THE AIRPORT TO LAND. THE COMPRESSION WAS FOUND TO BE LOW IN THE NR 3 CYLINDER.  AI	R WAS FOUND TO BE LEAKING OUT THE EXHAUST.  THE EXHAUST VALVE WAS FOUND TO HAVE A 1/16 IN DIA HOLE.THE VALVE HAD ALSO MA	DE CONTACT WITH THE PISTON.TWO FLIGHTS PRIOR TO THE INCIDENT FLIGHT THE ENGINE EXPERIENCED A SUBSTANTIAL BACKFIRE ON SHU	TDOWN DUE TO SHUTTING DOWN AT HIGH POWER.IT IS UNCLEAR IF THIS CONTRIBUTED TO THE DAMAGED VALVE.		1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002022000105	20020220	00105	NE  	2002	2	20	CA020205002      	1	20020128	G	3213	14102B	CYLINDER        			CONAER	C2    	C2          	5110202	NE  	LYC   	O360  	O360A1A     	41514	EA  					MLG	FAILED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA											(CAN) A/C C-2 SKIMMERS, BOTH UTILIZE COLONIAL STYLE MAIN UNDER CARRIAGE OLEOS. ONE OLEO PER A/C CAME APART.THE MAIN GEAR	 OLEOS ARE CRACKING AT LOWER END CAP TO CYLINDER (CASING) ATTACH BOLTS. WHEN THIS OCCURS, BEFORE LONG END CAP DISLODGES 	FROM OLEO CAUSING GEAR LEG & TRAILING DRAG ARM TO COLLAPSE.THE CRACKS IN THIS AREA HAVE ALSO BEEN FOUND ON NEWER STYLE G	ERDES & AEROFAB MANUFACTURED OLEOS, P/N 2-4111-11 INST ON LA-4 SERIES A/C. IF CRACKS ARE FOUND, LAKE A/C REPAIR IS TO RO	TATE END CAP WITHIN CYLINDER, RE-DRILL & INST NEW HARDWARE.		1	H	7	1 	3O	3	O	 	1A13    	E286				 
2002022000106	20020220	00106	NE  	2002	2	20	CA020205003      	1	20020124	G	7910	41650	CAP             			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					OIL TANK	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PHASE IVA OPS 6, WE FOUND OIL CONTAMINATION ON ENGINE NR 2 TANK. THE PACKING P/N MS29513-232 ON THE CAP ASS	EMBLY P/N 416-50 TO BE THE CAUSE. REPLACED THE PACKING, FLUSHED OIL AND CHANGE OIL FILTER. RAN THE AIRCRAFT FOR 15 MINUT	ES AND AFTER OIL AND FILTER WILL BE REPLACED.  IF NO FURTHER CONTAMINATION AIRCRAFT WILL BE RETURNED TO SERVICE.				2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2002022000107	20020220	00107	GL  	2002	2	20	CA020205004      	3	20020125	G	6111	A0971	BEARING         													HARTZL	HCA3V	PHCA3VF2    	GL  	PROPELLER	DENTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BEARING WAS BADLY DENTED ON BALL SURFACE. MUSHROOM CRACKED AROUND BASE. ALL BEARINGS REPLACED.MUSHROOM REPLACED.BE	ARINGS P/N A0971MUSHROOM P/N A0856															5	C	P6EA	 
2002032200001	20020322	00001	EU  	2002	3	22	CA020207001      	1	20020120	G	3520	C24091	SQUAT SWITCH    			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE73121C   	 	NE  					LT MLG	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN)  LOSS OF PRESSURIZATION AFTER TAKEOFF.  RECTIFICATION: MOISTURE WAS FOUND ON THE LT LANDING GEAR SQUAT SWITCH 9G1.	  SUSPECT SQUAT SWITCH 9G1 WAS COLD SOAKED, CLEANED AND LUBED.    PASSENGER OXYGEN MASK HAD NO OXYGEN FLOW.    SYSTEM IS	 OPERATING IAW F10 M.M. WHICH STATES THAT THERE IS NO OXYGEN FLOW BELOW 15,000 FT. AIRCRAFT SYSTEM GROUND CHECKED SERVIC	EABLE.			2	L	7	2 	4F	4	F	 	A33EU   	E6WE				 
2002030800052	20020308	00052	EA  	2002	3	8	CA020207002      	2	20020203	G	7250	3027301	BLADE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TWO (2) CT BLADES CRACKED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002032200002	20020322	00002	EA  	2002	3	22	CA020207003      	1	20020118	G	3241		BRAKE           			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					ANIT SKID	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI- ANTI-SKID TEST FAILURE - WIRES BG15B20BLU & GB30B20WHT - SUSPECT CYCLIC FAILURE.						2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2002030400121	20020304	00121	EA  	2002	3	4	CA020207004      	1	20020206	G	5210	6003189021	BELLCRANK       	CNDAIR      	CL6012A12   	CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  	 		            		NIL	                	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				3037					(CAN) DOOR HARD TO OPEN: INSPECTION FOUND CRANK ASSY CRACKED (P/N 600-31890-21) -  PART CRACKED DUE TO IMPROPER INSTALLA	TION OF SB 601-0192 - DOGS OF LOST MOTION CRANK NOT CONTACTING DRIVE CRANK AND COLLAR SIMULTANIOUSLY.  THIS CAUSED STRES	S ON OPPOSITE EARS CAUSING EACH TO CRACK.				2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2002032200003	20020322	00003	CE  	2002	3	22	CA020207005      	1	20020130	G	5414	016A1331621	HANDLE          	MTSBSI      	016A133003  	MTSBSI	MU2   	MU2B60      	5780460	CE  										COWLING	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) AFTER MAINTENANCE, AN ENGINEER AND A PILOT DID A WALK AROUND CHECK AND DID NOT NOTICE ANYTHING UNUSUAL. THE AIRCRA	FT DEPARTED AND ON ROUTE ONE LATCH ON THE LEFT HAND UPPER COWLING SEEMED TO HAVE BECOME UNLATCHED. THE AIRCRAFT LANDED I	N TIMMINS AND ON ENGINE SHUTDOWN THE COWLING CAME FORWARD AND CONTACTED THE PROP CAUSING THE COWLING TO FLY OFF ONTO THE	 RUNWAY.THE COWLING AND PROP WERE REPLACEDTHE COWL LATCH WAS INSPECTED AND NO DEFECTS COULD BE FOUNDWE HAVE INITIATED PR	OCEDURES TO PUT SCREWS INTO THE UPPER COWLINGS SO THIS PROBLEM WILL NOT HAPPEN AGAIN		1	H	7	2 	3T			RT	A10SW   					 
2002030800053	20020308	00053	CE  	2002	3	8	CA020208001      	1	20020125	G	5610	10138402522	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	FAILED          	W				B	G	A		EMER. DESCENT           	O2 MASK DEPLOYED        	UNSCHED LANDING         		O			OTHER                     			CR	CRUISE         	1			CA						97300H8611					(CAN) APPROX 15 MINS AFTER LEVELLING OFF AT CRUISE ALTITUDE OF 29,000 FEET,  SMALL CRACK FORMED ON RIGHT WINDSHIELD.  FE	W SECONDS LATER, ENTIRE INNER PLY SHATTERED & CABIN PRESSURIZATION LOST AT RATE OF APPROX 2500 FT/MIN . EMERGENCY OXYGEN	 DEPLOYED & MASKS DONNED, & EMERGENCY DESCENT TO SAFE ALTITUDE OF 11,000 FEET CARRIED OUT BY CREW.  A/C CARRIED ON TO ME	DICINE HAT (CYXH), WHERE UNEVENTFUL APPROACH & LANDING WERE CARRIED OUT.  INSPECTION OF WINDSHIELD UPON ARRIVAL CONFIRME	D THAT ENTIRE INNER PLY HAD SHATTERED.  HAD BEEN NO PREVIOUS REPORTS OF DAMAGE ON WINDOW,&WINDHSIELD HEAT OP NORMAL.INSP	OF FUSELAGE WINDSHIELD ATTACH STRUCTURE REVEALED NO ABNORMALITIES.  REPLACED WINDSHIELD.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002032200004	20020322	00004		2002	3	22	CA020208002      	4	20020208	G	3422		VANE            	SIGMATEK    	235010616   	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	GYRO	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						T53207J					(CAN) COPPER VANE RUBS AGAINST POT ALUMINUM GYRO CASE CREATING BLACK RESIDUE CAUSING VANE TO STICK.  THIS CAUSES HORIZIO	N TO DIPLAY A PITCH OR ROLL WHEN LEVEL.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002030800055	20020308	00055	CE  	2002	3	8	CA020208004      	1	20020127	G	2731	043200122	SKIN            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11841								(CAN) - CRACK FOUND ON PRE-FLIGHT. - CRACK LOCATED AT OUTBOARD AFT CORNER OF ELEVATOR UNDER TRIM TAB HINGE.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002032200005	20020322	00005	CE  	2002	3	22	CA020208005      	1	20020206	G	2497		WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	FUSELAGE	SHORTED         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) DURING PREFLIGHT CHECKS, CREW NOTICED FALSE FIRE WARNING, FUEL SHUTOFF VALVE ACTUATION, ALTHOUGHT VALVE ACTUATION 	WAS AUDIBLE. AIRCRAFT WAS FERRIED TO MAINTENANCE FACILITY FOR REPAIRS.  WIRING SUSPECTED AS CAUSE OF FALSE INDICATIONS H	OWEVERE MEG OF WIRING REVEALED NO SHORTS.  PRIMARY WIRES WERE TO BE REPLACED BUT DURING PROCESS, A CHAFFED WIRE WAS DISC	OVERED UNDER THE FORWARD CLOSET AREA, BEHIND THE TCAS RX / TX. OCCASIONALLY,  THE WIRE WAS MAKING CONTACT WITH A KNURLED	 FITTING RELATING TO THE TCAS. THE WIRE WAS REPAIRED AND THE AREA PROTECTED FROM ADDITIONAL CHAFFING. AIRCRAFT RETURNED 	TO SERVICE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002032200006	20020322	00006	NM  	2002	3	22	CA020211001      	1	20020210	G	5420	85310380	BEAM            			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NLG WW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27861								(CAN) NLG WHEEL WELL BOX STRUCTURE WAS FOUND CRACKED WHILE DOING TASK 5310/27D (DETAILED VISUAL INSPECTION).DAMAGE WAS R	EPAIRED IN ACCORDANCE TO REPAIR DRAWING RD 8-53-2376					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002022800004	20020228	00004	NE  	2002	2	28	CA020211003      	2	20020130	G	7260	5018T49P01	CARBON SEAL     	GE          	CF343A1     	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  	 		            		ON R/H ENGINE	DAMAGED         	W			    	E	 	 	 	ENGINE SHUTDOWN         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA		 									(CAN) AIRCRAFT TAT:4900.3 FLIGHT 5589 FROM CVG TO MKE.R. ENGINE LOW OIL PRESSURE WARNING IN FLIGHT. PERFORMED QRH. R. EN	GINE TO IDLE, MSG WOULD NOT CLEAR. SHUT ENGINE DOWN. ENGINE OIL PSI FLUCTUATES BETWEEN 21 TO 30 PSI.DIVERTED TO GRR, DEC	LARED AN EMERGENCY AND LANDED.FOUND ENGINE 5 QTS LOW ON ARRIVAL AT GRR. REPLENISHED SYSTEM. SUBSEQUENTLY FAILED OIL CONS	UMPTION RUN CHECK. (2 QUARTS USED). FOUND STARTER AND IDG CARBON SWALS CARBON SEALS P/N 5018T49P01 AND 5016T32P01 LEAKIN	G.REPLACED SEALS. AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002030800068	20020308	00068	EU  	2002	3	8	CA020211015      	1	20020206	G	6220	350A31190703	STARFLEX        		355A3100200 	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					MAIN ROTOR HUB	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M1801					(CAN) AIRCRAFT TOTAL TIME 463 HOURS CONDUCTED A 500/A CALENDAR INSPECTION.  BUSHING FOUND LOOSE ON STARFLEX ARM DURING I	NSPECTION AS PER WORK CARD 62.20.605 PARA. 5.3.					1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2002032200008	20020322	00008	EA  	2002	3	22	CA020211016      	1	20020211	G	3222	C3UF1085	STRUT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18089								(CAN) FLOAT STRUTS REMOVED TO PERFORM ANNUAL INSPECTION AS PER DEHAVILLAND SERVICE BULLETIN 3/30. SIX INCH LONG CRACK FO	UND VISUALLY THROUGHOUT CENTER OF THE BASE OF THE STRUT CASTING.					1	H	7	1 	3R	3	R	 	A815    	E142				 
2002030800069	20020308	00069	EU  	2002	3	8	CA020211017      	2	20020209	G	7421	897255	SPARK PLUG      			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					CYLINDER HEAD	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  ENGINE ROUGHNESS WAS NOTED ON STARTUP AT ALL POWER SETTINGS BELOW 1600 RPM. NR 3 CYLINDER SPARK PLUG WAS FOUND TO	 HAVE ELECTRODE BROKEN OFF AT 90 DEGREE BEND.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002032200009	20020322	00009	EU  	2002	3	22	CA020212001      	1	20020212	G	5210	NOGIVEN	ATTACH FITTING  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CABIN DOOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ATTACHMENT BRACKET FOR CABIN DOOR COUNTER BALANCE SYSTEM FOUND WITH LOOSE RIVETS.  RIVETS REMOVED AND REPLACED WIT	H CR3243-4 BLIND RIVETS.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002032200010	20020322	00010	NE  	2002	3	22	CA020213001      	2	20020211	G	7210	7826511	BRACKET         			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	REDUCTION G/B	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22926								(CAN) WHILE REMOVING THE ENGINE ACCESSORIES IN THE SHOP,AFTER AN ENGINE CHANGE, IT WAS DISCOVERED THAT THE PROPELLER DE-	ICE BRUSH BLOCK MOUNTING BRACKET WAS CRACKED AROUND BOTH MOUNTING BOLT HOLES. THIS WOULD EVENTUALLY LEAD TO A COMPLETE F	AILURE OF THE BRACKET AND THEREFORE PROPELLER DAMAGE AND LOSS OF DE-ICE CAPABILITY. THE BRACKET WAS REPLACED WITH A NEW 	UNIT.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002032200011	20020322	00011	CE  	2002	3	22	CA020213006      	1	20020201	G	2435		BEARING         			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					STARTER GEN	FAILED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ON A TRIP FROM HOUSTON TO CALGARY, VIBRATION OCCURRED IN AIRCRAFT, RT GENERATOR FAILED, THE AIRCRAFT DIVERTED TO W	ICHITA WHERE THE RT STARTER/GENERATOR WAS REPLACED. AIRCRAFT AND COMPONENT TIME 871.0 HOURS, 454 CYCLES.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2002032200012	20020322	00012	CE  	2002	3	22	CA020213007      	1	20020213	G	2720	03101965	SPRING          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RUDDER WAS ANGLED TO ONE SIDE UPON FURTHER INSPECTION FOUND THAT IT WOULD NOT RETURN TO NEUTRAL.RUDDER SPRING WAS 	FOUND HANGING IN POSITION DETACHED FROM ONE SIDE, THE END HAD BROKEN OFF. PART WAS REPALCED AND AIRCRAFT WAS RETURNED TO	 SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002030800070	20020308	00070	GL  	2002	3	8	CA020213008      	2	20020208	G	7314	P94C16602	PUMP            			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					FUEL BOOST	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  NR 1 ENGINE FUEL BOOST PUMP WAS MAKING TOO MUCH NOISE AND VIBRATING AS COMPARED TO NR 2 FUEL BOOST PUMP.  INSPECT	ED THE NR 1 ENGINE DRIVEN FUEL PUMP FILTER AND FOUND NON-FERROUS METAL IN THE FILTER. INSPECTED THE FUEL CONTROL FILTER 	FOR CONTAMINATION AND FOUND NON-FERROUS METAL. THE NR 1 FUEL BOOST PUMP PRESSURE WAS LOWER THAN THE NR 2 FUEL BOOST PUMP	 PRESSURE. REPLACED FUEL CONTROL, ENGINE DRIVEN FUEL PUMP AND NR 1 FUEL BOOST PUMP.			1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2002030800071	20020308	00071	NE  	2002	3	8	CA020213010      	2	20020204	G	7310	70077200G600	B-NUT           			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					FUEL LINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)   SMALL AMOUNT OF FUEL OBSERVED LEAKING FROM RT FLOOR CAVITY DRAIN. CAVITY WAS OPENED, FUEL TRANSFER LINE INSPECTE	D. LEAK ORIGINATED FROM AFT 'B' NUT FITTING. TORQUE WAS CHECKED ON 'B' NUT, WITHIN SPECS. AIRCRAFT DRAINED OF FUEL, LINE	 REMOVED AND INSPECTED. OUTCOME, STAINLESS BRAIDED FUEL LINE MANUFACTURED TOO SHORT. ORDERED NEW LINE FROM B.H.T. THIS L	INE ALSO TOO SHORT. ORDERED NEW LINE, 2ND LINE LENGTH OK. NEW LINE INSTALLED. AIRCRAFT FUELED AND LEAK CHECK C/O. FUEL L	EAK SOLVED.		1	G	7	1 	3U	3	U	 	R00001RC	E42NE				 
2002030800072	20020308	00072	CE  	2002	3	8	CA020213011      	1	20020201	G	3221	05411212	SUPPORT         			CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT OUTBOARD LANDING GEAR SUPPORT CASTING FOUND TO BE CRACKED IN TWO PLACES.  FAULT WAS DISCOVERED WHEN GEAR LEG WA	S REMOVED FOR NDT OF LANDING GEAR COMPONENTS.  NO OTHER FAULTS FOUND.  LANDING GEAR NDT INSPECTION WAS CARRIED OUT AT OW	NER'S REQUEST.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P880	 
2002030800073	20020308	00073	SW  	2002	3	8	CA020213012      	1	20020125	G	7920	427065244101	LINE            			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					ENGINE OIL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MODIFICATION OF AIRCRAFT,  NR 2 ENGINE  OIL LINES WERE REMOVED. UPON REMOVAL OF LINES IT WAS OBSERVED THAT 	THE MAIN OIL FEED LINE (FROM OIL COOLER) WAS CHAFED TO A DEPTH OF 0.004 INCH. THE CHAFING OCCURRED IN THE AREA BELOW THE	 FORWARD ENGINE FIREWALL. THE FIREWALL HAS A STAINLESS STEEL 'TUNNEL' WHICH THE OIL LINES PASS THROUGH. THE FORWARD OUTB	OARD EDGE OF THIS TUNNEL CHAFED INTO THE ALUMINUM OIL TUBE. THIS TUBE WAS REMOVED FROM SERVICE.			1	G	7	1 	3U	3	U	 	R00001RC	E42NE				 
2002030800074	20020308	00074	SW  	2002	3	8	CA020213014      	1	20020202	G	6320	2120400545	CASE            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					TRANSMISSION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LIFT LINK BEARING BOSS WAS FOUND CRACKED DURING ROUTINE MAINTENANCE.						1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002030800075	20020308	00075	EU  	2002	3	8	CA020214002      	1	20020205	G	2435	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STARTER GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE IN CRUISE FLT "ESSENTIAL BUS" WARNING LIGHT ILLUMINATED ON CAWS PANEL.  NR 2 BATTERY OBSERVED TO BE DISCHARG	ING AT APPROX 35 AMPS & SELECTED TO OFF POSITION. DISCHARGE RATE FROM BATTERY STOPPED & "ESSENTIAL BUS" LIGHT WENT OUT. 	 WITHIN 3 MINS AOA CAUTION LIGHT CAME ON & LT WINDSCREEN FROSTING OVER.  EMERGENCY LANDING REQUIRED & CARRIED OUT WITHOU	T INCIDENT. MAINT PERFORMED GROUND RUN & FOUND FOLLOWING: NR 2 GENERATOR INDICATING 28.5 VOLTS BUT NO AMPRE OUTPUT. WHEN	 PROBE HEAT & LT WINDSCREEN HEATING WERE SELECTED ON. NR 2 BATTERY WOULD SHOW DISCHARGE OF 35 AMPS.  THE NR 2 GEN RELAY 	REMOVED & BENCH TESTED.  MAINT FOUND THAT TOP SET OF CONTACTS IN RELAY WERE NOT CLOSING.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002032200013	20020322	00013	EA  	2002	3	22	CA020215001      	1	20020211	G	2612		WIRE HARNESS    			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					FIRE DETECTION	CHAFED          	W				C				ABORTED TAKEOFF         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF ROLL, THE POWER SET TO TAKE OFF N1, THE SPEED WERE JUST CALLED ALIVE, WHEN THE LEFT ENGINE ROLLED 	BACK TO IDLE. THE AIRCRAFT WAS TAXIED CLEAR AND WHILE TAXIING BACK TO FBO LEFT ENGINE SHUT DOWN. THE CAS MESSAGE INDICAT	ED HYD SOV 1 AND ENGINE FUEL SOV CLOSED WITH OUT SELECTION. TROUBLESHOOTING REVEALED WIRE BUNDLE LOCATED BEHIND NR 2 EFI	S TUBE CHAFING ON THE EFIS CONNECTOR. THE LEFT ENGINE FIRE PUSH BUTTON WIRE MADE CONTACT WITH A LIVEWIRE AND ACTIVATED A	 FIRE PUSH SELECTION. FOUR WIRES REPAIRED AND WIRE BUNDLE SECURED AS REQUIRED.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002030400122	20020304	00122	EA  	2002	3	4	CA020215003      	1	20020212	G	5610	NP1393215	WINDSHIELD      	PPG         	NP1393215   	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		WINDSHIELD	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				00229H5665					(CAN) RIGHT WINDSHIELD FOUND CRACKED ON THE GROUND. WINDSHIELD REMOVED AND REPLACED.THE WINDSHIELD INSTALLED WAS A PRE S	ERVICE BULLETIN WINDSHIELD.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002030400123	20020304	00123	EA  	2002	3	4	CA020215006      	1	20020116	G	2613	356072310	ELEMENT         	FENWAL      	            	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  	 		            		ELEMENT	FAILED          	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 									(CAN) LEFT 14TH DUCT WARNING ON AT TAKEOFF ROLL ABOVE V, ON EICAS, RED BY ENGINE. AIRCRAFT RETURNED TO TORONTO. RIGHT BL	EED LEAK DETECTION CONTROL UNIT AND LOOP SENSING ELEMENT (A58WK) REPLACED.OPERATIONAL TEST OF 14TH STAGE BLEED PERFORMED	 AND OPERATION TEST OF BLEED LEAK DETECTION PERFORMED.ALL TESTS OK UNABLE TO FAULT SYSTEM, CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002030800077	20020308	00077	NM  	2002	3	8	CA020215007      	1	20020128	G	5754		ARM             			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					LE SLAT	DISLODGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAINTENANCE FOUND NR 2 SLAT FOUND PROTRUDING 4 INCHES ON ONE SIDE ON WALKAROUND CHECK.  SLAT MECHANISM FOUND OFF G	UIDE TRACK. FLIGHT PERMIT (SPECIFIC PURPOSE, FERRY FLIGHT) ISSUED AND AIRCRAFT FLOWN TO BASE FOR REPAIRS. NR 2 LEADING E	DGE SLAT DETENT ARM REPLACED AS PER MAINTENANCE MANUAL 51-81-00. SLAT OPERATED THROUGH ENTIRE RANGE SEVERAL TIMES AND OP	ERATION CHECKED SERVICEABLE.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002022800005	20020228	00005	WP  	2002	2	28	CA020215008      	1	20020214	G	5302	C0231	TAIL CONE       	ROBSIN      	C0231       	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1A5    	41532	EA  	 		            		TOP SKIN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				0253					(CAN) 2 INCH CRACK FOUND ON TOP SKIN OF TAIL CONE AT LOCATION OF AFT FACTORY INSTALLED VHF ANTENNA MOUNT 51.5 TO 53.5 IN	CHES AFT OF FORWARD TAIL CONE SKIN. CRACK APPEARS TO HAVE ORIGINATED FROM TAPERED FACTORY SHIM PN B322-1.					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002030800085	20020308	00085	NE  	2002	3	8	CA020215010      	2	20020204	G	7270	3021436	DUCT            			CESSNA	501   	501         	2076603	CE  	PWA   	JD15  	JT15D1A     	 	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING DAILY INSPECTION, RT ENGINE FRONT & REAR INNER BYPASS DUCT FOUND CRACKED AND PIECE OF REAR UNDER BYPASS DUC	T MISSING. AFTER REMOVAL OF THOSE ITEMS FROM THE ENGINE, THE INSPECTION REVEALED THAT THEY WERE PARTS WHICH WAS PREVIOUS	LY WELDED/OVERHAUL ASSEMBLY INSTALLED AT THE LAST HOT SECTION INSPECTION.UNDER BYPASS DUCT P/N 3021436 & 3020330				1	L	7	2 	4F	4	F	 	A27CE   	E25EA				 
2002022800006	20020228	00006	EU  	2002	2	28	CA020215011      	1	20020207	G	2820	9170M59P03	FUEL LINE       	GE          	CF650C2     	AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  	 		            		AT 'B' NUT RANGE	BROKEN          	W			    	A	 	 	 	UNSCHED LANDING         				Y	 	 	ENGINE STOPPAGE           			CR	CRUISE         	1			CA		 				455262					(CAN) WHILE IN CRUISE THE #1 ENGINE SHUTDOWN BY ITSELF. COULD NOT RE-START THE ENGINE. CAPTAIN DECIDED TO LAND IN HOUSTO	N, TEXAS. MAINTENANCE FOUND A BROKEN FUEL LINE ON THE MEC GOING TO VARIABLE STATOR ACTUATOR.					2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2002041700068	20020417	00068	CE  	2002	4	17	CA020215013      	1	20020214	G	3213	358152607	STRUT           			BEECH 	33    	35B33       	1151406	CE  										RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION PISTON LOWER SHOCK TUBE WAS FOUND WITH CHROME BLISTERED. NDT SHOWED A CRACK IN TUBE.CHROME WAS REMOV	ED TO EXPOSE THE CRACK WHICH WAS 8 1/4 INCH DOWN FROM THE TOP OF THE TUBE. THE CRACK RAN HORIZONTAL FOR 1 1/2 INCH THROU	GH THE TUBE.				1	L	7	1 	3O			 	3A15    					 
2002042600073	20020426	00073	SW  	2002	4	26	CA020215015      	1	20020215	G	5270	V31	SWITCH          			SWRNGN	SA227 	SA227AC     	8780603	SW  										CARGO DOOR	OUT OF ADJUST   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) PART TIME UK PILOT REPORTED THE CARGO DOOR LIGHT CAME ON AFTER 15 MINUTES OF FLIGHT.  AIRCRAFT RETURNED TO POINT O	F ORIGIN AND DURING SHUTDOWN THE LIGHT WENT OUT.  MAINTENANCE FOUND THE CARGO DOOR MICROSWITCH OUT OF ADJUSTMENT. MICROS	WITCH ADJUSTED AND AIRCRAFT RETURNED OT SERVICE.				2	L	7	2 	4T			RT	A8SW    					 
2002032200014	20020322	00014	EU  	2002	3	22	CA020215016      	1	20020214	G	3230	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LANDING GEAR	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) LANDING GEAR WOULD NOT EXTEND.  PILOT HAD TO USE EMERGENCY EXTENSION.  MAINTENANCE FOUND THE POWER PACK RELAY WAS 	ACTUATING YET NO POWER WOULD GO THROUGH.RELAY WAS REPLACED AND AIRCRAFT RETURNED OT SERVICE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002042600074	20020426	00074	EU  	2002	4	26	CA020218002      	1	20020214	G	2780	9450202201	SHAFT           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT LE  FLAP	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) WHILE ON APPROACH, PILOT REPORTED THAT WHEN HE SELECTED 30 DEGS OF FLAP HE GOT FLAP WARNING ON CAWS PANEL. NO EFFE	CT ON FLT CONTROLS AND HE LANDED WITH OUT INCIDENT. PILOT RESET FLAPS ON GROUND AND TRIED TO RETRACT FLAPS. FLAPS WOULD 	NOT RETRACT AND FLAP WARNING ON CAWS PANEL CAME ON. PILOT COULD NOT GET FLAPS TO RESET.  MAINTENANCE DISPATCHED FROM PRI	NCE ALBERT BASE. FLAPS WERE CHECKED FOR ASSEMETARY. IT FOUND THAT LT FLAP 1/2 INCH LOWER THAN RIGHT FLAP. WHEN LEFT INBO	ARD FLEX SHAFT DISCONNECTED FROM POWER DRIVE UNIT, FLEX SHAFT HAD SHEARED AT SWAGED END THAT GOES INTO POWER DRIVE UNIT.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002032200015	20020322	00015	NM  	2002	3	22	CA020219002      	1	20020215	G	3232	1U1085	SEQUENCE VALVE  			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D*       	 	NE  					LT MLG	CRACKED         	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ON ENGINE START UP FOR DEPARTURE, CREW NOTICED QUANTITY OF "A" SYSTEM HYDRAULICS DROPPING .ENGINE SHUT DOWN MAINTE	NANCE FOUND LT MLG DOOR LOCK SEQUENCE VALVE HOUSING WAS CRACKED AND LEAKING FLUID.MAINTENANCE REPLACED THE VALVE, A/C WA	S POSITIONED GEAR DOWN TO A MAINTENANCE FACILITY FOR A GEAR SWING,WHICH WAS CARRIED OUT AND THE A/C WAS RETURNED TO SERV	ICE.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002031100008	20020311	00008	CE  	2002	3	11	CA020220008      	1	20020213	G	2780	99100554	MOTOR           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LE FLAPS	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) THE SUBJECT LT MOTOR WILL MOVE TO ITS EXTREME END TRAVEL AND LOCK THE ARMATURE CAUSING THE C.B. TO POP AND THE FLA	P SYSTEM TO STOP. WHEN THE CB WAS RESET THE FLAPS WOULD OPERATE NORMALLY, THIS HAPPENED TWICE DURING FLAP SELECTION AND 	WAS SNAGGED IN THE LOG BOOK. WHILE TROUBLESHOOTING THE SNAG, THE LT MOTOR LOCKED AND THE RT MOTOR CONTINUED TO RUN,  SHE	ARING THE DRIVE SPROCKET ON THE RT GEARBOX OUTPUT SHAFT.  THE FLAPS STOPPED MOVING AND THE MOTOR CONTINUED TO RUN UNTIL 	THE LIMIT SWITCH WAS REACHED AND THE MOTOR SHUT OFF. BOTH MOTORS AND GEARBOXES WERE REPLACED.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002041700069	20020417	00069	CE  	2002	4	17	CA020220009      	1	20020214	G	2497	AIRDATA115VAC	WIRE            			BEECH 	100   	B100        	1152919	CE  										ADC	CHAFED          	W				O				OTHER                   				G	H		MULTIPLE FAILURE          	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA											(CAN) TWO DAYS RUNNING THE AIR DATA COMPUTER CIRCUIT PROTECTION FUSE OPENED CAUSING LOSS OF THECAPTAINS ALTIMETER, THE A	LTITUDE PRE-SELECT, AND THE MODE C TRANSPONDER FUNCTION. ON THE FIRST DAY THE FAILURE OCCURRED WHILE THE AIRCRAFT WAS AW	AY FROM BASE, AND HAD TO BE FERRIED VFR TO EDMONTON WHERE THE ADC AND THE FUSE WERE REPLACED. SPECIAL PERMISSION WAS OBT	AINED TO ALLOW THE LANDING IN YXD. ON A RETURN FLIGHT TO CALGARY THE NEXT DAY THE SAME FAILURE OCCURRED AGAIN AFTER APPR	OXIMATELY 3 HOURS FLYING. THE PROBLEM IS CURRENTLY UNDER INVESTIGATION TO DETERMINE THE CAUSE. SO FAR THE SYSTEM HAS RUN	 FOR 4 HOURS ON THE GROUND WITHOUT FAILURE.	1	L	7	2 	4T			 	A14CE   					 
2002031100009	20020311	00009	EU  	2002	3	11	CA020220010      	1	20020208	G	2435	80601401	STARTER GEN     			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START SEQUENCE, NR 2 ENGINE FAILED TO ROTATE, START SEQUENCE WAS CANCELLED, AND TRIED A SECOND TIME WITH NO	 ROTATION OF ENGINE. FAULT WAS TRACED TO THE STARTER GENERATOR, UNIT WAS REPLACED WITH A NEW AND START SEQUENCE WAS OK. 	NR 2 ENGINE STARTED AS PER MM. THIS IS THE SECOND STARTER GENERATOR FAILURE, THE OTHER HAPPENED 100 HOURS AGO ON NR 3 EN	GINE. INSTALLED UPGRADED STARTER/GENERATOR [/N 8060-150. FALCON JET IS AWARE OF THIS PROBLEM. THE NR 1 ENGINE STARTER GE	N AND APU STARTER GEN ARE GOING TO BE UPGRADED TO -150.		2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2002040900023	20020409	00023	EU  	2002	4	9	CA020220011      	1	20020213	G	5753	T700A575000001	INSERT          			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A6A      	52043	EA  					TE FLAPS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HOUR INSPECTION NOTICED THAT FLAP CARRIAGE INBOARD IS MOVING AT ATTACHMENT. REMOVED FLAP AND CARRIAGE A	ND FOUND POTTED INSERTS THAT SECURE THE CARRIAGE TO FLAP WERE LOOSE CAUSING DAMAGE TO COMPOSITE RIB, HONEYCOMB (INTERNAL	LY). ONE OF THE INSERTS WAS FREE TO SPIN. BOND ON INSERT WAS NOT RETAINING. FLAP REMOVED FOR REPAIR.				1	L	7	1 	3T	3	T	RT	A60EU   	E4EA				 
2002032500002	20020325	00002	NM  	2002	3	25	CA020220014      	1	20020219	G	3310	18271	POWER SUPPLY    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	INSTRUMENT PANEL	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			30945								(CAN) THE FLIGHT CREW DETECTED A STRONG BURNING ODOUR SHORTLY AFTER TAKE OFF FROM YTZ - MUCH LIKE "A BURNING CIRCUIT BOA	RD".  THE AIRCRAFT DIVERTED INTO YYZ FOR LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE 5 VOLT POWER SUPPLY F	OR THE CAPTAIN'S INSTRUMENT PANEL LIGHTING WAS BURNING. THE POWER SUPPLY WAS REMOVED AND REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002031100011	20020311	00011	GL  	2002	3	11	CA020220015      	1	20020216	G	7410	N965177	WIRE            			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  	HOFMAN	HOV352	HOV352F     	NE  	COIL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING A FLIGHT THE ENGINE DID NOT SHUTDOWN WHEN IGNITION SELECTED TO OFF.  NO RPM DROP WAS NOTED WHEN SWITCHIN	G IGNITION FROM 'BOTH' TO 'R'.A BROKEN GROUND WIRE WAS FOUUND IN THE IGNITION CIRCUIT.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I	5	C	TP5BO	 
2002032500003	20020325	00003	EA  	2002	3	25	CA020221002      	1	20020221	G	5711	S66422024T8511	SPAR CAP        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK WAS DICOVERED WHILE PERFORMING NDT IN ACCORDANCE WITH AIRWORTHINESS DIRECTIVE CF93-07. WHILE CARRYING OUT RE	PAIR, ADDITIONAL CRACKING WAS FOUND IN AREA OUTSIDE OF THE INSPECTION PARAMETERS OF AD CF93-07 AT RBL 53 AND RBL 58.					2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
2002042600107	20020426	00107	EA  	2002	4	26	CA020221004      	1	20020211	G	3246	50105711	WHEEL           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LT MLG	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN)  AFTER FLT. CREW PERFORMED POST FLT INSPECTION AND FOUND LT OB WHEEL ASSY MISSING FROM A/C.  THE MISSING WHEEL ASS	Y RECOVERED IN ATL FROM AIRPORT AUTH. IT OBVIOUSLY DEPARTED WHILE ON TAXI OR TAKEOFF.  IT WAS RECOVERED WITH ANTI SKID D	RIVE CAP INTACT.  NEITHER INNER OR OUTER BEARINGS WERE FOUND IN WHEEL.  INNER BORE OF WHEEL DAMAGED BY AXLE AS IT ROTATE	D AND CAME OFF AXLE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002022800007	20020228	00007	EA  	2002	2	28	CA020221005      	1	20020213	G	7620		ENGINE          	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		ENGINE	FAILED          	W			    	A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			CA		 				872329					(CAN) AIRCRAFT WAS CLIMBING THROUGH 21K, ENGINE VIBE WENT TO 2.6, THEN ENGINE SHUT DOWN UNCOMMANDED. FLIGHT ATTENDANT RE	PORTED HEARING A "BANG" IN THE CABIN. ON THE GROUND, OIL WAS NOTED ON THE COWLINGS AND IN THE TAIL PIPE.PREPARATIONS BEI	NG MADE FOR A CREW TO GO TO FWA TO PERFORM ENGINE CHANGE. REMOVED AND AREPLACED ENGINE. AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002031100013	20020311	00013		2002	3	11	CA020221006      	4	20020214	G	2210	6229815704	CIRCUIT BOARD   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FCC CARD	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			56512								(CAN)  "ON FINAL TO TXK A/C WAS ALMOST UNCONTROLLABLE.  YAW DAMPER THREW A/C IN A LT BANK & THEN A RT BANK WITH AUTOPILO	T OFF. IT SETTLED DOWN ENOUGH TO GET A/C ON GROUND."MAINT SIGN OFF AS FOLLOWS: PERFORMED FCC DIAGNOSTICS T/S IAW CRJ MM.	 NO DEFECTS NOTED. PERFORMED CHECK ON RUDDER PRIMARY & SECONDARY FEEL MECHANISM CENTERING SPRINGS. FOUND PRIMARY SPRING 	TENSION TO BE AT 5 LBS. SET PRIMARY SPRING TENSION TO 10 LBS IAW CRJ MM. CHECKED RUDDER CONTROL CABLE TENSIONS & PERFORM	ED RIGGING CHECK IAW CRJ MM. OPS  CHECK GOOD. R&R NR 1 & 2 FCC IAPS CARDS IAW CARJ MM. OPS CHECKS WERE GOOD & A/C WAS TE	ST FLOWN.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002042600112	20020426	00112	EA  	2002	4	26	CA020221008      	1	20020215	G	7603	NAS464P416	BOLT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					THROTTLE	WORN            	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, THE FLIGHT CREW WERE UNABLE TO RETARD THE NR 1 THROTTLE LEVER. THE ENGINE WAS SHUTDOWN THROUGH THE	 GLARE SHIELD'S FIRE PUSH BUTTON.  EMERGENCY LANDING WAS DECLARED. MAINTENANCE STAFF VERIFIED THE BOLT SECURING THE "THR	OTTLE CONTROL LEVER ASSEMBLY" TO THE DOUBLE SPLINE EXHIBITED WEAR. "ROD ASSEMBLY" FOUND DISPLACED,  AWAY FROM THE GEARBO	X ASSEMBLY UNTIL THE ROD END'S RIVET CONTACTED WITH THE HEAT SHIELD BRACKET (BINDING CONDITION).BOLT REPLACED, THROTTLE 	CONTROL LEVER ASSEMBLY AND ROD ASSEMBLY REINSTALLED AND SECURED AS PER AMM. AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500004	20020325	00004	NM  	2002	3	25	CA020221009      	1	20020201	G	2170		CLAMP           			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					PRECOOLER	LOOSE           	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) WHEN REACHING FL330 , THE CABIN ALTITUDE LIGHT CAME NI AND THE RT PACK INOP LIGHT CAME N. WE STARTED DESCENT, THE	 CABIN STABILIZED AT FL 250. THE RT PACK WAS RESETTED AND FOUND OK. THE CREW STAYED AT THAT LEVEL FOR THE REMAINDER OF T	HE FLIGHT . MAINTENANCE FOUND A COUPLING /CLAMP ON THE PRECOOLER LINE LOOSE  THE COUPLING / CLAMP WAS RESECURED & LEAK C	HECKED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2002042600115	20020426	00115	EA  	2002	4	26	CA020221010      	1	20020219	G	2710	6009117153	AILERON         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT WING	FROZEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			12611								(CAN) "AT 24,000 FEET DURING CLIMB LEFT AILERON CONTROL FROZE - LIGHT PRESS UNSTUCK CONTROL". VERBAL REPORT FROM PILOT S	TATES: "PUDDLES OF WATER ON TAXI/RWY WHEN LEAVING MEMPHIS. DID NOT HAVE CONTROL OF AILERON AT 24,000 FEET & MINUS 20 DEG	 C. DISCONNECTED AILERON CONTROL & CONFIRMED THAT JAM ON PILOTS SIDE. THEN JERKED CONTROLS & RIGHT SIDE RELEASED. RECONN	ECTED & DESCENDING THROUGH 18,000 FT & WARMER TEMP SYS REMAINED FREE. CONTINUED ON TO DESTINATION AT CINCINNATI".			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050300004	20020503	00004		2002	5	3	CA020221012      	4	20020202	G	3460		ADC             			AIRBUS	310   	A310300     	3930305	EU  										COCKPIT	OUT OF ADJUST   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT RETURNED AFTER TAKEOFF WITH MULTIPLE FLIGHT ENVELOPE AND SPEED PROTECTION FAULTS. MAINTENANCE FOUND LOADE	D FLIGHT PLAN DATA NOT IN AGREEMENT . IRS(INERTIAL REFERENCE SYSTEM) WERE REALIGNED , FLIGHT PLAN DATA REINSERTED AND AL	L FMS (FLIGHT MANAGEMENT SYSTEM) FUNCTIONS NORMAL.				2	L	7	2 	4F			RT	A35EU   					 
2002042600120	20020426	00120	NE  	2002	4	26	CA020221017      	2	20020210	G	7200	RB211524B4	ENGINE          			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					NR 1	OVERHEATED      	W				F				ACTIVATE FIRE EXT.      				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								14838			(CAN) 2 MINUTES AFTER LANDING , AFTER THRUST REVERSER STOWING , THE FIRST OFFICER CALLED OUT HIGH TGT RAISING RAPIDALY A	ND ENGINE RUN DOWN , TEMPERATURE ROSE TO 850 DEGREES ON NR  1 ENGINE. THE TAIL PIPE FIRE DRILL  WAS CARRIED OUT.  MAINTE	NANCE CARRIED OUT AN HP TURBINE BOROSCOPE IAW MM,  NO FAULTS FOUND.  THE DFDR WAS REPLACED.  THE ENGINE WAS REPLACED FOR	 COMPANY CONVENIENCE.			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002042600123	20020426	00123	NE  	2002	4	26	CA020221018      	2	20020202	G	7230	RB21122B02	FAN BLADE       			LKHEED	1011  	10113851    	5265010	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					NR 2 ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				F	E	J	FLT CONT AFFECTED         	VIBRATION/BUFFET          	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF NR 2 ENGINE N1 INDICATION SHOWED 10 PERCENT HIGHER THAN NR  1 AND 3 ENGINES.  ALL PARAMETERS	 WERE THE SAME.  WHEN THRUST WAS REDUCED TO LOWER N1 SETTING, NR  2 ENGINE HIGH VIBRATION WAS CONFIRMED ON BOTH CHANNELS	 AT 2.5 UNITS (VIB. LIGHT ON).  ENGINE NR  2 WAS SHUT DOWN PER QRH. AFTER INSPECTION , MAINTENANCE FOUND ICE ACCUMULATIO	N STUCK IN THE DUCT AND MANY LP FAN BLADE TIPS WERE BENT. ALL LP FAN BLADES WERE REPLACED.			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002042600124	20020426	00124	EU  	2002	4	26	CA020221019      	2	20020218	G	8530	N854115	EXHAUST VALVE   			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  					NR 3 CYLINDER	CHIPPED         	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF IT WAS NOTED THAT THE ENGINE WAS NOT DEVELOPING FULL POWER.  WHEN THE POWER SETTING WAS REDUCED TO 	ESTABLISH THE AIRCRAFT ON A DOWNWIND LEG A LOW FREQUENCY ENGINE VIBRATION WAS NOTED.  A 1/4 INCH DIA CHIP WAS FOUND MISS	ING ON THE CIRCUMFERENCE OF THE EXHAUST VALVE OF NR 3 CYLINDER.				1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2002042600156	20020426	00156	NM  	2002	4	26	CA020222001      	1	20020214	G	7830	LJ76673	ACCESS PANEL    		LJ75010     	BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					THRUST REVERSER	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA						0044					(CAN) WHEN AIRCRAFT  LANDED CREW SELECTED REVERSERS,  THE NR  2 ENGINE, RT THRUST REVERSER WOULD NOT STOW.  DURING THE W	ALK AROUND,  THE CREW FOUND THE NR 2 ENGINE THRUST REVERSER DUCT ACCESS PANEL (P/N LJ76673) RIPPED OFF AND DAMAGE TO THE	 THE RT TRANSLATING COWL (P/N 75010 ; S/N 0044). THE NR 2 ENGINE THRUST REVERSER FORWARD LATCH ACCESS PANEL HAD A TEMPOR	ARY REPAIR CARRIED OUT I.A.W. ROLLS-ROYCE REPAIR PROJECT-PRODUCT. THE AIRCRAFT RELEASED.			2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2002042600058	20020426	00058	CE  	2002	4	26	CA020225001      	1	20020225	G	2710	MS276404	BEARING         	BEECH       	1185210588  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	BALL BEARING	CORRODED        	W			    	O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA		 	13115	13115		NA					(CAN) R/H AILERON FOUND WITH EXSCESSIVE UP AND DOWN PLAY.PLAY WAS CAUSED DUE TO R/H AILERON TERMINAL BELLCRANK BEARING W	ORN.BALL INSIDE BEARING WAS FOUND HEAVILY CORRODED AND OUT OF SHAPE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002050300005	20020503	00005	EU  	2002	5	3	CA020225002      	1	20020220	G	2140	5113412233	FAN BLADE       		9686781507  	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CABIN HEATER	BENT            	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						483767					(CAN) CREW REPORTS GROWLING NOISE WHEN TURNING ON CABIN HEATER. INSPECTED CABIN HEATER INLET DUCT AND FOUND I.D.TAG FROM	 BAGGAGE NET JAMMED IN FAN SHROUD. CABIN HEATER REQUIRED REPLACEMENT. INLET IS LOCATED BELOW REAR BAGGAGE AREA AND HAS F	AIRLY LARGE GRILL OPENINGS. PILATUS S.B 25-016 REQUIRES INSTALLATION OF I.D. TAGS ON BAGGAGE NETS. TAGS WERE TO BE ATTAC	HED WITH WIRE CABLE. TAGS SHOULD BE INSPECTED PERIODICALLY FOR SECURITY.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002032500005	20020325	00005	EA  	2002	3	25	CA020225003      	2	20020211	G	7200	PT6A34	ENGINE          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  					NACELLE	DETERIORATED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			12395								(CAN) - DETERIORATION INTERNALLY- COATING DETERIORATED ON SMALL EXIT DUCT WHICH CAUSED DAMAGE TO TURBINE BLADES.- CORROS	ION THROUGHOUT ENGINE (UNEXPLAINABLE) INSIDE AND OUT - WHITE POWDER.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002041700070	20020417	00070	EA  	2002	4	17	CA020225004      	2	20020211	G	7200	PT6A34	ENGINE          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  					NACELLE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) - DETERIORATION INTERNALLY- CORROSION THROUGHOUT ENGINE - WHITE POWDER						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002031100022	20020311	00022	EU  	2002	3	11	CA020225005      	2	20020225	G	8530	N854105	INTAKE VALVE    	ROTAX       	913435      	DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					CYLINDER HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE POST-INSPECTION ENGINE RUN SUBSTANTIAL ENGINE VIBRATION WAS NOTED.  THE NR 4 CYLINDER WAS REMOVED AND T	HE INTAKE VALVE WAS FOUND TO HAVE A CRACK EXTENDING FROM A CENTRAL LOCATION TO THE EDGE OF THE VAVLE.  SMALL CHIPS WERE 	ALSO NOTED TO BE MISSING FROM THE VALVE NEAR THE EDGES.				1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002031100023	20020311	00023	EU  	2002	3	11	CA020225006      	2	20020225	G	8530	N854105	INTAKE VALVE    	ROTAX       	913435      	DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					CYLINDER HEAD	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BASE OF THE INTAKE VALVE STEM FROM THE NR 2 CYLINDER WAS FOUND TO BE PITTED.						1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002031100024	20020311	00024	EU  	2002	3	11	CA020225007      	2	20020225	G	8530	N854115	EXHAUST VALVE   	ROTAX       	913435      	DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					CYLINDER HEAD	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE VALVE SEAT ON THE EXHAUST VALVE FROM CYLINDER NR 2 WAS FOUND TO BE DISHED.						1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002031100025	20020311	00025	SW  	2002	3	11	CA020226001      	1	20020202	G	7810	114018201	COVER           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					EXHAUST DIFUSER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE DAILY INSPECTOIN, DAMAGE TO THE M/R BLADE WAS NOTICED.  INSPECTION OF THE AIRCRAFT REVEALED THAT THE CO	VER, EXHAUST DIFFUSER, HELD BY A SPEC.  BOLT  AND TABWASHER ON THE COVER, TURB., REAR  WAS MISSING. THE BOLT & TABWASHER	 WHERE STILL IN PLACE ON THE REAR TURB. COVER. IT SEEMS THAT THE EXHAUST DIFFUSER COVER HAD DISINTEGRATED AND ONE PIECE,	 APPROX 1 INCH LONG AND .250 INCH  WIDE (APPROX 1.0 GR.) WAS SENT THROUGH THE ROTOR DISC FROM THE TAILROTOR, CAUSING THE	 MAIN ROTOR BALDE DAMAGE. BLADE CHANGE AND SPEC. INSPECTION AS PER MAINTENANCE MANUAL WILL BE CARRIED OUT.		1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002032100023	20020321	00023	CE  	2002	3	21	CA020226002      	1	20020226	G	7800	175400125	MUFFLER         	CESSNA      	175400125   	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ON ENGINE	CRACKED         	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				NONE					(CAN) FOUND DURING AD CF90-03R2 MUFFLER INSPECTION. CRACK FOUND AT BASE OF TAIL PIPE TO MUFFLER CAN CONNECTION. (ALONG W	ELD BEAD.)MUFFLER REPLACED IN ACCORDANCE ADCF90-03R2. PART 1 SUB PART 5.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002032500006	20020325	00006		2002	3	25	CA020226003      	4	20020213	G	3160	9788132012	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CAWS	FAILED          	W				E				ENGINE SHUTDOWN         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) - POWER FAILURE IN CAWS DISPLAY UPON START UP.- DISPLAY & CONTROL UNIT REMOVED DIRECTED FOR BENCH CHECK.- REPLACED	 DISPLAY & CONTROL UNIT, NORMAL OPERATION RESULTS.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002050300006	20020503	00006	EU  	2002	5	3	CA020226004      	2	20020214	G	8550	V9277	FITTING         	GODFREY     	139153      	GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  	ROTOL	R4304	R1844304    	EU  	SUPERCHARGER	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA						23977					(CAN) GEARBOX LOW OIL PRESSURE LIGHT CAME ON, ENGINE SHUTDOWN AND AIRCRAFT LANDED. GEARBOX OIL LEVEL FOUND LOW BUT STILL	 ON DIP STICK. OIL LEAK TRACED TO FAILED FITTING ON SUPERCHARGER. UNIT HAS OVERHAUL LIFE OF 2,500 HOURS. LINE IS PRESSUR	E CHECKED (LOW PRESSURE) AT OVERHAUL. CRACK INITIATED FROM UNDER (B) NUT AND WOULD NOT HAVE BEEN VISIBLE AT OVERHAUL. OF	 4 EXTERNAL LINES ON UNIT ONLY LINE FROM GEARBOX IS REPLACED AT OVERHAUL. THESE LINES ARE SUBJECT TO HANDLING STRESS. WE	 ARE LOOKING AT HAVING ALL LINES REPLACED AT EACH OVERHAUL.  NOTE: SUPERCHARGER P/N 139312, USES AN OIL LINE WITH BANJO 	FITTINGS AND CAN THEREFORE BE INSPECTED TO GREATER DEGREE AT OVERHUAL.	2	L	7	2 	4T	4	T	 	1A17    	E297	6	C	P899	 
2002031100026	20020311	00026	NE  	2002	3	11	CA020226005      	2	20020207	G	7314	02532330003	PUMP            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, NOTICED A DRIP OF FUEL COMING OFF OF THE ENGINE DRIVEN FUEL PUMP TO ENGINE FLANGE. W	ITH A CLOSER LOOK FOUND A BROWN STAIN AS WELL. REMOVED ENGINE DRIVEN FUEL PUMP ASSEMBLY AND INSPECTED. FOUND SPLINE DRIV	E COUPLING WHICH ENTERS THE ENGINE ACCESSORY CASE CORRDED AND SEVERELY WORN. ENGINE DRIVEN PUMP ASSEMBLY REPLACED.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002032500007	20020325	00007	CE  	2002	3	25	CA020226008      	1	20020220	G	2823	NAS561P36	ROLL PIN        	CESSNA      	12161061    	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					YOKE	SHEARED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) FUEL SELECTOR WOULD NOT ROTATE VALVE. DISASSEMBLED AND FOUND PIN SECTION MISSING ALLOWING HOUSING YOKE TO ROTATE O	N SHAFT. PIN REPLACED.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2002032500008	20020325	00008	EA  	2002	3	25	CA020226009      	1	20020213	G	5610	6003303026	WINDSHIELD      			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) ENROUTE TO KINGSTON, JAMAICA, FROM TORONTO, A CRACK OCCURRED IN THE FACEPLY OF THE CO-PILOT'S WINDSCREEN. ON DESCE	NT INTO KINGSTON, THE PLY BEGAN TO DELAMINATE. APPROXIMATELY 2/3'S OF THE FACE PLY DEPARTED THE AIRCRAFT PRIOR TO TOUCHD	OWN IN JAMAICA.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500009	20020325	00009	NM  	2002	3	25	CA020226011      	1	20020223	G	2910	82970009129	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			31242								(CAN) UPON A WALK AROUND INSPECTION, MAINTENANCE NOTICED A LARGE AMOUNT OF FLUID DRIPPING FROM THE LEFT NACELLE. THE LEF	T MAIN LANDING GEAR DOORS MECHANICAL SEQUENCE VALVE "DOWN" PRESSURE LINE WAS FOUND LEAKING. THE LINE WAS REPLACED AND TH	E SYSTEM LEAK CHECKED AND SERVICED PRIOR TO RETURNING THE AIRCRAFT TO SERVICE				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002032500010	20020325	00010	NM  	2002	3	25	CA020226012      	1	20020222	G	2910	82950010269	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			28282								(CAN) THE FLIGHT CREW REPORTED A HYDRAULIC FLUID LEAK FROM THE RT NACELLE AND NR 4 FLAP TRACK AREA.MAINTENANCE FOUND THE	 NR 1 HYDRAULIC SYSTEM "DUMP" LINE FOR THE RT INBOARD SPOILER LEAKING. THE LINE WAS REPLACED AND THE SYSTEM LEAK CHECKED	 AND FUNCTION CHECKED PRIOR TO RETURNING THE AIRCRAFT TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002032500011	20020325	00011	NM  	2002	3	25	CA020226013      	1	20020225	G	2497	242110037C12A1	WIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUSELAGE	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			35067								(CAN) FLIGHT CREW REPORTED THAT THE LEFT INTAKE HEATER ADAPTER WAS INTERMITTANT AND LEFT AC "A" PHASE VOLTAGE SHOWED 64-	80 VOLTS. AFTER MANY COMPONENTS WERE REPLACED FOR TROUBLESHOOTING, BURNED WIRING WAS FOUND BENEATH THE ENTRANCE FLOOR (W	IRING TROUGH) FOR THE AC SYSTEM. THE WIRING WAS REPAIRED IN ACCORDANCE TO SYD 8-24-005. NOTE: AD CF 98-08R2 ADDRESSES SI	MILAR PROBLEMS BUT DOES NOTAFFECT THIS AREA OF THE TROUGH!THIS WIRING WAS CHAFED AGAINST THE TROUGH WHICH OVERHEATED AND	 BURNT THROUGH "A" PHASE. "B" AND "C" PHASE WIRING WAS ALSO DAMAGED BUT NOT A BAD AS "A" PHASE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002050300007	20020503	00007	CE  	2002	5	3	CA020226014      	1	20020221	G	5610	1013840257	WINDSHIELD      			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ENROUTE AT FL210 THE OUTER PANE OF THE LEFT  WINDSHIELD CRACKED.  CREW MADE NORMAL DESCENT TO LOWER ALTITUDE, REDU	CED PRESSURIZATION AND RETURNED TO LAND. PART WAS REPLACED WITH NEW P/N 101-384025-21.					1	L	7	2 	4T	4	T	 	A31CE   	E4EA	6	C	P56GL	 
2002032500012	20020325	00012	EU  	2002	3	25	CA020226016      	1	20020222	G	5244	5711012367	ATTACH FITTING  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	OIL COOLER DOOR	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS IN ROUTE TO HOME BASE AND 20 MINUTES INTO ITS FLIGHT WNEN THE OIL TEMPERATURE DROPPED FROM 60 C TO 40	 C AND THE OIL PRESSURE WENT UP THE BOTTOM OF THE RED LINE WHICH IS 130 PSI.THE PROBLEM WAS THE OIL COOLER DOOR HINGE HO	LDER CRACKED AND ALLOWED THE DOOR TO BE INEFFECTIVE IN CONTROLLING THE TEMPERATURE OF THE OIL.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002032500013	20020325	00013	WP  	2002	3	25	CA020227001      	2	20020219	G	7322	307080022	FUEL CONTROL    			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					LT ENGINE	DEFECTIVE       	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			TX	TAXI/GRND HDL  	1			CA											(CAN) LT ENGINE HOT START ON MANUAL AND COMPUTER MODE. LT FCU REPLACED, GROUND RUNS C/O, GROUD CHECK SERVICEABLE.						2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2002040900024	20020409	00024	SW  	2002	4	9	CA020227002      	1	20020225	G	6310	CL422501	CAGE            	BELL        	20604023013 	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					SPRAG CLUTCH	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						B12539					(CAN) THE FREEWHEEL UNIT WAS REMOVED EARLY FOR ITS 1500 HOUR INSPECTION FOR MAINTENANCE CONVIENIENCE.  DURING INSPECTION	 IT WAS NOTED THAT THE CAGE WINDOWS WERE WORN BEYOND THE 0.004					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002030400124	20020304	00124	NE  	2002	3	4	CA020227003      	2	20020131	G	8520	SL74309	BEARING         	LYC         	TIO540J2B   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2B   	 	NE  	HARTZL	HCC4Y	HCC4YR2     	GL  	BEARING	DESTROYED       	W			    	K	 	 	 	NONE                    				Y	 	 	ENGINE STOPPAGE           			IN	INSP/MAINT     	1			CA		 				L429361A					(CAN) #6 CON ROD BEARING FAILURE. PARTS RETURNED TO SUPERIOR AIR PARTS FOR EXAMINATION.THESE BEARINGS ARE A BIMETAL AS O	PPOSED TO A TRIMETAL THAT WAS USED FOR MANY YEARS. I HAVE RECIEVED REPORTS FROM AUSTRALIA OF SEVERAL FAILURES OF THIS TY	PE OF BEARING				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P52GL	 
2002032500014	20020325	00014	EU  	2002	3	25	CA020227004      	1	20020226	G	3242	9462061335	SWIVEL          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG BRAKE SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYD BRAKE FLUID WAS NOTED LEAKING FROM THE SWIVEL FITTING ON THE BRAKE LINE ,LT MLG TRAILING LINK AREA. PART REPLA	CED WITH NEW, BRAKES BLED, RETURNED TO SERVICE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002050300008	20020503	00008	CE  	2002	5	3	CA020227005      	1	20020227	G	3233	11238002223	ACTUATOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) DURING NORMAL APPRAOCH, CREW EXTENDED LANDING GEAR BUT DID NOT GET A NOSE GREEN. GEAR WAS CYCLED WITHOUT CHANGE. E	MERGENCY PROCEDURES PROVIDED FOR MANUAL EXTENSION BUT STILL WITHOUT GREEN. DUE TO SYSTEM WIRING, THE GEAR WAS ASSERTAINE	D DOWN DUE TO THE ABSCENCE OF A RED HANDLE LIGHT WHICH FUNCTIONED NORMALLY. THE GREEN AND RED LIGHTS FUNCTION OFF A DOUB	LE POLE SWITCH PROVIDING SOME ASSURANCE OF ACTUAL GEAR POSITION DURING MALFUNCTIONS. DURING TROUBLESHOOTING, THE GEAR FU	NCTIONED NORMALLY WITH ALL LIGHTS OPERATING PROPERLY, HOWEVER, THE NOSE GEAR ACTUATOR WAS REPLACED FOR PRECAUTIONARY REA	SONS AND THE AIRCRAFT RELEASED AFTER NUMEROUS GEAR CYCLES.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002041700071	20020417	00071	NE  	2002	4	17	CA020227007      	3	20020224	G	6197	1293640919	WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	AUTOFEATHER SYS	SHORTED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) DURING CRUISE FLT,  CREW NOTICED FAINT SMOKE SMELL, & NOTICED THAT PROP AUTOFEATHER CIRCUIT BREAKER HAD POPPED. TH	EY DECIDED TO RETURN TO YYC. DURING APPROACH / LDG PHASE OF FLT, SMELL OF SMOKE BECAME MORE NOTICEABLE. THE LDG & TAXIIN	G TO GATE WENT UNEVENTFULLY. DURING MAINT INVEST. SEVERAL WIRES ON BACK OF AUTOFEATHER OFF/ON/ TEST SWITCH WERE SHORTED 	/ MELTED.  FURTHER INVEST. REVEALED SHORTED / MELTED WIRES ON POWER LEVER MICROSWITCHES FOR AUTOFEATHER,  TRACING SYS FU	RTHER IT NOTICED THAT A123 PRINTED CCT BOARD P/N 129-364091-9 HAD BURNT TRACKS & DAMAGED COMPONENTS ON IT. ALL COMPONENT	S&WIRING WILL BE TESTED/REPL, FOLL OWED BY EXTENSIVE GROUND CHECK OF ENTIRE AU	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002031100029	20020311	00029	EU  	2002	3	11	CA020227009      	2	20020216	G	7322	961215	NEEDLE          			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					CARBURETOR	SHEARED         	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT SUDDEN ROUGHNESS OCCURRED,  PROP UNRESPONDSIVE WITH POWER FULL, AIRCRAFT RAN ROUGH THE WHOLE FLIGHT 	BACK, UNABLE TO MAINTAIN ALTITUDE, SLOW DESCENT APPROX 100 FEET/MIN FROM BIRDS HILL TO ST. ANDREWS. WINGS REMOVED AND AI	RCRAFT TRANSOORTED TO WINNIPEG BASE, UPON INSPECTION FOUND L/H CARB NEEDLE SHEARED, NEEDLE AND CIRCLIP REPLACED, RT CARB	 INSP, WINGS REINSTALLED, SAFETIED AND TRAVEL CHECKED, PITOT STATIC TEST CARRIED OUT AS PER AWM 511 APPENDIX B. NO DEFEC	TS NOTED. AIRCRAFT GROUND RUN AND LEAK CHECKED SERVICEABLE.		1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002032500016	20020325	00016	NM  	2002	3	25	CA020227010      	1	20020226	G	3230		LATCH           			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING GEAR RETRACTION LEVER LATCH FAILED TO RELEASE ALL OTHER INDICATIONS NORMAL.REPAIRED WIRING AT LEVER LOCK SO	LENOID BY REPLACING TERMINAL CONNECTOR LEVER LOCK SYSTEMM OPS TESTED AS PER MM 32-31-11. NO FURTHER DISCREPANCY.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002032500017	20020325	00017	SO  	2002	3	25	CA020227011      	1	20020222	G	2510	ASABOVE	FRAME           			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					SEAT	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) BOTH LT AND RT UPPER FORWARD WELD JOINTS FAILED ON SEAT FRAME ASSEMBLY.  THE SEAT ASSEMBLY IS VERY DIFFICULT TO IN	SPECT IN THIS AREA AS IT IS COVERED WITH UPHOLSTERY.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002032500018	20020325	00018	SO  	2002	3	25	CA020227013      	1	20020222	G	2520		FRAME           			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					SEAT	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) BOTH LT AND RT UPPER FORWARD WELD JOINTS FAILED ON SEAT FRAME ASSEMBLY.THE SEAT ASSEMBLY IS VERY DIFFICULT TO INSP	ECT IN THIS AREA AS IT IS COVERED WITH UPHOLSTERY.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2002032500019	20020325	00019		2002	3	25	CA020228001      	4	20020217	G	3417	34100408	ADC             			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) JUST AFTER TAKEOFF CAPTAINS AIRSPEED, STANDBY AIRSPEED, GROUND PROX WARNING, AND MACH TRIM INDICATORS FAILED. AIRC	RAFT RETURNED TO AIRPORT. NR 1 CENTRAL AIR DATA COMPUTER REPLACED AND OPERATION CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002032500020	20020325	00020	NM  	2002	3	25	CA020228002      	1	20020123	G	3211	NHA65B0150211	BEARING         			BOEING	747   	747475      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						MHB950					(CAN) RT BODY GEAR RETRACT ACTUATOR,, LOWER BEARING FAILED.FOUND SPHERICAL BEARING INNER RACE CRACKED THROUGH. LARGE PIE	CE OF INNER RACE BROKEN OUT.   ROLLERS CORRODED AND MISSING. WATER INGRESSION TO BEARING EVIDENT UPON DISASSEMBLY.  HIGH	 LEVEL OF CORROSION TO ROLLERS AND INNER RACE. RETAINING RING AND ATTACHING HARDWARE WORN THROUGH.  END ASSEMBLY REPLACE	D.END ASSEMBLY - 65B01531-4 P/N NHA 65B01502-11 S/N MHB950			2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2002032500021	20020325	00021	EU  	2002	3	25	CA020228003      	1	20020212	G	5530	D5537002500800	PANEL           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERTICAL STAB LEADING EDGE PANELS 322AL, 322CL AND 322BL CRACKED. PANEL 322AL CRACKED APPROXIMATELY 4 INCHES FROM 	LOWER EDGE LT SIDE. PANEL 322CL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. ALSO 322BL. PRODUCTION PERMIT RA	ISED FOR REPAIR IF BEYOND LIMITS.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002032500022	20020325	00022	EU  	2002	3	25	CA020228004      	1	20020212	G	2740	D55981002	FITTING         			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					RT & LT STAB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT THS REAR ATTACH BEARING FOUND LOOSE IN REAR YOKE FITTINGS.BORES IN THE THS LT AND RT REAR SUPPORT FITTIN	G  FOUND BEYOND PRODUCTION TOLERANCES.  BUSHINGS WILL BE NICKEL PLATED TO RETURN OD DIAMETER. THIS CONSIDERED A PERMANEN	T FIX FOR THE RT FITTING AND TEMPORARY REPAIR & THE LT IS ACCEPTABLE FOR 4000 FLIGHT CYCLES, AWAITING AIRBUS FINAL DISPO	STION.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002032500023	20020325	00023	NM  	2002	3	25	CA020228005      	1	20020212	G	5532	D5537002500800	PANEL           			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERTICAL STAB LEADING EDGE PANELS 322AL AND 322CL CRACKED.  PANEL 322AL CRACKED APPROXIMATELY 4 INCHES FROM LOWER 	EDGE LT SIDE. PANEL 322CL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002032100024	20020321	00024	EA  	2002	3	21	CA020228008      	1	20020214	G	5610	NP1393225	WINDOW          	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  	 		            		CAPTAIN SIDE	CRACKED         	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				7082					(CAN) DURING FLIGHT L-2 WINDOW DEVELOPED A CRACK. CAPTAINS SIDE WINDOW REPLACED AS PER AIRCRAFT MAINTENANCE MANUAL 56-12	-01.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032100025	20020321	00025	EA  	2002	3	21	CA020228009      	1	20020204	G	2760	3G5209C	SPOILER         	            	            	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  	 		            		L/H OUTBOARD	FAILED          	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 									(CAN) SPOILER FAULT EICAS INDICATES LEFT OUTBOARD SPOILER PROBLEM (WHITE BOX).SEVERAL PREVIOUS SNAGS OCCURRED WITH SYSTE	M CHECKED OUT AND NO FAULTS FOUND (INTERMITTENT FAULT). WIRING CHECKED OUT NO FAULT FOUND.FLIGHT SPOILER CONTROL LEVER H	ANDLE REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500024	20020325	00024	EA  	2002	3	25	CA020228010      	1	20020205	G	2760	270003	PCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					SPOILERS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLIGHT SPOILER CAUTION MESSAGE CAME ON DURING APPROACH.  WENT OUT AFTER LANDING. INTERMITTENT PROBLEM THAT OCCURRE	D SEVERAL TIME IN RECENT PAST. SECU (SPOILER ELECTRONIC CONTROL UNIT) NR 1 FAULT CODES 02,51,E8 DISPLAYED. SECU NR 2 FAU	LT CODES EC,52,EA DISPLAYED. RIGHT OUTBOARD SPOILER PCU (POWER COANTROL UNIT) REPLACED AND RIGGED. SECU NR 1 AND 2 REPLA	CED.  SYSTEM RESET AND OPERATION CHECKED SERVICEABLE. PCU  P/N 27000-3SECU P/N 49-164-05			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002030400125	20020304	00125	EA  	2002	3	4	CA020228012      	2	20020216	G	7323		GOVERNOR        	BENDIX      	25249994    	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  	 		            		GOVERNOR	                	W			    	D	 	 	 	RETURN TO BLOCK         				E	 	 	VIBRATION/BUFFET          			HO	HOVERING       	1			CA		 				C8103					(CAN) COCKPIT INDICATION OF ENGINE TORQUE SPLIT DURING HOVER TAXI, AIRCRAFT RETURNED TO RAMP. TORQUE SPLIT CAUSED BY N2 	GOVERNOR FAILURE CONFIRMED BY UNIT REPLACEMENT.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002031100036	20020311	00036	SW  	2002	3	11	CA020228013      	1	20020201	G	6220	222010405115	SLEEVE          	BELL        	222010400121	BELL  	222   	222B        	1182124	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					SWASHPLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						EA73					(CAN) WHEN SWASH PLATE ASSY WAS REMOVED TO FACILITATE 7 YEAR MAST REMOVAL FOR INSPECTION AND RECALIBRATION, THE SLIDER B	EARINGS (2OF) P/N 222-310-464-003 WERE FOUND DETACHED AND LOOSE, CREATING AN EXCESSIVE WEAR ON THE SLEEVE JOURNALS THAT 	HOUSE THESE BEARINGS TO A POINT WELL BEYOND CONTINUED AIRWORTHINESS. THE BALL SLEEVE ASSY AND SUPPORT WERE DEEMED UNSERV	ICEABLE AND WERE REPLACED AT GREAT EXPENSE.			1	G	7	2 	3U	3	U	 	H9SW    	E5NE				 
2002032500026	20020325	00026	EA  	2002	3	25	CA020228014      	1	20020222	G	2720	8220287401	CIRCUIT CARD    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RUDDER CONTROL	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER EXCEEDING 250 KTS IAS, RUDDER FLUTTERED UNTIL AIRCRAFT WAS IN LANDING CONFIGURATION. REMOVED AND REPLACED LE	FT (UPPER) LHP-4000 CARD IAW AIRCRAFT MM 22-12-01. OPS CHECKED GOOD ON GROUND.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041600007	20020416	00007	EA  	2002	4	16	CA020228015      	1	20020228	G	5610	NP13932110	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			13551								(CAN) THE WINDSHIELD INSTALLED WAS A POST SERVICE BULLETIN WINDSHIELD.  RT WINDSHIELD CORE PLY CRACKED IN CRUISE AT FL 3	50. FLIGHT DIVERTEDREMOVED AND REPLACED WINSHIELD. AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002031100037	20020311	00037	NM  	2002	3	11	CA020228016      	1	20020202	G	7920	920024647	HOSE            			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					ENGINE	RUPTURED        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) TURBO OIL SUPPLY HOSE FROM OPTIONAL FILTER P/N 300180-501 TO WAISTGATE ACTUATOR ROUTED IN CLOSE PROXIMITY TO EXHAU	ST PIPES WITH SHARP BENDS DUE TO EXTREMITY TIGHT ROUTING. ADDITIONALLY THIS HOSE IS DISTURBED EVERY 50 HOURS DUE TO REMO	VAL AND CLEANING OF FILTER ELEMENT CLEANING, SUBJECTING HOSE TO ADDITIONAL STRESSES. HOSE FAILED IN CLIMB OUT, RESULTING	 IN LOSS OF OIL PRESSURE.			1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2002032500027	20020325	00027	NM  	2002	3	25	CA020228017      	1	20020205	G	3320		LIGHT           			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					ROW 20A	BURNED OUT      	W				H				DEACTIVATE SYST/CIRCUITS				A			FLAME/FIRE                			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION MAINTENANCE NOTICED THE LT SIDEWALL LAMP (FORWARD SHORT OR SECOND FROM THE BACK) AT ROW 20A W	AS FOUND BURNED. THE LAMP WAS REPLACED AND APPROXIMATELY 1 HOUR LATER WE HAD A FIRE. THE CREW IMMEDIATELY TURNED THE LIG	HTS OFF AND PULLED THE CB. THE 20 AMP CB DID NOT POP. THE ASSEMBLY WAS REMOVED AND REPLACED.IT WAS NOTED THAT THE LOCKIN	G RELEASE DID NOT PROTRUDE AS MUCH AS THE NEW ASSEMBLY INSTALLED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002032500028	20020325	00028	NM  	2002	3	25	CA020228019      	1	20020223	G	2913	6617302	PUMP            			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					HYD SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING A FLIGHT THE AIRCRAFT LOST THE RT HYDRAULIC SYSTEM DUE TO PUMP FAILURE DURING CRUISE, AFTER USING THE POWER	 TRANSFER UNIT (LEFT TO RIGHT HYDRAULIC PUMP) FOR GEAR EXTENSION, NO FLAP MOVEMENT OBSERVED (LEFT HYDRAULIC SYSTEM), A F	LAPLESS LANDING WAS PERFORMED.  NR 2 EDP REPLACED. CASE DRAIN FILTER BADLY CONTAMINATED WITH METAL. CASE DRAIN, RETURN A	ND PRESSURE FILTERS REPLACED. ENGINE UNS CARRIED OUT, ALL THREE FILTERS REPLACED, SYSTEM BLEED AND SERVICED. AIRCRAFT RE	LEASED FOR 25 HOURS PRIOR TO REPLACING FILTERS AGAIN.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002050300009	20020503	00009	EA  	2002	5	3	CA020228020      	1	20020215	G	3260	6015778827	INDICATOR       			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF34*       	 	NE  					NLG	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) AFTER LANDING, GEAR SELECTED TO DOWN, ALL 3 GEAR GREEN ILLUMINATED BUT FLASHING LIGHT IN GEAR HANDLE REMAINED ON. 	 CYCLED GEAR UP,  NLG GREEN DOWNLOCK INDICATION AND HANDLE FLASHER REMAINED ON. NO NOSEGEAR DOOR LIGHTS ILLUMINATED, DID	 NOT HEAR SOUND OF NOSEGEAR RETRACTING.  CYCLED WITH SAME EFFECT. DID FLYBY OF TOWER. MAINS WERE DOWN BUT NO SIGN OF NOS	EGEAR AND NOSE DOORS WERE CLOSED.  RETURNED TO AIRPORT,   SELECTED GEAR DOWN AND PULLED MANUAL RELEASE HANDLE. ALL 3 GEA	R EXTENDED AS CONFIRMED BY GROUND SUPPORT. NOW INDICATIONS WERE BOTH MAIN GEAR GREEN DOWNLOCK ILLUMINATED, BUT NOSEGEAR 	GREEN DOWNLOCK LIGHT WENT OUT. FLASHER IN GEAR HANDLE ALSO WENT OUT. A/C LANDED WITHOUT INCIDENT.	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2002032500029	20020325	00029	NE  	2002	3	25	CA020301001      	2	20020228	G	7250		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) A/C 7216, FLT 5266 FROM ATW TO CVG. PRELIM INFO.AT 3000 FEET IN CLIMB RIGHT ENGINE SHUTDOWN DUE TO VIBRATION. RETU	RNED TO ATW. AFT END (LPTM) OF NR 2 ENGINE MISSING. RIGHT HORIZ STAB L/E DAMAGED. VERTICAL STAB APPARENTLY HAS A SMALL H	OLE. NO CONFIRMATION OF ANY FUSELAGE PENETRATION OR DENTS. PIE FAIRING DAMAGED. MAINT CREW ALREADY ON GROUND AT ATW SEND	ING REPL ENGINE, 2 CORE COWLS, PIE FAIRING&JETPIPE CONE. MORE DETAILS WILL BE FURNISHED WHEN KNOWN. ENGINE IS ORIG EQUIP	, DELIVERED ON FEB 26, 1998. NO PREVIOUS HISTORY ON ENGINE OTHER THAN ON FEB 10/11 IN ORLANDO FAN BLADES 7 THRU 28 BLEND	ED OUT FOR ROUGHNESS & R. INLET CROSION ON LOWER HALF REPD.ADD: 2-28-2002 NEGEL KEYS - ARRIVE D ON-SITE AT 22:00 APPROX 	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500030	20020325	00030	EA  	2002	3	25	CA020301002      	1	20020301	G	5610	601R330331	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			15704								(CAN) LEFT WINDSHIELD CRACKED DURING DESCENT. REMOVED AND REPLACED WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500031	20020325	00031	EA  	2002	3	25	CA020301003      	1	20020301	G	5610	NP1393222	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, COPILOT WINDOW INNER PLY SHATTERED. AIRCRAFT LANDED SAFELY. NEW WINDOW INSTALLED P/N NP-139322-6 AN	D S/N 01138H8148.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500032	20020325	00032		2002	3	25	CA020301004      	4	20020301	G	6113	055032111	BULKHEAD        	CESSNA      	055032111   	CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						NONE					(CAN) SPINNER WAS NOTICED DEFORMED DURING GROUND HANDLING.SPINNER BULKHEAD FOUND CRACKED AND FLANGE SEPERATED CAUSING SP	INNER DEFORMATION.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2002032500033	20020325	00033	SO  	2002	3	25	CA020304001      	1	20020227	G	5740	4029400	FITTING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16370	16370							(CAN) INSPECTION REVEALED A SMALL CRACK IN THE WEB WHERE IT JOINS THE LOWER RIGHT BOLT HOLE.THE CRACK RUNS PERPENDICULAR	 TO THE WEB.PART TIME IS UNKNOWN, TIME GIVEN IS AIRFRAME TIME.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002032500034	20020325	00034	NE  	2002	3	25	CA020304002      	2	20020301	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RIGHT	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			13218								(CAN) DEPARTURE FROM SAN ANTONIO, TEXAS DURING CRUISE PHASE OF FLT NR 2 ENGINE EXHIBITED OIL TEMP OF 185C & PRESSURE OF 	27 PSI. CREW C/W WITH AFM PROCEEDURES & SHUTDOWN ENGINE. CREW DECLARED EMERGENCY & LANDED IN EL PASO, TEXAS. MESA SENT 2	 MECHANICS TO INVESTIGATE. DURING INVEST. OIL FOUND IN TAIL PIPE & OIL FILTER FOUND TO HAVE CARBON RESIDUE / PIECES IN I	T ALSO CARBON RESIDUE FOUND IN B-SUMP SCREENS. GE REP CONSULTED. IT DETERMINED WITH GE THAT ENGINE EXPERIENCED "B-SUMP C	OKE SHEDDING". GAE SUGGESTED THAT MX CLEAN ALL SCREENS REASSEMBLE & RUN ENGINE AT CRUISE POWER FOR 1 HR THEN REMOVE & CH	ECK FILTER&SCREENS. FINDING WERE GOOD. A/C THEN FAIRIED TO FRES NO & CHECKED AGAIN PER GE SB 79-0014&AD 2001	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041700073	20020417	00073	EA  	2002	4	17	CA020304003      	1	20020225	G	2510	C3FF3143	FORK            			DHAV  	DHC6  	DHC6        	2802606	EA  										SEAT BELT	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PART NOT MANUFACTURED AS PER DEHAVILLAND/BOMBARDIER SPEC. FOUR FORKS FROM INVENTORY FOUND NOT FILLET RADIUS TO O.0	31 INCH. SEVEN OF EIGHT ON AIRCRAFT SEATS NOT FILLET RADIUS TO O.031 INCH. THIS MAY PUT UNDUE STRESS ON HEAD OF BOLT LEA	DING TO SEAT BELT RETENTION FAILURE. THESE FORK ARE USED ON ALL POST MOD 6/1601 OR S.O.O.6104 SEATS				1	H	7	2 	3T			RT	A9EA    					 
2002050300010	20020503	00010		2002	5	3	CA020304004      	4	20020219	G	6113	07526371	BULKHEAD        			CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SPINNER BULKHEAD FOUND MOUNTED BETWEEN PROP AND CRANKSHAFT FLANGE - BULKHEAD SUPPOSED TO BE MOUNTED ON REAR RACK O	F CRANKSHAFT FLANGE.  INCORRECT MOUNTING RESULTED IN  CRACKED BULKHEAD AND PROP HUB DISTORTION LEADING TO FLUID LOSS.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2002032500035	20020325	00035	EA  	2002	3	25	CA020304005      	2	20020301	G	8520		CONNECTING ROD  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING A SHORT FLIGHT APPROXIMATLY 5 MINUTES.  AFTER T/O, PILOTS NOTICED A FAINT CLICKING NOISE FOLLOWED IMMEDIATL	Y BY A SLIGHT VIBRATION THEN SMOKE FROM THE LT ENGINE. THE ENGINE WAS SHUT DOWN AND FEATHERED IMMEDIATLY. AFTER LANDING 	VISUAL INSPECTION CONFIRMED THE NR 6 CONNECTING ROD HAD PENETRATED THE CRANKCASE ABOUT 2-3 INCHES OUTBOARD OF THE CASE S	PINE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002032500036	20020325	00036	EU  	2002	3	25	CA020304006      	2	20020222	G	7320	77208602	SLEEVE          	TRW         	CASC509     	FOKKER	F27   	F27MK100    	4990617	EU  	RROYCE	TAY   	TAYMK65015  	 	EU  					GOVERNOR ASSY	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						1751					(CAN) TWO FUEL FLOW REGULATORS RECEIVED  HAD SLIPPER SLEEVE ASSEMBLIES INSTALLED IN REVERSE MODE. THESE UNITS HAD BEEN P	REVIOUSLY REPAIRED BY ROLLS ROYCE BRAZIL AND IT IS ESTIMATED THAT THERE MAY BE 11 (ELEVEN) SIMILAR UNITS. THIS CONDITIIO	N HAS BEEN ASSOCIATED WITH POSSIBLE LOW FLOW AND LOW EPR.				2	H	7	2 	4T	4	F	 	A817    	 				 
2002032500037	20020325	00037		2002	3	25	CA020305002      	4	20020220	G	2210		AUTOPILOT SYS   			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH WITH THE AUTOPILOT ENGAGED WHEN AT APPROX. 6300 FT, THE AIRCRAFT PITCHED UP 5-10 DEGREES AND THE AUTO 	THROTTLES MOVED FORWARD. THE AUTOPILOT WAS DISENGAGFED BY THE COPILOT AND THE AIRCRAFT CONTINUED ITS APPROACH WITH THE A	UTOPILOT OFF AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE COMPLETED A SERIES OF AUTOPILOT TESTS AND WER	E UNABLE TO IDENTIFY ANY DISCREPANCIES. OPERATOR HAS SENT THE FLIGHT DATA ACQUISITION DATA TO BOEING AND THE AUTOPILOT M	ANUFACTURER, HONEYWELL ASKING THEM TO PROVIDE AN EXPLANATION AS TO WHAT MAY HAVE CAUSED THE DATA AIRPLANE TO DEPART THE 	FLIGHT PLAN.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2002032500038	20020325	00038	NM  	2002	3	25	CA020305003      	1	20020222	G	2697		WIRE            			BOEING	737   	737297      	1384480	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					APU BAY	CHAFED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN)  DURING FLT A/C EXPERIENCED FLICKERING LT WING BODY OVERHEAT INDICATION WITH INCREASING FREQ. OVERHEAT LIGHT ILLUM	INATED OFF & FLICKERED ON & OFF CONTINUOUSLY WHEN LT ENGINE BLEED VALVE & ISOLATION VALVE WERE CLOSED (WITH APU OFF).  F	LT CREW CONTACTED MCC & CYCLED VALVES WITH NO RESOLVE.DUE TO ICING CONDITIONS ENROUTE & INABILITY TO CONFIRM BLEED AIR W	AS ISOLATED - A/C WAS DIVERTED TO FOR PRECAUTIONARY LDG. FLT CREW PERFORMED ENGINE RUNS & COULD NOT FAULT.  MAINT CALLED	 OUT TO INSPECT - INDICATION PROBLEM WAS ISOLATED TO A SEVERELY CHAFED WIRE IN APU AREA  OF OVERHEAT LOOP. TEMP REPAIR C	ARRIED OUT.A/C RT-SRV WITH NO FURTHER INCIDENTS TO REPORT.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002032500039	20020325	00039	EA  	2002	3	25	CA020306001      	2	20020223	G	7200		COMPRESSOR      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RT ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E	A		VIBRATION/BUFFET          	FLAME/FIRE                		CR	CRUISE         	1			CA			17593								(CAN)   THE AIRCRAFT WAS IN CRUISE FLIGHT AT FL20000. THERE WAS A LOUD BANG THAT SHUCK THE AIRCRAFT AND FLAMES APPEARED 	COMING OUT OF THE EXHAUST STACKS. THE ENGINE WAS SHUT DOWN AND FEATHERED. FLAMES EXTINGUISHED RIGHT AWAY IN THE STAKES. 	THERE WAS A SMALL AMOUNT OF FLAME NOTICED IN THE LOUVERS OF THE BLEED AIR VALVE OUTLETS, THAT EXTINGUISHED AFTER A BRIEF	 PERIOD. THE AIRCRAFT CONTINUED AND LANDED WITHOUT ANY FURTHER DIFFICULTIES.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002032500040	20020325	00040	EA  	2002	3	25	CA020306002      	1	20020304	G	3234	7179015	HANDLE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG SELECTOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE, LOUD NOISE COMING FROM NOSE AREA AND MESSAGES (GEAR DISAGREE(W) AND NOSE DOOR (W) POSTED. MESSAGE CLEAR	ED BY THEMSELVES AFTER SEVERAL SECONDS. AIRCRAFT DID AN AIR TURN BACK WHERE IT LANDED SAFELY. AIRCRAFT WAS FERRIED FOR T	ROUBLESHOOTING. GEAR SWINGS WERE CARRIED OUT BUT UNABLE TO REPRODUCE SNAG. BASED ON THE SYMPTOMS, IT WAS ELECTED TO REPL	ACE THE PSEU AND THE LANDING GEAR HANDLE.PSEU REMOVED: P/N 8-648-08 S/N 221AIRCRAFT BACK IN SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500041	20020325	00041	NM  	2002	3	25	CA020306003      	1	20020301	G	2150		ACM             			BOEING	737   	737268      	138448Q	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ACM BAY	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FLIGHT 183 AIRCRAFT ON FLIGHT TO YWG FROM YHM AND AT CRUISING ALTITUDE, THE FORWARD LAV SMOKE DETECTOR ACTIVATED. 	THE FLIGHT ATTENDENTS ADVISED THE CAPTAIN OF SMOKE IN THE CABIN AND THE REAR SMOKE DETECTOR GOING OFF. FLIGHT CREW REQUE	STED PRIORITY LANDING ING YAM AND LANDED WITHOUT INCIDENT. CFR WAS CALLED OUT AND FOLLOWED AIRCRAFT TO THE GATE - NO REP	ORT OF SMOKE.MAINTENANCE IN YAM INSPECTED THE AIR CONDITIONING SYSTEM AND SUSPECTED THE LT ACM OIL EAS OVERSERVICED - AC	M WAS DRAINED AND AIR CONDITIONING SYSTEM WAS TESTED IAW MM 21-51-00 AND CHECKED SERVICEABLE - NO SMOKE (SMELL) PRESENT.	AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. AIRCRAFT GROUND CHECKED SERVICEABLE.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002032500042	20020325	00042	EU  	2002	3	25	CA020306004      	1	20020228	G	5610	9598110111	WINDOW          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  A CRACK WAS FOUND IN THE LT SIDE WINDOW IN THE TOP CORNER EXTENDING FORWARD AND AFT FROM A SCREW HOLE. THE CRACK 	WAS NOT VISIBLE INSTALLED IN THE AIRCRAFT.  IT WAS DISCOVERED WHILE REMOVING FOR A DIFFERENT REASON. SIDE WINDOW WAS REP	LACED AND AIRCRAFT RETURNED TO SERVICE. THE SIDE WINDOW CRACK WAS COVERED BY THE WINDOW/WINDSHIELD ONE PIECE RETAINER.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002032100026	20020321	00026	SW  	2002	3	21	CA020306005      	1	20020305	G	6220	204011143005	BARREL          	BELL        	204011140005	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  	 		            		INTERIOR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				A13534					(CAN) NDT REVEALED A 1.5 INCH CRACK ON THE INTERIOR OF THE COARSE THREADED END. THE CRACK IS NOT VISIBLE ON THE EXTERIOR	.					1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002040900083	20020409	00083		2002	4	9	CA020307001      	4	20020228	G	3457		POWER SUPPLY    			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					GPS RECEIVER	BURNED OUT      	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA						29472					(CAN) DURING ROUTINE SERVICEABILITY CHECK, WITH GROUND POWER APPLIED TO AIRCRAFT, STRONG BURING SMELL NOTICED IN AIRCRAF	T.GPS RECEIVER DISPLAY WENT BLANK. (GPS KLN 90B RECEIVER) SUBSEQUENT INSPECTION FOUND & CONFIRMED BURNING SMELL ORIGINAT	ED FROM GPS RECEIVER. RECEIVER REPLACED AND AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002032500043	20020325	00043	CE  	2002	3	25	CA020307002      	1	20020222	G	5312	07126161	BULKHEAD        			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470C       	17026	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REAR BULKHEAD FOUND CRACKED DURING IMPORT INSPECTION.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002050700107	20020507	00107	CE  	2002	5	7	CA020307003      	1	20020307	G	3260	1148200773	BRACKET         	            	            	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ATTACHMENT	CRACKED         	W			    	D	 	 	 	RETURN TO BLOCK         				N	 	 	FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA		 									(CAN) CREW BEGAN TAXI FROM OUTSTATION&NOTED THAT "GREEN" NOSEGEAR IND. EXTINGUISHED&"RED" UNSAFE IND. ILLUMINATED. A/C S	HUTDOWN, PAX DEPLANED&A/C CHOCKED. MAINT FOUND BRACKET THAT PROVIDES DO WN MICRO SWITCH STRIKE PLATE HAD CRACKED ACROSS 	ATTACHMENT FLANGE&WORKED ITS WAY UP ALLOWING MICROSWITCH TO "UNMAKE" DURING TAXI. GEAR DOWN&LOCKED&ONLY INDICATING UNSAF	E CONDITION. A/C FERRIED TO MAIN FACILITY FOR BRACKET REPL&GEAR SWINGS. A/C RT-SRV. DUE TO LOCATION OF CRACK, IT IS VERY	 DIFFICULT TO FIND AS HEADS OF ATTACH BOLTS&WASHERS OBSCURE CRACK BY APPROX 70%&ADDITIONAL LOCKWIRING A LSO HIDES DEFECT	. ALL CO A/C HAVE BE	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002032500044	20020325	00044	CE  	2002	3	25	CA020307004      	1	20020222	G	3211	07416032	SUPPORT         	CESSNA      	07416032    	CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470C       	17026	SO  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT LANDING GEAR OUTBOARD SUPPORT BRACKET CRACKED IN REAR CORNER FROM LANDING GEAR LEG ATTACH BOLT. FOUND ON IMPORT	 INSPECTION. PERIODIC REMOVAL OF LANDING GEAR LEGS FOR INSPECTION WOULD FACILITATE INSPECTION.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002032500045	20020325	00045	CE  	2002	3	25	CA020307005      	1	20020222	G	5330	LM07133343	SKIN            			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470C       	17026	SO  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FORWARD FUSELAGE SKIN CORRODED AT FORWARD SKIN BASE OF DOOR POST.  STRINGER ENGINE MOUNT CORRODED AT ENGINE MOUNT 	STRINGER.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002051300007	20020513	00007	SO  	2002	5	13	CA020307006      	1	20020306	G	3242	754612	DISK            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MLG BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION BOTH LT AND RT MAIN WHEEL BRAKE DISCS WERE FOUND CRACKED.  EACH HAD ONE 1/2 INCH CRACK ON THE RI	NG PORTION (BRAKING PORTION).					1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2002032500048	20020325	00048	GL  	2002	3	25	CA020307007      	3	20020304	G	6111	A1633109	O-RING          	MCAULY      	2A34C203BC  											MCAULY	2A34C	2A34C203    	GL  	PROPELLER	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						921402					(CAN) PROPELLER LEAKING RED DYE OIL FROM BLADE NR 2. BLADE NR 2 O-RING FOUND SHREDED WHICH WAS THE REASON FOR THE OIL LE	AK.  ALSO FOUND 2 CRACKED SLOT BLOCKS AND A WORN ACTUATING PIN ASSEMBLY.															5	C	P3EA	 
2002032500065	20020325	00065	CE  	2002	3	25	CA020307008      	1	20020228	G	3060	C40536	BRACKET         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	BRUSH BLOCK	BENT            	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) PROP SYNCROPHASER TARGET CONTACTED THE SYNCROPHASER MONOPOLE DAMAGING THE MONOPOLE, MONOPOLE BRACKET AND PROP DE-I	CE BRUSH BLOCK BRACKET. THE PROP DE-ICE BRUSH BLOCK BRACKET WAS BENT ENOUGH TO DISPLACE THE PROP DE-ICE BRUSHES ENOUGH T	O SHORT ACROSS DE-ICE SLIP RING CAUSING PARALLEL PROTECTION BREAKERS TO POP.AS YOU CAN SEE WITH THE ILLUSTRATION PROVIDE	D THE WHOLE ASSEMBLY (PROP DEICE BRUSH BLOCK & PROP SYNCROPHASER PICKUP) IS SECURED TO (2) 'A' FLANGE BOLTS. THERE IS A 	SIGNIFICANT DISTANCE (ARM) THAT IS NOT SUPPORTED WHILE TRYING TO MAINTAIN TARGET TO MONOPOLE GAP (0.032 +/- 0.005).		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002032500068	20020325	00068	SW  	2002	3	25	CA020307009      	1	20020226	G	6320	68750121	INSERT          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMPESSOR MOUNT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL LEAKING FROM LOWER STARBOARD COMPRESSOR MOUNT INSERT. ENGINE REMOVED, DISASSEMBLED AND GEARBOX SENT TO ENGINE 	OVERHAUL FACILITY.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002032500069	20020325	00069	SO  	2002	3	25	CA020307010      	2	20020304	G	8540	627307A	CASTING         			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					RT MAG OPENING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE REMOVING COMPONENTS OFF OF THE ACCESORIE CASE, (UN RELATED REPAIR) DISCOVERED VER DEEP PITTING AND CORROSSIO	N AROUND THE RIGHT MAGNETO OPENING.CASTING WAS REPLACED.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002032500070	20020325	00070	SW  	2002	3	25	CA020307011      	1	20020227	G	2520	206031103043	ANGLE           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10942								(CAN) WHILE COMPLETING INTERIOR REPAINTING PROCESS, TWO CRACKS WERE DISCOVERED ALMOST IDENTICAL, ORIGINATING FROM THE JO	INTS BETWEEN EACH OF THE 3 SEAT PANELS. THE CRACKS WERE EACH APPROX. 2 INCHES IN LENGTH ON THE FORWARD SIDE OF THE ANGLE	.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002032500071	20020325	00071	CE  	2002	3	25	CA020307012      	1	20020305	G	3260	21EN96	SWITCH          			MTSBSI	MU2   	MU2B36      	5780412	CE  										MLG	INTERMITTENT    	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN)  DURING APPROACH, CREW SELECTED GEAR DOWN & NOTHING HAPPENED. THEY BROKE OFF APPROACH & FLEW LOCALLY MAKING SEVERA	L ATTEMPTS. EMERGENCY EXTENSION PERFORMED & GEAR LOWERED NORMALLY. INVESTIGATION & SUBSEQUENT GEAR SWINGS COULD FIND NO 	FAULT & ALL FUNCTIONS WERE NORMAL. NOSE DOWNLOCK SWITCH CHANGED OUT FOR NEW SWITCH AS BEING MOST LIKELY CAUSE OF PROBLEM	 ALTHOUGH IT COULD NOT BE CONFIRMED. DOOR OPEN SOLENOID  (ORIG PART WITH 20,007 HRS) ALSO CHANGED AS BEING NEXT MOST PLA	USIBLE SOURCE OF TROUBLE DUE TO COLD WEATHER, ALTHOUGH IT TESTED OK. A/C GEAR SYS LUBRICATED, RIG CHECKED&SWUNG SEVERAL 	TIMES & A/C RELEASED FOR RETURN TO SERVICE.	1	H	7	2 	3T			RT	A10SW   					 
2002032500072	20020325	00072	EA  	2002	3	25	CA020307013      	1	20020307	G	2130	GG670800051	SENSOR          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF34*       	 	NE  					BLEED TEMP	INOPERATIVE     	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CL	CLIMB          	1			CA											(CAN)  IN CLIMB, AT FL310 (GOING TO FL390), FLT CREW NOTICED CABIN PRESSURE OF 7700 FT. BY LOOKING AT ECSP, THEY OBSERVE	D THAT 2 BLEED PRESSURE WERE AT ZERO & THAT BOTH PACKS OUTLINES WERE WHITE. NO MORE PRESSURIZATION & NO MESSAGES WERE PO	STED. FLT CREW CARRIED OUT EMERGENCY DESCENT TO FL100 DURING WHICH CABIN ALTITUDE REACHED 11200 FT (THEY GOT CAS MESSAGE	S CABIN ALT (C) & CABIN ALT (W) DURING DESCENT).  AFTER 2 TENTATIVES OF RESETTNG PACKS, CREW ELECTED TO APPLY QRH ABN 2-	12 "UNPRESSURIZED FLT PROC" & TO CONTINUE FLT TO DESTINATION AT FL100. ON GROUND MECHANICS REPLACED BOTH BLEED TEMPERATU	RE SENSORS.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500073	20020325	00073	SO  	2002	3	25	CA020307015      	2	20020304	G	8550	22355	GEAR            			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					OIL PUMP	BROKEN          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT RETURNED TO BLOCKS AND SHUT ENGINE DOWN AFTER NOTICING THAT THE RPM GAUGE WAS UNSERVICABLE. UPON FURTHER INS	PECTION FOUND THAT THE UPPER OIL PUMP GEAR,  WHICH IS ALSO THE TACHOMETER DRIVE SHAFT. HAD SPLIT. THE PIECE WAS RECOVERE	D. AND THE GEAR / SHAFT WAS REPLACED WITH NEW. THE RESULTING DEFECT MAY HAVE ALSO CAUSED SOME WEAR TO THE BUSHING AND OI	L PUMP HOUSING.			1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002032500074	20020325	00074	EU  	2002	3	25	CA020307016      	1	20020305	G	2913	AE71112112CTD	PUMP            			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					HYD SYSTEM	LOOSE           	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA											(CAN) DURING FINAL APPROACH INTO YVR, ECAM INDICATION OF GREEN SYSTEM RESERVOIR "UNDERFULL" WAS TRIGGERED, CREW CARRIED 	OUT PROCEDURES AS DETAILED ON ECAM WHICH INCLUDED DEPRESSURISING BOTH GREEN SYSTEM ENGINE DRIVEN PUMPS. AS A RESULT ON L	ANDING, AFTER ROLL-OUT A/C HAD TO BE TOWED FROM RUNWAY DUE TO NO NOSE WHEEL STEERING. INSPECTION WAS CARRIED OUT AND FOU	ND NR 1 HYDRAULIC PUMP(GREEN SYSTEM) ON NR 2 ENGINE PRESSURE LINE WAS LEAKING AT THE E.D.H.P DUE TO "B" NUT HAD BACKED O	FF CAUSING A LEAK. "B" NUT WAS TIGHTENED, SYSTEM WAS SERVICED AND LEAK CHECK SERVICEABLE. AIRCRAFT WAS RETURNED TO SERVI	CE.	1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002032500075	20020325	00075	EU  	2002	3	25	CA020308001      	1	20020308	G	2720	102C32016	PULLEY          			GROB  	103CAT	G103TWNASTIR	1660202	EU  										RUDDER PEDAL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PLASTIC PULLEY HAS RADIAL CRACKS COMING FROM THE BEARING, SOME CRACKS EXTEND TO OUTER EDGE.						1	K	0	0 	  			 	G39EU   					 
2002032500076	20020325	00076	NE  	2002	3	25	CA020308002      	2	20020305	G	7314	5008735G	PUMP            			AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     	 	NE  					FUEL SYSTEM	FAILED          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R	W	J	PARTIAL RPM/PWR LOSS      	INADEQUATE Q C            	WARNING INDICATION        	TO	TAKEOFF        	1			CA			24191	24191							(CAN) DURING INITIAL ROLL AT 1.2 EPR THE ECAM MESSAGE "COMP VANE NR 2" APPEARED ON THE UPPER ECAM SCREEN. THE ENGINE EXP	ERIENCED A LIGHT COMPRESSOR STALL. THE TAKE-OFF WAS REJECTED AT 50 KTS AND THE AIRCRAFT RETURNED TO THE GATE WITH BOTH E	NGINES RUNNING. MAINTENANCE OPERATIONS CONTROL DISPATCHED ENGINEERS FROM YYZ. THE HP FUEL PUMP AND FUEL MANAGEMENT UNIT 	WERE REPLACED. A POWER ASSURANCE TEST WAS CARRIED OUT AND NO FAULTS WERE FOUND. THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A28NM   	E311NE				 
2002032500078	20020325	00078	EU  	2002	3	25	CA020308003      	1	20020308	G	2761	30829100	VALVE           			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2A5   	 	NE  					SPOILERS	UNSERVICEABLE   	W				H				DEACTIVATE SYST/CIRCUITS				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) FLT 757, LOST OF BLUE HYDRAULIC SYSTEM FLUID IN FLIGHT. HYDRAULIC LEAK WAS FOUND COMING FROM NR 3 RT SPOILER VALVE	 GROUP AT THE FILTER HOUSING CAP PACKING. AFFECTED SPOILER VALVE GROUP WAS REPLACED AND A/C WAS RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2002032500080	20020325	00080	WP  	2002	3	25	CA020308004      	1	20020308	G	3220	152460101	SLEEVE          			LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					NLG TORQUE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING WALKAROUND FOUND NLG UPPER TORQUE LINK RT DETENT SLEEVE BROKEN IN TWO. REPLACED UPPER TORQUE LINK'S RT SPR	ING, INDEX AND DETENT SLEEVES AND A/C WAS RETURNED TO SERVICE.					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002032500082	20020325	00082	CE  	2002	3	25	CA020308005      	1	20020307	G	2100	2419151133	TUBE            			LEAR  	35    	36LEAR      	5170601	CE  										PRESSURE MODULE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TUBE ASSEMBLY RUNNING FROM AFT PRESSURE BULKHEAD ALONG THE RT SIDE OF CABIN CEILING TO PRESSURE MODULE HAS VARIOUS	 AREAS OF CORROSION AND CHAFING DAMAGE ALONG FULL LENGTH. NEW PART INSTALLED.					2	L	7	2 	4F			 	A10CE   					 
2002042900047	20020429	00047	EA  	2002	4	29	CA020308006      	2	20020224	G	7414	10382588	COIL            	BENDIX      	1068255514  	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO	WRONG PART      	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA						GO1FA068					(CAN) NEW OVERHAUL ENGINE FROM LYCOMING. ENGINE 25 HOURS.  ENGINE VERY ROUGH BACKFIRE, NO POWER.  POINTS DEEPLY PITTED, 	BRUSH ASSEMBLY WORN AT 25 HOURS.  CANADIAN AIRCRAFT COMPONENT CORD STRIP REPORT W/O 2244.   WRONG PART NUMBER COIL FOR T	HIS MAGNETO 10-382588 18 FOR 8 CYLINDERS ENGINE.  PARTS REQUIRED:COIL10-382790 QTY 2 BRUSH 10-160844 QTY 2 CONTACT ASSY1	0-382585 QTY 2			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002041000002	20020410	00002	EU  	2002	4	10	CA020308007      	1	20020225	G	5532	D5537002600800	PANEL           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERTICAL STAB LEADING EDGE PANEL 322AL AND 322BL CRACKED. PANEL 322AL APPEARS CRACKED ON BOTH LT AND RT SIDES APRO	X 4 INCHES BELOW UPPER EDGE. ALSO APPROX. 4 INCHES UP FROM LOWER EDGE ON LT SIDE APPEARS TO BE A THIRD CRACK. 322BL APPE	ARS TOBE DELAMINATED ON RT SIDE APPROX. 4 INCHES DOWN FROM UPPER EDGE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002041000003	20020410	00003	NM  	2002	4	10	CA020308008      	1	20020225	G	5532	D5537002600800	PANEL           			AIRBUS	A319  	A319114     	3930350	NM  										VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERTICAL STAB LEADING EDGE PANELS 322BL CRACKED. PANEL 322BL CRACKED.						2	L	7	2 	4F			RT	A28NM   					 
2002050700108	20020507	00108	NE  	2002	5	7	CA020308009      	2	20020217	G	7200		ENGINE          	GE          	CFM565A1    	AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  	 		            		ENGINE	FAULTY          	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA		 				731697					(CAN) BIRD INGESTION/STRIKE ON #2 ENGINE AT TOUCHDOWN.NORMAL REVERSE USED. NO ABNORMAL ENGINE INDICATIONS IN COCKPIT. BI	RD STRIKE INSPECTION CARRIED OUT NIL FAULTS FOUND.ENGINE RUN COMPLETE NIL FAULTS FOUND. THRUST REVERSER OPERATION CHECK 	COMPLETED NIL FAULTS FOUND. AIRCRAFT CONSIDERED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002041000005	20020410	00005	EA  	2002	4	10	CA020308011      	1	20020222	G	2133	601R386493	ROD             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					OUTFLOW VALVE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT NOT PRESSURIZING ON CLIMB OUT. FLIGHT DIVERTED WITH OVERWEIGHT LANDING. FOUND MAIN PASSENGER DOOR PRESSUR	E VALVE PUSHROD BROKEN. PUSHROD REPLACED AND RIGGED. PRESSURIZATION CHECK AND OVERWEIGHT LANDING CHECK CARRIED OUT AS PE	R AMM 05-51-01.NO FAULTS FOUND.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002032500085	20020325	00085	NM  	2002	3	25	CA020308013      	1	20020228	G	7931		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LEFT	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) START OF THE DAY. NR 1 OIL PRESSURE WOULD GO TO 70PSI. THEN SPIKED TO 90PSI. ALL GROUND TEST SYSTEM NORMAL. ON TAK	EOFF ROLL AT V1 NR 1 ENGINE OIL PRESSURE LIGHT CAME ON INTERMITTENTLY AS OIL DROPPED TO 40PSI AT LEAST 3 TIMES OIL PRESS	URE THEN RESUMED NORMAL OPERATION. AIRCRAFT FLOWN BACK TO OTTAWA, THE OIL FILTERS, AND SCAVENGE FILTER CHECKED NO METAL 	FOUND. TALKING WITH ENGINE MANUFACTURER THEY ADVISE TO REPLACE THE PRESSURE REGULATING VALVE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002041000006	20020410	00006	CE  	2002	4	10	CA020308014      	1	20020306	G	5620	010A31870	WINDOW          			MTSBSI	MU2   	MU2B60      	5780460	CE  										FUSELAGE	MISSING         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) A/C LEVELED OFF AT 20,000 FT,  LOUD BANG HEARD FOLLOWED BY IMMEDIATE DE-PRESSURIZATION. A/C WENT TO 6000 FT AND LA	NDED IN THUNDER BAY. FOUND 1ST WINDOW ON LEFT SIDE PARTIALLY GONE AND 2ND WINDOW ON LT SIDE COMPLETLY GONE.					1	H	7	2 	3T			RT	A10SW   					 
2002042900053	20020429	00053	SW  	2002	4	29	CA020311003      	1	20020306	G	2497		WIRE            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	MAIN BUSS FEEDER	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION THE MAIN BUSS FEEDER WIRE BETWEEN THE MAIN 120 AMP CIRCUIT BREAKER AND THE COCKPIT BUSS B	AR WAS TIE STRAPPED TO THE RT UPPER ENGINE MOUNT TUBE AND WAS CHAFING ON THE 2 BOLT HEADS THAT SECURE THE RT FORWARD FOA	M TANK SUPPORT CLAMP. THE WIRE WAS INSPECTED AND FOUND SERVICEABLE. A STANDOFF GROMMET WAS INSTALLED TO ENSURE ADEQUATE 	CLEARANCE BETWEEN THE ENGINE MOUNT TUBE AND THE HARNESS.			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2002041000007	20020410	00007	EA  	2002	4	10	CA020311004      	1	20020311	G	2120		DUCT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ACM	DAMAGED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN FLT A/C DEPRESSURIZED AT FL 300. CABIN ALTITUDE CLIMBED TO 14,000 FEET. EICAS MESSAGE AUTO PRESS 2 FAIL(S) POST	ED. A/C LANDED UNEVENTFULLY. A/C THEN FERRY LYS FOR TROUBLESHOOTING. MDC INDICATON SHOWED CABIN PRESS CONTOLLER NR 2 AT 	FAULT. CPC 2 REPLACED & SYS TESTED SERVICEABLE. DURING FLT, A/C EXPERIENCED PRESSURIZATION PROBLEMS AGAIN. AT 1500 FT, C	ABIN ALTITUDE AT 5,800 FEET. A/C DID AIR TURNBACK. 2 OUTFLOW VALVES & THE CABIN PRESSURE CONTROL PANEL (CPCP) WERE REPLA	CED & SYS TESTED GOOD PENDING TEST FLT. DURING TEST FLT (WHICH ALSO A/C POSING), PRESSURIZATION PROBLEM REAPPEARED. A/C 	RETURNED. TROUBLESHOOTING REVEALED DAMAGED RT ACM SUPPLY DUCT.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041000009	20020410	00009	EA  	2002	4	10	CA020312001      	1	20020312	G	3213	901230602	FITTING         		4930        	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					STRUT ATTACHMENT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						TB472					(CAN) RIGHT FLOAT WAS REMOVED FROM AIRCRAFT FOR REPAIRS TO BOTTOM SKIN. UPON REMOVAL, THE FRONT STRUT ATTACH FITTING WAS	 FOUND CRACKED AT HOLE FOR TAPER PIN. PART IS BEING REPLACED WITH NEW.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002032500086	20020325	00086	EA  	2002	3	25	CA020312002      	2	20020301	G	8520	AEL18840	CAMSHAFT        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) METAL FOUND IN OIL FILTER DURING SCHEDULED MAINTENANCE. ENGINE DISMANTLED AT OVERHAUL FACILITY. NR 4 EXHAUST LOBE 	FOUND TO BE WEARING AFTER 85.2 HOURS SINCE NEW.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002032500087	20020325	00087	EU  	2002	3	25	CA020312003      	1	20020222	G	5412		SKIN            			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					FIREWALL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) - FIREWALL ASSEMBLY AFT LT.- STA 5896, WL 2830, BL 430 AND WL 2740, BL570.- FIREWALL IS MADE OF 0.016" TITANIUM TH	ROUGH WHICH BOTH THE FIRE EXTINGUISHER AND AIR CONDITIONER TUBING ASSEMBLY FITTINGS PASS. - CRACKS FORM AROUND FITTING H	OLES IN TITANIUM. - SUSPECT CRACKS FORM DUE TO EXTREME VIBRATION AS HELICOPTER PASSES THRU TRANSLATIONAL LIFT. FITTINGS 	ARE RIGID - FIREWALL VIBRATES.			1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2002041000010	20020410	00010	EU  	2002	4	10	CA020312004      	2	20020306	G	8570	2072000002	LINE            			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ENG COOLING	LEAKING         	W				B				EMER. DESCENT           				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) SMELL OF ANTI-FREEZE IN COCKPIT.  INVESTIGTION REVEALED THAT COOLANT PIPE HAD MOVED AND RUBBED ON HEAT SHROUD, CAU	SING SMALL HOLE ALLOWING ANTI-FREEZE TO LEAK OUT.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002041000011	20020410	00011	SO  	2002	4	10	CA020312005      	1	20020304	G	2497	761488	WIRE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					COCKPIT	BURNED          	W				H	E			DEACTIVATE SYST/CIRCUITS	ENGINE SHUTDOWN         			B	B		SMOKE/FUMES/ODORS/SPARKS  	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE THIS A/C WAS TAXIING OUT PILOT NOTICED A BURNING SMELL & THEN SMOKE IN VICINITY OF BREAKER PANEL ON LEFT SID	E OF COCKPIT. SHUT OFF MASTER SWITCH, SHUTDOWN ENGINES & EVACUATED A/C. ON INVESTIGATION FOUND THAT A 20 GAUGE WIRE WAS 	BURNED ABOUT 1.5 FT IN VICINITY OF BREAKER PANEL. IT ALSO BURNED ABOUT 4 OTHER WIRES IN THIS VICINITY AS  WELL. WIRE THA	T INITIATED PROBLEM WAS A POWER WIRE THAT OPERATES FASTEN SEAT BELT & NO SMOKING LIGHTS. IT WAS VERY HARD TO DETERMINE W	HAT IT HAD SHORTED ON.  ALL WIRES WERE REPLACED & PROTECTIVE SHIELDING WAS INSTALLED. BREAKERS FOR THIS SYS ALSO REPLACE	D.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002032500088	20020325	00088	EU  	2002	3	25	CA020312006      	1	20020222	G	7920		ENGINE          			AMD   	FALC20	FALCON200   	2730150	EU  	GARRTT	ATF3  	ATF36A4     	29002	WP  					LEFT	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	K	J	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) THE CREW HAD SMOKE IN THE COCKPIT. THEY NOTICED THAT THE LT ENGINE OIL PRESSURE HAD DROPPED. THEY TURNED OFF THE L	T BLEED VALVE WHICH CLEARED THE SMOKE THEN THEY SHUT DOWN THE ENGINE AFTER THEY LANDED. I FOUND A LARGE AMOUNT OF OIL ON	 THE ENGINE'S TAIL CONE. THE OIL WAS COMING FROM THE NR 4 AND 5 SUMP VENT TUBE. THIS ENGINE HAS HAD THE NR 4 AND 5 CARBO	N SEALS REPLACED TWICE IN THE LAST YEAR DUE TO OIL LEAKING ON THE VENT TUBE AND HAVING HIGH SUMP PRESSURES.			2	L	7	2 	4F	4	F	RT	A7EU    	E7WE				 
2002050300011	20020503	00011	SW  	2002	5	3	CA020312007      	1	20020305	G	2821		CASE            	MICHDYNAMICS	2223666213  	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL FILTER	RUPTURED        	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA						4570					(CAN) - AFTER START,  FUEL FILTER CLOG LIGHT CAME ON.   AIRCRAFT SHUT DOWN AND FOUND FUEL LEAK FROM FILTER HEAD & FOUND 	BROKEN CASTING.  INVESTIGATION FOUND THAT AN INPROPER FUEL VALVE ASSY WAS INSTALLED. THE ASSY DID NOT ALLOW THE SYSTEM T	O BLEED OFF IN THE EVENT OF PRESSURE BUILD UP DUE TO EXPANSION OF THE FUEL IN THE SYSTEM WHEN THE AIRCRAFT FUEL VALVE IS	 IN THE "OFF" POSITION.   FUEL EXPANDED WITH THE AIRCRAFT PARKED OUTSIDE, COVERS ON THE ENGINE COWL & CAR HEATER INSTALL	ED OVERNIGHT.   A PROPER FUEL VALVE ASSEMBLY WAS INSTALLED AS PER THE TYPE REQIRED FOR THE "S/N" OF AIRCRAFT.   THE FUEL	 VALVE ASSY INSTALLED HAS A PRESSURE RELIEF VALVE INSTALLED, THE OLD ONE DID NOT.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002032500090	20020325	00090	EA  	2002	3	25	CA020312008      	2	20020305	G	8520	LW13282	CRANKCASE       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DEFECT OBSERVED DURING ROUTINE MAINTENANCE. OIL LEAKING FROM CRANKCASE LT HALF NEAR CENTRE BOLTS THAT SECURE CASES	 TOGETHER. FURTHER INSPECTION REVEALED A PIN HOLE THAT APPEARS TO ORIGINATE FROM WITHIN/INTERNAL TO THE CRANKCASE. ENGIN	E REMOVED SENT TO APPROVED OVERHAUL STATION FOR INSPECTION AND POSSIBLE REPAIR.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002032500091	20020325	00091	NE  	2002	3	25	CA020312009      	2	20020219	G	7230	310061601	BEARING         								PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE OPERATOR REMOVED THE ENGINE FROM THE AIRCRAFT WHEN HE FOUND EXTENSIVE METAL CONTAMINATION OF THE OIL PRESSURE 	FILTER. AFTER PERFORMING AN OIL FLUSH, RUN & RECHECK AS SUGGESTED BY THE MAINTENANCE MANUAL. THE ENGINE WAS REMOVED AND 	SHIPPED TO ATI FOR INVESTIGATION AND CORRECTION.THE CAUSE OF THE METAL CONTAMINATION WAS FOUND TO BE A DAMAGED NR 1 BEAR	ING.   THE CAUSE OF THE BEARING FAILURE WAS NOT ABLE TO BE DETERMINED.								4	F			E25EA				 
2002041000012	20020410	00012	NM  	2002	4	10	CA020312010      	1	20020312	G	2750	734382D	TORQUE TUBE     			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	TE FLAPS	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			28095	28095							(CAN) DURING SHEDULED INSPECTION OF THE FLAP PRIMARY TORQUE TUBE DRIVES.IPC REFERENCE 27-51-00 FIG 5 ITEM 180 , FAULTY T	UBE FOUND ON RT WING , 2ND TUBE IN FROM WING TIP ,INBORAD END OF TUBE END HAD RIVET HOLES DRASTICALLY ELONGATED . TORGE 	TUBE SCHEDULED TO BE REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002032500092	20020325	00092	EU  	2002	3	25	CA020313002      	1	20020222	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TAIL ROTOR	WILL NOT BALANCE	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN)   THE TAIL ROTOR HAS HAD A PROBLEM OF GOING OUT OF BALANCE. THE FIRST TIME IT WENT OUT OF BALANCE HAD TO REMOVE WE	IGHT FROM ONE OF THE TIPS OF THE BLADE. THE SECOND TIME HAD TO ADD WEIGHT TO THE BLADE OUT OF BALANCE. THE THIRD TIME TH	E T/R WENT OUT OF BALANCE HAD TO ADD MAXIMUM WEIGHT TO THE BLADE TIP. REPLACED TAIL ROTOR BLADE ASSEMBLY.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002041000013	20020410	00013	CE  	2002	4	10	CA020313003      	1	20020302	G	2910	HYC5005	BRUSHES         			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  					HYD MOTOR	WORN            	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			CA											(CAN) LANDING GEAR HYDRAULIC POWER PACK MOTOR DID NOT RUN. AIRCRAFT PUT ON JACKS & GEAR SELECTED UP, WITH A LIGHT TAP ON	 MOTOR GEAR RETRACTED NORMALLY WITHIN ALLOWABLE TIME LIMITS. SAME PROBLEM OCCURRED WHEN GEAR SELECTED BACK DOWN. INVESTI	GATION REVEALED BRUSHES WERE BADLY WORN AND COMMUTATOR DAMAGED. BRUSHES ARE INSPECTED PERIODICALLY BUT IT IS NOT A REQUI	REMENT TO INSPECT I.A.W. BEECH 76 MAINTENANCE SCHEDULED. WE SUGGEST THAT FIELD WIRES ARE BREAKING DOWN IN MOTOR CAUSING 	UNUSUALLY SHORT LIFE OF BRUSHES, MOTOR AND POWER PACK ASSEMBLY REPLACED. AIRCRAFT TESTED SERVICEABLE. BRUSHES SHOULD BE 	INSPECTED NO LESS THAN 500 HOURS.	1	L	7	2 	3O	3	O	 	A29CE   	E286				 
2002041000014	20020410	00014	CE  	2002	4	10	CA020313004      	1	20020308	G	2997	S31064	DIODE           			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					HYD VALVE	MISSING         	W				O				OTHER                   				W	J		INADEQUATE Q C            	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) HYDRAULIC POWER STAYED ON WHEN GEAR WAS SELECTED DOWN. FOUND WHEN CESSNA HAD INSTALLED SB 550-32-40 REV.3. THEY DI	D NOT INSTALL DIODE CAUSING POWER FEEDBACK AND HYDRAULIC CENTRE VALVE STAYING CLOSED.					1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2002032500093	20020325	00093	EA  	2002	3	25	CA020313005      	2	20020305	G	8520	LW12201	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE ROCKER VALVES INSPECTION,  NR 4 CYLINDER INTAKE VALVE LIFT WAS FOUND VERY LOW. THE CYLINDER WAS REMO	VED AND CAMSHAFT INTAKE VALVE LOBE WAS FOUND WORN. THE ENGINE WAS REMOVED FROM THE AIRCRAFT AND SENT FOR REPAIR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002032500094	20020325	00094	NE  	2002	3	25	CA020313006      	2	20020311	G	7314		SHAFT           			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					FUEL PUMP	STRIPPED        	W				E				ENGINE SHUTDOWN         				X	Y		ENGINE FLAMEOUT           	ENGINE STOPPAGE           		DE	DESCENT        	1			CA											(CAN) FCU AND FUEL PUMP WAS REMOVED FROM ENGINE. FUEL PUMP TO ENGINE SHAFT WAS FOUND STRIPPED, RESULTING IN FUEL STARVAT	ION.					1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2002041000015	20020410	00015	CE  	2002	4	10	CA020314001      	1	20020312	G	2917	MS28893C6	PRESSURE SWITCH 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					HYD PUMP	STICKS          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THE HYDRAULIC PUMP CYCLED ON FOR AN ABNORMAL LENGTH OF TIME WITH THE GEAR SELECTED TO THE UP POSITIO	N. THE LANDING GEAR WAS SELECTED TO DOWN AND THE CIRCUIT BREAKER POPPED. THE CREW CARRIED OUT THE LANDING GEAR EMERGENCY	 EXTENSION PROCEDURE AND 3 GREEN, DOWN AND LOCKED WAS INDICATED. MAINTENANCE PLACED THE AIRCRAFT ON JACKS AND DETERMINED	 THAT THE PRESSURE RELIEF VALVE WAS NOT CYCLING AT THE CORRECT TIME ONCE PRESSURE HAD BUILT TO THE PRESCRIBED SETTING. T	HEREFORE THE HYDRAULIC PUMP WOULD CONTINUE TO RUN FOR LONGER THAN NORMAL. THE PRESSURE RELIEF VALVE / SWITCH WAS REPLACE	D AND THE LANDING GEAR FUNCTION CHECKS COMPLETED.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002032500096	20020325	00096	EU  	2002	3	25	CA020314002      	1	20020312	G	3222	AN427	BOLT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG LINK	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT WAS DELIVERED WITH S/B 32-006 COMPLIED WITH THEREBY NOT REQUIRING INSPECTION EVERY 100HRS OF THE MLG TRAI	LING LINK BOLTS THE SUBJECT AIRCRAFT HAD THE TRAILING LINK SAFETY BOLTS REMOVED FOR OTHER ACESS AND THEY WERE FOUND TO B	E BADLY CORRODED AND GOUGED AND WORN.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002041000016	20020410	00016	EU  	2002	4	10	CA020315001      	1	20020217	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD PUMP	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN PERFORMING A 100 HOUR INSPECTION ON AIRCRAFT. IT WAS NOTICED THAT THIS HYDRAULIC BELT WAS SPLITTING OR FRAYIN	G AT ITS SEAM.THIS BELT WAS FOUND TO BE INSTALLED CORRECT AS PER EUROCOPTER MAINTENANCE MANUALS.WE INSTALLED A NEW BELT 	AS THIS ONE WOULD HAVE SPLIT IN TWO AFTER A FEW HOURS OF OPERATION.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002041000017	20020410	00017	EA  	2002	4	10	CA020315002      	1	20020312	G	5610	601R3303314	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) RT WINDSHIELD CENTRE PLY CRACKED DURING CLIMB.  THE WINDSHIELD INSTALLED WAS A POST SERVICE BULLETIN WINDSHIELD.  	RT WINDSHIELD HAS BEEN REPLACED AND AIRCRFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041000019	20020410	00019	EU  	2002	4	10	CA020315005      	1	20020304	G	2910	AE7088224	LINE            			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) AFTER TAKEOFF, DURING FLAP RETACTION ECAM MSG HYDRAULIC BLUE ENGINE PUMP PRESSURE LOW CAME ON INTERMITTENTLY. AIRC	RAFT RETURNED TO VANCOUVER. FOUND NR 2 ENGINE RETURN LINE LEAKING FROM A CRACK ELBOW. LINE REPLACED AND LEAK CHECKED OK.	 ALL FILTERS AND ENGINE GROUND RUN.				2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2002041000020	20020410	00020	NM  	2002	4	10	CA020315006      	1	20020129	G	5753	657094728	PANEL           			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RT WING TE FLAPS	SHEARED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) PRIOR TO DEPARTURE, FLAPS EXTENDED FOR SREVICE CHECK INSPECTION. UPON RETRACTION RT CLOSURE PANEL AT INBOARD FLAPS	 HUNG UP AT 10 UNITS.FOUND RT  INBOARD CLOSURE PANEL SHEARED CAUSING FLAPS TO JAM. CLOSURE PANEL REMOVED. AIRCRAFT OPERA	TED PER CDL 57-52-01. AIRCRAFT FERRIED FOR SCRAPPING PROCESS. OPERATIONAL LIFE ENDED AT DESTINATION.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002041000021	20020410	00021	NE  	2002	4	10	CA020315007      	2	20020306	G	7230	1442M66G06	TUBE            			BOEING	747   	747475      	       	NM  	GE    	CF6   	CF680C2B2   	30025	NE  					TURBINE COOLING	CRACKED         	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMB, EICAS ENGINE OVERHEAT NR 2 NAC. FLIGHT CREW FOLLOWED THE CHECK LIST, BLEED OFF, MESSAGE REMAINED. REDUCE	D THRUST TO APPROX 75 PERCENT POWER, MESSAGE DISAPPEARED.  AIRCRAFT RETURNED TO HAWAII.  FOUND CRACK AT UPPER BEND OF NR	 2 HP TURBINE COOLING TUBE. NO PARTS AVAILABLE. TUBING WELDED AS PER RPODUCTION PERMIT. TUBING TO BE INSPECTED PRIOR EAC	H FLIGHT UNTIL REPLACED. ENGINE GROUND RUN CARRIED OUT, ALL INDICATIONS NORMAL AND NO LEAK FOUND. AIRCRAFT SERVICEABLE.			2	L	7	4 	4F	4	F	RT	A20WE   	E13NE				 
2002041000023	20020410	00023	NE  	2002	4	10	CA020315009      	2	20020311	G	7200	6558135	B-NUT           			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 1 ENGINE	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) NR 1 ENGINE EPR READ HIGHER THAN NR 2 ENGINE AT TAKEOFF POWER. AIRCRAFT RETURNED TO MAINTENANCE BASE. NR 1 ENGINE 	INSPECTED AND PT7BD BLEED AIR LINE FOUND LOOSE. LINE TIGHTENED AND TAKEOFF POWER RUN ACCOMPLISHED. ALL PARAMETERS CHECKE	D NORMAL FOR TYPE. AIRCRAFT RELEASED FOR RETURN TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002041000024	20020410	00024	EU  	2002	4	10	CA020315011      	1	20020314	G	3310	308135	BALLAST         			AIRBUS	310   	A310300     	3930305	EU  										CABIN	FAILED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) ON PUSH BACK THE FLIGHT ATTENDANT NOTICED A STRONG ELECTRICAL BURNING SMELL , NO SMOKE , IN THE FORWARD CABIN LT S	IDE . THE AIRCRAFT RETURNED TO THE GATE FOR INVESTIGATION . THE FORWARD CABIN CEILING AREA WAS INSPECTED FOR SIGNS OF A 	BURNED WIRE OR DISCOLORED EQUIPMENT. MAINTENANCE FOUND THE LT FORWARD CEILING LIGHT BALLASTS   SLIGHTLY DISCOLORED. THE 	BALLAST WAS REPLACED IN ACCORDANCE WITH MM AND ALL ELECTRICAL SYSTEM CHECKED WHILE CEILING OPEN , NO MORE ODORS OR ANY S	IGNS OF BURNING. THE BALLASTS WERE RETURNED TO YMX FOR INVESTIGATION.		2	L	7	2 	4F			RT	A35EU   					 
2002041000026	20020410	00026	EA  	2002	4	10	CA020318001      	1	20020315	G	5711	21510032242	SPAR            			CNDAIR	CL215 	CL2151A10   	1900320	EA  										RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED RIGHT REAR LOWER SPAR CAP BEING REPLACED IN ACCORDANCE WITH CF92-26. FURTHER CRACKING DISCOVERED IN WING S	PAR WEB AT RBL 50 DURING REPAIRS. THIS AREA IS OUTSIDE OF THE INSPECTION REQUIREMENTS OF THE AIRWORTHINESS DIRECTIVE.					2	H	7	2 	4R			RT	A14EA   					 
2002041000027	20020410	00027	EA  	2002	4	10	CA020318002      	1	20020318	G	5720	2153003156	ANGLE           			CNDAIR	CL215 	CL2151A10   	1900320	EA  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON THE LEFT HAND SIDE OF THE FUSELAGE, THE DRAG ANGLE THAT JOINS THE FUSELAGE AND WING AT WS 51 WAS FOUND CRACKED 	DURING THE NORMAL "B" CHECK.THE CRACK IS APPROXIMATLEY ONE INCH(1")LONG FROM THEFRONT FACE TOWARDS THE REAR OF THE ANGLE	 IN THE BEND RADIUS.* LANDING CYCLES=2451 * BOMB CYCLES=15247				2	H	7	2 	4R			RT	A14EA   					 
2002041000028	20020410	00028	WP  	2002	4	10	CA020318003      	2	20020307	G	7321	UN	SPRING          								GARRTT	TPE331	TFE33112UHR 	 	WP  					FUEL CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN REMOVAL OF THE REAR COVER TO ALLOW RE INDEXING OF THE FLIGHT IDLE FUEL FLOW IT WAS NOTED THE COIL SPRING HAD 	COME IN CONTACT WITH THE REAR COVER. THE RESULTING FRICTION HAD WORN THE COILS OF THE SPRING 50 PERCENT THROUGH. THE FCU	 WAS REMOVED AND SENT FOR REPAIR.									4	T			E4WE				 
2002041000029	20020410	00029	NE  	2002	4	10	CA020318004      	2	20020311	G	7250	3022312	TURBINE WHEEL   			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 2 ENGINE	DAMAGED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING HELI-SKI OPRATIONS UNUSUAL, INTERMITTENT VIBRATION FELT BY PILOT & NOTICED TO BE INCREASING WITH TIME. ON-S	ITE ENGINEER BEGAN TROUBLESHOOTING PROCESS BY REMOVING & INSPECTING ENGINE OIL COOLER BLOWER FANS. ON INSTATI ON NR 2 PO	WER SECTION COULD NOT BE ROTATED BY HAND TO ALIGN BLOWER. AS IS NOT NORMAL FOR PT6 TWIN PAC A/C GROUNDED & POWER SECTION	 REPL COMPLETE WITH AFCU, MFCU, FUEL PUMP&BLEED VALVE. GROUND RUN AND TEST FLT INDICATED NORMAL VIBRATION LEVEL&A/C FLOW	N TO HOME BASE IN KELOWNA. SHORTLY BEFORE LDG WITH INCREASED POWER SETTINGS VIBRATION RETURNED TO IT'S PREVIOUS LEVEL.		1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002041000030	20020410	00030	WP  	2002	4	10	CA020318005      	2	20020312	G	7321		FUEL CONTROL    								GARRTT	TPE331	TFE33112UHR 	 	WP  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA											(CAN) FUEL FLOW FROM FLIGHT IDLE TO GROUND IDLE TRANSITION WAS ERRATIC CAUSING AIRCRAFT TO PULL ERRATICALLY ON LANDING. 	REPLACING THE FCU CORRECTED THE PROBLEM. PREVIOUSLY THERE HAD BEEN MANY ATTEMPTS TO ADJUST THE FCU WITH NO SUCCESS.										4	T			E4WE				 
2002041000031	20020410	00031	CE  	2002	4	10	CA020318006      	1	20020301	G	3243		SHUTTLE VALVE   			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					BRAKE SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WHEN THE AIRCRAFT WAS PARKED FOR AN EXTENDED PERIOD IN MINUS 20-DEGREE WEATHER WITH THE PARKING BRAKES ON, A PUDDL	E OF HYDRAULIC OIL WAS NOTICED UNDER AFT FUSELAGE. INVESTIGATION FOUND THE BRAKE SHUTTLE VALVE ASSY. WAS LEAKING, WHICH 	WAS THEN REPLACED.				2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2002041000032	20020410	00032		2002	4	10	CA020318007      	4	20020308	G	3418		COMPUTER        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					STALL WARNING	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB AFTER TAKEOFF CREW WAS UNABLE TO SELECT AUTOPILOT. INVESTIGATION FOUND RT STICK SHAKER REGISTER GROUN	DED ON NR 2 INTEGRATED COMPUTER.  REPLACED STALL WARNING COMPUTER.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2002041000033	20020410	00033	WP  	2002	4	10	CA020319001      	2	20020308	G	7260	358348	BEARING         								GARRTT	TPE331	TPE33110UA  	01514	WP  					GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SOAP SAMPLE SENT TO WINSOAP INDICATED INSPECT ENGINE IMMEDIATELY. INSPECTION OF GEAR BOX INDICATED BEARING ON PG D	RIVE GEAR WAS FAILING AND MAKING METAL.										4	T			E4WE				 
2002041000062	20020410	00062	GL  	2002	4	10	CA020319003      	2	20020320	G	7230	6890550	COMPRESSOR      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			CA			12288								(CAN) ON THE 3RD START OF THE DAY THE PILOT COULD NOT MOTOR THE ENGINE TO START THE AIRCRAFT. PULLED THE STARTER AND TRI	ED TO TURN N1 GEARTRAIN AND WAS UNABLE TO TURN. TRIED TO TURN THE COMPRESSOR THRU THE BYPASS DOOR BY HAND AND WAS UNABLE	 TO TURN. REMOVED THE ENGINE FROM THE AIRFRAME. TOOK THE COMPRESSOR OF THE GEARBOX AND WAS STILL UNABLE TO TURN THE COMP	RESSOR. NO DAMAGE TO THE FIRST STAGES WAS FOUND ON THE COMPRESSOR. SUSPECTED THAT THE IMPELLAR CLEARANCES ARE TO TIGHT A	ND HAVE CONTACTED. COMPRESSOR OUT FOR EVALUATION.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002041000065	20020410	00065	NM  	2002	4	10	CA020319004      	1	20020317	G	7500	655386511	DUCT            			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 1 ENGINE	MISSING         	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER DEPARTING, FLIGHT CREW RECEIVED A NR 1 ENGINE OVERHEAT INDICATION AND IMMEDIATELY RETURNED TO BASE -	 AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTION REVEALED THE CLAMP FOR THE 8TH STAGE ANTI ICE VALVE WAS MISSIN	G AND THE BLEED DUCT FROM THE ENGINE CORE WAS BENT OUTWARD BLOWING UNREGULATED HOT BLEED AIR INTO THE COWLING CAUSING AN	 OVERHEAT CONDITION. MAINTENANCE REPLACED THE COWLING ANTI ICE DUCT, AND ATTACHED CLAMP, GROUND RUNS WERE COMPLETED WITH	 NO FAULTS FOUND - AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002041000066	20020410	00066	GL  	2002	4	10	CA020320004      	2	20020108	G	7210	23035178	GEARBOX         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	SEIZED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING START N1 WAS LOST AT 55 PERCENT N1 TROUBLESHOOTING FOUND N1 TACH DRIVE SEIZED. INSPECTION OF GEARBOX BY STA	NDARD AERO REVEALED OIL PUMP SEIZED. ENGINE HAD JUST BEEN REINSTALLED AFTER REPAIRS TO OIL PUMP IN GEARBOX. ENGINE HAD B	EEN RUN ON TEST STAND BEFORE FAILURE AFTER INSTALLATION IN AIRCRAFT. TIME SINCE REPAIR - 00.0				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002041000068	20020410	00068	GL  	2002	4	10	CA020321001      	2	20020212	G	7220	NAS697A3	ENGINE          			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE BAY	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UNUSUAL SOUND HEARD FROM THE A/C ON COOL DOWN COMING FROM THE ENGINE INLET AREA. UPON FURTHER INVESTIGATION THE CO	MPRESSOR HAD FOD. A NUTPLATE ON THE FORWARD SIDE OF THE PARTICLE SEPERATOR, THAT FASTEN THE FOWARD INLET COWLS ON, HAD S	PLIT AND HALF OF THE NUT PLATE WENT THRU THE PARTICLE SEPERATOR AND WAS INGESTED BY THE ENGINE. THE NUT PLATE MADE IT TH	RU THRU THE ENTIRE ENGINE.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002041700081	20020417	00081	NM  	2002	4	17	CA020321002      	1	20020315	G	2131		CONTROLLER      			BOEING	737   	7372E3      	       	NM  	PWA   	JT8   	JT8D15      	52051	NE  					CABIN PRESSURE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				L			NO TEST                   			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF WHILE CLIMING THROUGH 31,000 FT, CREW NOTICED THAT CABIN ALTITUDE READING 9,500 FT. A/C DESC	ENTED TO 14,000 FT. CREW DONNED OXYGEN MASKS, AS PER QRC FOR RAPID DEPRESSURIZATION & PROCEEDED TO SELECT MANUAL CONTROL	 ON PRESUURIZATION PANEL & OUTFLOW VALVE TO CLOSE. CABIN ALTITUDE IND READ BELOW SEA LEVEL & PRESSURE DIFFERENTIAL WENT 	TO 8.4 PSI CAUSING DISCOMFORT ON EARS FOR EVERYONE. A/C WAS CLEARED TO 10,000 FT. & UNSCHEDULED PRESSURIZATION CHECKLIST	 COMPLETED TO REDUCE CABIN PRESSURE: FLT RETURNED UNPRESSURIZED & LANDED W/O INCIDENT. MAINT PERFORMED OPAL TEST OF PRES	SURE CONTROL SYS AS PER MM 21-31-00 WITH NO FAULTS FOUND.	2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2002041000126	20020410	00126	NM  	2002	4	10	CA020321003      	1	20020321	G	5751	85740004003	STIFFENER       			DHAV  	DHC8  	DHC8*       	       	NM  										AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THREE SKIN STIFFENERS LOCATED AT STA Y485.000 P/N 85740036-102, STA 447.00, P/N 85740030-102 AND AT STA 419.00, P/	N 85740024-102 WERE FOUND TO BE CRACKED ON AFT MOST RIVET HOLE. N.B. PHOTOS ATTACHED. PART CYCLES, TSN, TSO ARE ALL UNKN	OWN.				2	H	7	2 	4T			RT	A13NM   					 
2002041000127	20020410	00127	EU  	2002	4	10	CA020321004      	1	20020319	G	6720	60102RS1MT33CA	BEARING         			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					T/R SPYDER	ROUGH           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN AIRCRAFT SHUTDOWN AFTER LANDING, A ODD CLICKING NOISE WAS HEARD COMINGFROM TAIL ROTOR AREA.INVESTIGATION UPON	 DISASSEMBLY FOUND TAIL ROTOR SWASHPLATE BEARING ROUGH.  REPLACED ASSEMBLY.					1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2002050300012	20020503	00012	EU  	2002	5	3	CA020322002      	1	20020306	G	6720	1053176201	SLEEVE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					T/R PITCH CHANGE	ROUGH           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE TO REPLACE RUDDER BELLOWS BETWEEN SUBJECT SLIDING SLEEVE WAS FOUND TO BE VOID OF GREASE AND THE	 DUPLEX BEARINGS WERE DRY AND "RATTLING" WHEN SPAN. BASE MAINTENANCE STAFF WERE UNAWARE OF THE PRESENCE OF A NEEDLE POIN	T GREASE FITTING ON THE SLEEVE TO FACILITATE LUBRICATION. STAFF INFORMED ME THEY WERE INSTRUCTED BY THE LAST PERMANENT S	UPERVISOR ON PROCEDURES FOR INSPECTION, CLEANING AND LUBRICATING SPLINES BUT WERE UNAWARE OF REQUIREMENTS TO LUBE BEARIN	GS. (C.A.M.P. CODE 672046 LUBE T/R SLIDING SLEEVE OPS 2,3,4.)		1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002041000128	20020410	00128	EU  	2002	4	10	CA020322003      	2	20020304	G	7260	IPC726120	CAGE            			BOEING	727   	727100      	1384036	NM  	RROYCE	TAY   	TAY65154    	 	EU  					SHAFT BEARING	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE NR 3 CSD/GEN TRIPPED, FOLLOWED BY LOW ENGINE OIL PRESSURE WHICH RESULTED IN AN IFSD DUE TO LACK OF OIL AND PRE	SSURE. GROUND MAINTENANCE ADDED 6 LITERS/QTS OF OIL TO THE ENGINE AND TOPPED OFF THE CSD. THERE WERE NO REPORTED NOR ANY	 SIGNS OF EXTERNAL LEAKAGE. ON LOW POWER ENGINE RUN, CSD OIL LEVEL DROPPED. DEBRIS FOUND ON CHIP DETECTORS AND EXCESSIVE	 OIL IN G/BOX. INITIAL EXAMINATION PRIOR TO STRIP FOUND THAT THE GENERATOR SPUR GEARSHAFT REAR ROLLER BEARING CAGE AND R	OLLERS FAILED.		2	L	7	3 	4F	4	F	RT	A3WE    	E25NE				 
2002041000132	20020410	00132	CE  	2002	4	10	CA020322004      	1	20020312	G	5512	07326012	FITTING         			CESSNA	206   	TU206C      	2073334	CE  	CONT  	O520  	TSIO520C    	17040	SO  					HORIZONTAL STAB	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RIVETS THAT ATTACH FITTING TO FORWARD SPAR WERE SHEARED. MOST RIVETS, 10 IN ALL, SHOWED SIGNS OF RINGS AROUND SHAN	KS AT FITTING/SKIN SEAM. ONE RIVETS WAS SHEARED IN HALF. THERE WERE NO EXTERNAL SIGNS OF ANY PROBLEMS. THE STABILIZER IN	 QUESTION CAME IN FOR SKINS TO BE REPLACED. HAVING RECOLLECTED A PREVIOUS SDR ON THIS MATTER, WE DECIDED TO CHANGE ALL T	HE RIVETS 'JUST CAUSE' IN CASE THERE WAS A PROBLEM. THE RINGS AROUND THE SHANKS OF THE NON-SHEARED RIVETS MAY BE FROM WH	EN THE RIVETS WERE ORIGINALLY INSTALLED. THEY MAY HAVE SOME STRESSES IMPOSED ON THEM. I CAN'T TELL JUST BY LOOKING AT TH	EM.	1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2002051300009	20020513	00009	SO  	2002	5	13	CA020322005      	1	20020321	G	5531	7105907	ANGLE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION THE RT VERTICAL STABILIZER FORWARD SPAR ATTACH TO FUSELAGE BULKHEAD, FOUND THE RT DRAG A	NGLE CRACKED.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002091800001	20020918	00001	SW  	2002	9	18	CA020322006      	1	20020307	G	2730		CONTROL CABLE   			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235K2C     	41505	EA  					ELEVATOR	FRAYED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING ACCEPTANCE INSPECTION BEFORE ADDITION TO FLEET, THE TRIM CABLES WERE FOUND TO BE CHAFING ON THE TOP ELEVATO	R CABLE. THESE CABLES RUN IN CLOSE PROXIMITY TO ONE ANOTHER AND IT APPEARS THAT THE ELEVATOR CABLE WAS RUN OVER THE TRIM	 CABLES RATHER THAN UNDER, AND CHAFING RESULTED.ONE TRIM CABLE WAS FRAYED AND THE OTHER HAD A WORN AREA WITHOUT BROKEN W	IRES. THE ELEVAOR CABLE HAD ONE BROKEN WIRE.THE DEFECT APPEARS TO HAVE EXISTED SINCE AIRCRAFT MANUFACTURE.			1	H	7	1 	3O	3	O	 	A759    	E223				 
2002041000133	20020410	00133	CE  	2002	4	10	CA020322007      	1	20020307	G	3232	508202085	ACTUATOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) AFTER TAKEOFF GEAR WAS SELECTED UP, BUT SHOWED A RED LIGHT IN GEAR HANDLE. GEAR WAS CYCLED WITH SAME RESULTS. GEAR	 WAS THEN SELECTED DOWN AND AIRCRAFT CONTINUED TO DESTINATION. CREW THEN NOTICED THAT THE NOSE GEAR DOWN LIGHT WAS NOT L	IT. AIRCRAFT DID 2 FLYOVERS TO CONFIRM GEAR WAS DOWN. AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND FAULTY UP POSITION SWITC	H. NOSE GEAR IN DOWN POSITION WAS NOT FULLY DOWN. NOSE GEAR ACTUATOREND PLAY FOUND TO BE OUT OF LIMITS. REPLACED UP POSI	TION SWITCH AND NOSE GEAR ACTUATOR, RIGGED GEAR, AND RETURNED AIRCRAFT TO SERVICE.		1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002043000001	20020430	00001	SW  	2002	4	30	CA020322009      	1	20020319	G	2810		VENT LINE       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					FUEL CELL	OBSTRUCTED      	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED 100 HOUR ANNUAL & 12 MONTH INSPECTION. PROCEEDED TO CHECK OP OF LOW FUEL WARNING SYS. REMOVED FUE	L LINE GOING TO AIRFRAME FUEL FILTER AND ATTACHED LONG FUEL LINE SO WE COULD DRAIN FUEL CELL VIA A/C FUEL BOOST PUMPS. W	E PUT A/C POWER ON AND NOTED A/C HAD 80 GALLONS OF FUEL.  APPLIED POWER TO A/C FUEL BOOST PUMPS AND STARTED TO DRAIN THE	 FUEL SYS. NOTED THAT FUEL INDICATOR HAD NOT MOVED OFF ITS INDICATED 80 GALLONS, EVEN THOUGH LARGE AMOUNT OF FUEL HAD BE	EN REMOVED FROM A/C.  REMOVED FUEL CAP AND FOUND THAT RUBBER FUEL CELL HAD COLLAPSED AND OBSTRUCTED THE VENT LINE.		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002041000134	20020410	00134	NE  	2002	4	10	CA020322010      	2	20020215	G	8520	5999	ROLLER          			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	S3H1        	52016	NE  					ENGINE	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PN 5999 ROLLER STARTED GALLING.  LEFT SMALL STEEL FLAKES ON OIL SCREEN WHICH WERE FOUND AND IDENTIFIED DURING INSP	ECTION.  ENGINE NOSE CASE REMOVED, AND CAM RING PN 11768 REMOVED FOR RECONDITIONING.ALL 5999 ROLLERS REPLACED AS A PRECA	UTION.IF PROBLEM HAD BEEN FOUND LATER, SERIOUS DAMAGE TO ENGINE WOULD HAVE RESULTED.				1	L	7	1 	3R	3	R	 	EXPA1L71	E143				 
2002041000135	20020410	00135	EA  	2002	4	10	CA020322012      	1	20020318	G	2740	70608	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZ STAB TRIM	FAILED          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE AT THE GATE, STAB TRIM PERFORMED UNCOMMANDED FULL NOSE UP TO FULL NOSE DOWN MOVEMENT. 'STAB CH 2 INOP' STATU	S MESSAGE APPEARED. DISCONNECTED STAB TRIM. STAB TRIM RE-ENGAGED SEVERAL TIMES ON ITS OWN. INSTALLED SERVICEABLE HSTCU. 	OPS CHECKS OF STAB/YAW SYSTEM IAW 27-41-00.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002043000002	20020430	00002	EA  	2002	4	30	CA020322013      	1	20020318	G	4990	38004883	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					APU BAY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FLIGHT CAREW REPORTED SMOKE AND OIL SMELL IN COCKPIT AND CABIN. EMERGENCY DECLARED AND AIRCRAFT LANDED WITHOUT FUR	THER INCIDENT.  MAINTENANCE STARTED APU ON GROUND AND UPON TRANSFER OF BLEEDS TO APU, SMOKE FILLED THE CABIN AND COCKPIT	. ALSO,  APU OIL PRESSURE CAUTION MESSAGE APPEARED. APU DEFERRED AND THEN LATER REPLACED. FOUND THAT OIL PRESSURE RELIEF	 VALVE BOSS CRACKED. THIS SAME UNIT WAS PREVIOUSLY REPAIRED BY ALIENCE AVIATOIN FOR THE SAME PROBLEM.  RECORDS SHOW NO R	EPORTED EGT OVERTEMP CONDITIONS. APU REPLACED AND AIRCRAFT RETURNED IN SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041000136	20020410	00136	EA  	2002	4	10	CA020322014      	1	20020318	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			15051	14730							(CAN) CLIMBING THROUGH FL240 THE RIGHT COCKPIT SIDE WINDOW CRACKED. SIDE WINDOW REPLACED AND AIRCRAFT RETURNED TO SERVIC	E.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041000137	20020410	00137	EA  	2002	4	10	CA020322015      	1	20020320	G	3213	601R85001103	STRUT           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22055								(CAN) DURING INSPECTION, MAINTENANCE FOUND LT MAIN LANDING GEAR CRACKED. MAIN LANDING GEAR REMOVED AND REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041000138	20020410	00138	EA  	2002	4	10	CA020322016      	1	20020320	G	3510	380270260	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					OBSERVER OXYGEN	RUPTURED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OXYGEN LINE AT OBSERVER MASK RUPTURED. MAINTENANCE REPLACED LINE AND SERVICED THE O2 SYSTEM. LEAK CHECK CARRIED OU	T.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041000139	20020410	00139	EU  	2002	4	10	CA020325002      	1	20020321	G	2740	9443019112	SWITCH          		527401202   	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STAB TRIM	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REURNED FROM FLIGHT,LANDED AND WAS TAXIING TO HANGER WHEN HE TRIED TO CENTER HIS HORIZONTAL STAB. TRIM.,USIN	G PILOT'SSWITCH ON CONTROL COLUMN. SELECTING "UP" TRIM,THE INDICATOR SHOWED NO MOVEMENT.SO HE USED THE CO'PILOTS SWITCH 	AND STAB WAS ABLE TO CENTER. INVESTIGATION REVEALED THAT THE PILOTS STAB TRIM SWITCH HAD NO CONTINUITY WHEN SELECTED TO 	THE "UP" POSITION,AN INTERNAL MALFUNCTION.A NEW SWITCH WAS INSTALLED AND SYSTEM FUNCTIONAL TESTS WERE NORMAL.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002041000140	20020410	00140	CE  	2002	4	10	CA020325003      	1	20020204	G	8011		BEARING         		PM1201      	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	STARTER	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						80098702					(CAN) PILOT OF AIRCRAFT FOUND "A PART" BENEATH THE COWLING. COWLINGS WERE REMOVED & ENGINE INSPECTED FOR "MISSING PARTS"	. REAR SUPPORT BEARING (ROLLER TYPE) FOUND MISSING ON LAMAIR STARTER. PILOT REPORTED FURTHER THAT STARTER WAS STILL ENGA	GED TO FLYWHEEL AT THIS TIME. LOSS OF REAR BEARING CAUSED STARTER SHAFT TO DROP OUT OF ALIGNMENT WITH CRANKSHAFT AND LOC	KED BENDIX GEAR ONTO FLYWHEEL. SARTER REPLACED WITH SERVICEABLE UNIT. OLD UNIT B.E.R. SCRAP.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002041000141	20020410	00141	CE  	2002	4	10	CA020325004      	1	20020318	G	3211		PIVOT           			CESSNA	172   	172RG       	2072438	CE  										MLG	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) INSTALLATION OF UNAPPROVED PARTS AS DEFINED BY APPENDIX D - REPORTING UNAPPROVED PARTS USING THE SDR SYSTEM. PARAG	RAPH (2)(C). LANDING GEAR PIVOTS DISCOVERED WHICH HAD MATERIAL REMOVED IN ORDER TO ADDRESS THE ISSUES RAISED BY AD 2000-	06-06 C IN CONTRAVENTION OF CESSNA APPROVED PRACTICES.				1	H	7	1 	3O			 	3A17    					 
2002041700082	20020417	00082	CE  	2002	4	17	CA020325006      	1	20020317	G	3230		FUSEABLE PLUG   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	EMER BLOWDOWN	OPEN            	W				B				EMER. DESCENT           				H	R		ELECT. POWER LOSS-50 PC   	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA											(CAN) NORTHWEST OF CALGARY (CYYC)APPROX. 15 MINS AFTER TAKEOFF, A/C SUFFERED TOTAL ELECT. FAILURE: EMERG DESCENT INITIAT	ED. ATC INFORMED. EMERG DECLARED, & PILOT ALTERED COURSE FOR RED DEER, ALBERTS (CYQF). LDG GEAR COULD NOT BE LOWERED IN 	NORMAL MANNER BECAUSE ELECT. POWER IS REQD TO OPERATE UP/DOWN SELECTOR VALVE. EMERG GEAR EXTENSION NOT SUCCESSFUL OWING 	TO CIRCUMSTANCES STILL UNDER INVEST.. DECISION MADE TO CARRY ON TO EDMONTON INTERNATIONAL (CYEG) BECAUSE OF SUPERIOR EME	RG SRVCS. PILOT MADE CONTACT WITH MAINT PERSONNEL & AFTER DISCUSSION A/C COMMITTED TO LDG - WHEELS UP - ALONGSIDE RWY 20	, WHICH COMPLETED W/O SERIOUS DAMAGE TO A/C.	1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002041700083	20020417	00083	CE  	2002	4	17	CA020325007      	1	20020322	G	3260		LANDING GEAR    			MTSBSI	MU2   	MU2B60      	5780460	CE  										NLG	FALSE INDICATION	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) AFTER TAKE OFF THE CREW SELECTED GEAR UP, THE GEAR CAME UP AS USUAL BUT THE NOSE GEAR GREEN LIGHT DID NOT GO OUT. 	THE CREW SELECTED GEAR DOWN BUT GEAR REMAINED UP. NOTE THE NOSE GEAR SWITCH CONTROLS THE ELECTRICS FOR THE GEAR EXTENSIO	N / RETRACTION CREW ATTEMPTED TO PUT GEAR DOWN MANUALLY BUT THE FORWARD GEAR DOORS WOULD NOT RELEASE. NOTE THE AIRCRAFT 	WENT THROUGH SLUSH ON THE RUNWAY BEFORE DEPARTURECREW LANDED AIRCRAFT WITH GEAR UP.ONCE MAINTENANCE PUT AIRCRAFT ON JACK	S AND GOT GEAR DOWN WE COULD NOT DUPLICATE THE SNAG. FURTHER INVESTIGATION REQUIRED		1	H	7	2 	3T			RT	A10SW   					 
2002041100001	20020411	00001	NM  	2002	4	11	CA020325008      	1	20020323	G	7500	652244146	DUCT            			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	RUPTURED        	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) NR 2 ENGINE FAILED ON TAKEOFF WITH AN AUTO PACK TRIP.  AFTER ABORTED TAKEOFF THE A/C RETURNED TO THE GATE IN AND S	UBSEQUENT INSPECTION REVEALED A RUPTURED 13TH STAGE SADDLE DUCT.NEW DUCT INSTALLED ENGINE GROUND RUN SATISFACTORY AND A/	C RELEASED FOR SERVICE.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002041100002	20020411	00002	EU  	2002	4	11	CA020326001      	1	20020321	G	2910	704A33690004	BELT            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD SYSTEM	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC BELT WAS STARTING TO DEBOND NEAR THE DIRECTION OF ROTATION ARROW NEAR THE BONDED JOINT. THE TTSN OF THE 	BELT BY THE MANUFACTURE IS 600 HOURS. WE HAVE FOUND THAT THE OCCURRENCE OF DEBONDING IS HAPPENING TOO OFTEN, SO OUR INSP	ECTION OF THE BELT IS MORE OFTEN SINCE WE DO NOT WANT A BELT FAILURE.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002041100003	20020411	00003	NM  	2002	4	11	CA020326002      	1	20020323	G	7932	AS3209015016	PACKING         		3032324     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SCAV TUBE	DETERIORATED    	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA						NA					(CAN) ON TAKE-OFF ROLL, LOW OIL PRESSURE CAUTION LIGHT FLICKERED.TAKE-OFF ABORTED.SECOND ATTEMPT WAS MADE OBSERVING PRES	SURE GAUGE AND OIL PRESSURE CAUTION LIGHT FLICKERED AGAIN AND OIL PRESSURE PHYSICALLY CONFIRMED TO BE LOW BY GAUGE. TAKE	 OFF ABORTED AGAIN AND AIRCRAFT RETURNED TO GATE. UPON INVESTIGATION, MAINTENANCE FOUND OIL QAUNTITY LOW, AND NR 3,4,5 B	EARING SCAVENGE TUBES LEAKING. O-RINGS WERE REPLACED AND ENGINE GROUND RUN. TEST FLIGHT WAS ALSO CARRIED OUT AND NO LEAK	S WERE OBSERVED. L/H ENGINE WAS STARTED AT -25 DUE TO FAILURE OF ENGINE PRE-HEAT SYSTEM, SUSPECT PROBLEM OCCURED DUE TO 	COLD TEMPERATURE START.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002050300017	20020503	00017	EU  	2002	5	3	CA020326003      	1	20020307	G	3220	5322012072	DRAG LINK       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) ON APPROACH PILOT HEARD A LOAD BANG A FEW SECONDS LATER A SECOND LOUD BANG WAS HEARD. THE NOSE GEAR EXTENDED AND G	EAR DOWN AND LOCKED LIGHT CAME ON AS WELL AS NOSE GEAR UNSAFE LIGHT. PILOT SLOWED AIRCRAFT DOWN TO GEAR EXTENDED SPEED S	ELECTED GEAR DOWN. LANDED WITHOUT FURTHER PROBLEM. ON INSPECTION DRAG LINK BROKE BELOW ATTACH POINT FOR HYDRAULIC ACTUAT	OR. REPLACED DRAG LINK AND SWUNG GEAR.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002041100004	20020411	00004	SO  	2002	4	11	CA020326004      	1	20020314	G	2120	8124402	TUBE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					AIR DISTRIBUTION	SEPARATED       	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CR	CRUISE         	1			CA			10123								(CAN) - THE FORWARD RUBBER TUBE ON THE FRESH AIR TUBE BECAME DISCONNECTED IN FLIGHT.- UPON INSPECTION, THE TUBE WAS CLEA	NED WITH MEK AND RECONNECTED THEN THE SYSTEM WAS TESTED SERVICEABLE.					1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2002041100005	20020411	00005	NE  	2002	4	11	CA020326005      	2	20020318	G	8530	399359	CYLINDER HEAD   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  ENGINE CYLINDER CRACKED ON TOP OF HEAD.						1	H	7	1 	3R	3	R	 	A815    	E142				 
2002041100006	20020411	00006	NE  	2002	4	11	CA020326006      	2	20020306	G	7230	M04622AB	MODULE          			BOEING	757   	757*        	       	NM  	RROYCE	RB211 	RB211535E4B3	 	NE  					NR 2 ENG COMP	FAILED          	W				E				ENGINE SHUTDOWN         				W	M		INADEQUATE Q C            	OVER TEMP                 		CL	CLIMB          	1			CA			24500								(CAN) AIRCRAFT A/C0125 HAD 3 RAPID VIOLENT VIBRATIONS FELT APPROXIMATELY 2 MINUTES AFTER TAKEOFF. NR 2 ENGINE EGT MAXED 	OUT AT 903 C. NR 2 ENGINE THROTTLE RETARDED AND EGT REMAINED SOMEWHAT HIGH. ENGINE NR 2 SHUTDOWN SUCCESSFULLY. NO OTHER 	ABNORMAL INDICATION. ENGINE NR 2 HAD PREVIOUSLY EXPERIENCE A COMPRESSOR STALL ON TAKEOFF AT APPROXIMATELY 1000 AGL AND O	VERTEMP TO 903C FOR 2.5 SEC REDUCED POWER TO STOP OVERTEMP AND ENGINE PARAMETERS RETURNED TO NORMAL, FULL POWER TAKEOFF 	WITH TAI ON OAT 49F, EVENT RECORDED ON MARCH 2, 2002.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2002050300018	20020503	00018	EA  	2002	5	3	CA020326007      	1	20020307	G	2710		CONTROL CABLE   			CNDAIR	CL604 	CL604       	1900301	EA  										RT WING AILERON	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION FOUND RT WING OUTBOARD AILERON CONTROL CABLE RUBBING AGAINST TOP AILERON FUEL SYNC TRANS	MITTER LINK. FURTHER DETAIL INSPECTION DISCOVERED AILERON DUAL SYNC TRANSMITTER LEVER  INSTECTED APPROX 180 DEG. OUT OF 	NORMAL POS. PERFORMED VISUAL INSPECTION OF RT WING OUTBOARD CONTROL CABLE PER M/M 20-40-00 NO DISCREPANCY FOUND. DETAIL 	INSPECTION OF AILERON DUAL SYNCHRO LEVER,   FOUND SMALL GROOVE OF 0.010 ON EDGE OF LINK.  INSPECTED SURROUNDING STRUCTUR	E FOR ABNORMALITIES,  NO DISCREPANCY FOUND.  ADJUSTED AILERON DUAL SYNCHRO TRANSMITTER PER M/M 22-11-11.  SECURED AILERO	N DUAL SYNCHRO TRANSDUCER LINK PER M/M 22-11-11.	2	L	7	2 	4F			RT	A21EA   					 
2002041100007	20020411	00007	NE  	2002	4	11	CA020326008      	1	20020326	G	6320	S613520670042	HOUSING         	SKRSKY      	S613520600  	SKRSKY	S61   	S61A        	814210C	NE  										M/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23186			A14891					(CAN) 6 CRACKS WERE NOTED ON AFT END OF OUTER FLANGE UNDERNEATH STUD HOLES.  2 OF CRACKS ARE UNDER STUD HOLES, WHICH WER	E NOT INST WITH STUDS (PRE-TAPPED FOR HEAVY RING GEAR; CURRENTLY PLUGGED). CRACKS ARE ABOUT 0.18-0.27 INCHES LONG MEASU 	RED FROM CRACK CENTER.IT APPEARED THAT CRACKS RESULTED FROM OVER TAPPING OF STUD HOLES. EXAMINATION OF OF STUD HOLES SHO	WED THAT THREADS ARE TAPPED BEYOND DRXXL DEPTH, WITH 4 FLUTE MARKS (WHICH APPEARS TO BE FROM TAPPING TOOL) SHOWN AT BOTT	OM OF STUD HOLES. ALL 6 HOLES WITH CRACKS HAVE SAME FLUTE MARKS.THE DEPTH OF TAPPED HOLES HAVE AVERAGE READING OF 1.33 I	N. ACCORDING TO SIKORSKY B/P, STUD HOLE IS TAPPED 0.375-16 UNC-3B X 1.18 DEEP PER  MXX-S-8879.MAIN GEAR B	2	G	7	2 	4U			 	H2EA    					 
2002050300019	20020503	00019	EA  	2002	5	3	CA020326009      	1	20020326	G	2750	21515065	ARM             			CNDAIR	CL215 	CL2151A10   	1900320	EA  										MASS BALANCE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SMALL CRACK FOUND IN RADIUS OF THE BASE OF THE MASS BALANCE ARM.						2	H	7	2 	4R			RT	A14EA   					 
2002051300011	20020513	00011	EU  	2002	5	13	CA020326010      	1	20020325	G	3213	AN427	BOLT            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG AXLE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DUE TO PREVIOUS EXPERIENCE REMOVED LEFT AND RIGHT AXLE BOLTS EVEN THOUGH AIRCRAFT WAS POST S/B 32-006 AND DID NOT 	REQUIRE REMOVAL. BOLT WAS FOUND TO BE WORN AND STEPPED EVEN THOUGH AIRCRAFT WAS LOW TIME.AS BEFORE THERE IS NO REQUIREME	NT TO REMOVE THIS BOLT FOR INSPECTION!				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002050300020	20020503	00020	SO  	2002	5	3	CA020326011      	1	20020319	G	5552	4A314003	HINGE           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ELEVATOR	CRACKED         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			18261	18261							(CAN) THE PILOT REPORTED INTEMITTENT ELEVATOR CONTROL ABNORMALITY. INSPECTION REVEALED THAT THE RT OUTBOARD ELEVATOR HIN	GE POINT WAS CRACKED.  THE EFFECTED PARTS WHERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2002051300012	20020513	00012	CE  	2002	5	13	CA020326012      	1	20020325	G	5311	5042002857	FRAME           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15724	15724							(CAN) DURING AIRFRAME INSPECTION SMOKING RIVETS WHERE DETECTED ON THE AIRCRAFT FUSELAGE. INVESTIGATION REVEALED THAT THE	 FUSELAGE FRAME AT FLIGHT STATION 207.00 WAS CRACKED. THE FUSELAGE FRAME IS BEING REPLACED IN ACCORDANCE WITH THE MANUFA	CTURER'S RECOMMENDATIONS				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002051300013	20020513	00013	SO  	2002	5	13	CA020327002      	1	20020321	G	5711	6205600	SPAR            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					LT & RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PLATES TO BOTH THE LEFT & RIGHT ATTACHMENT OF AFT WING SPAR TO FUSELAGE FOUND BADLY CORRODED AND NECESSITATED REPL	ACEMENT.THIS WILL CAUSE DISSIMILAR METAL. THE PLATES ARE RIVETED TO THE AFT SPAR. NEW PLATES ORDERED. ATTACHED PHOTO SHO	WS CONDITION. THE ALUMINUM AFT SPAR INSPECTED FOR CONDITION OF CORROSION AND DETERMINDED SERVICEABLE. ADEQUATE CLEANING 	AND CORROSION TREATMENT APPLY.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002041100008	20020411	00008	SO  	2002	4	11	CA020327003      	1	20020321	G	5540	6354600	RUDDER          			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION INSPECTED RUDDER & CONTROL SYSTEM FOUND CORROSION ON THE HORN ASSEMBLY ON THE STEEL PART.	 RUDDER REMOVED. HORN DERIVETED. PART SANDBLASTED. INSPECTED FOR CONDITION. FOUND SERVICEABLE CONSIDERING THIS SITUATION	 THE OWNER WILL BE ADVISED.THIS IS AN IMPORTANT AREA TO INSPECT.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002050300021	20020503	00021	EU  	2002	5	3	CA020327004      	1	20020320	G	2917		PRESSURE SWITCH 			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AFTER TAKEOFF,  REPORTED THE HYDRAULIC PUMP SEEMED TO RUN LONGER THAN NORMAL, AND THAT THE UNDER FLOOR HEATER WAS 	NOT FUNCTIONING. INVESTIGATION REVEALED THAT THE HYDRALIC SYSTEM PRESSURE SWITCH WAS INTERMITTENT, CAUSING THE HYDRAULIC	 PUMP TO RUN UNTILL THE THERMAL SWITCH SHUT IT OFF, AND ALSO DISABLEING THE UNDER FLOOR HEATER.  THE SWITCH WAS REPLACED	 WITH NEW, AND THE SYSTEM FUNCTIONS NORMALLY.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002041100009	20020411	00009	SO  	2002	4	11	CA020327005      	1	20020321	G	5751		BALANCE WEIGHT  			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					LT & RT AILERON	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON LEFT AND RIGHT BALANCE WEIGHT ASSY FOUND BADLY CORRODED. PART REMOVED SANDBLASTED STEEL PART INSPECTED FOU	ND SERVICEABLE.ADEQUATE TREATMENT PRFORMED BEFORE REASSEMBLED.THIS IS CONSIDERED VERY IMPORTANT IF NO ACTION TAKEN WILL 	CAUSE LOST OF CONTROLS FLUTTERING AILERON.SUGGEST THAT PIPER OWNER'S OF PA28 SERIES BE ADVISED AS SOON AS POSSIBLE DUE T	O THE FACT OF OLD AGE OF THE AIRCRAFT.AWD WILL SUPPORT THIS SITUATION.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002041100010	20020411	00010	EU  	2002	4	11	CA020327007      	1	20020315	G	6710	V51313842CR764	BELLOWS         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					DUST BOOT	FROZEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) WATER HAD FROZEN IN DUST BOOT AND RESTRICTED MOVEMENT OF LONGITUDINAL CONTROL ROD. BELOW HYDRAULIC PACK, ICE REMOV	ED, THAWED, DRIED OUT AND LIGHTLY SPRAYED WITH METHYL ALCOHOL TO REMOVE ANY FURTHER MOISTURE.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002050300022	20020503	00022	CE  	2002	5	3	CA020327008      	1	20020322	G	3242	1338931CGNGC	STATOR          	BFGOODRICH  	215286      	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2108					(CAN) WHILE CARRYING OUT A COMPANY DIRECTED INSPECTION, NR 1 STATOR DISC WAS FOUND CRACKED THROUGH, THE OTHER WAS CRACKE	D IN SEVERAL PLACES.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002041100011	20020411	00011	NM  	2002	4	11	CA020328001      	1	20020325	G	3210	651952031	SPACER          			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING LINE MAINT IMPACT DAMAGE NOTICED ON LOWER SEGMENT CLEVIS ASSY. SIDE STRUT HAD BEEN OVERHAULED.  THE AIRCRAF	T JACKED & UPON INVESTIGATION. IT FOUND THAT EXCESSIVE PLAY BETWEEN CLEVIS ASSY & LOWER SEGMENT OF SIDE STRUT. LOWER SEG	MENT REMOVED & FWDED TO REPAIR STATION FOR REVIEW & REPAIR. INVESTIGATION. BY REPAIR FACILITY FOUND THAT SPACER & WASHER	 WERE MISSING.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002041100012	20020411	00012	EU  	2002	4	11	CA020328002      	1	20020315	G	2742	D5598123320000	FITTING         			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					HORIZONTAL STAB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PLAY AT TRIMMABLE HORIZONTAL STABILIZER (THS) REAR ATTACH FITTINGS. THS REAR ATTTACH FITTINGS HAVE PLAY BETWEEN BU	SHINGS AND THS LT AND RT AFT ATTACH FITTING BORES.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002041100013	20020411	00013	EU  	2002	4	11	CA020328003      	1	20020309	G	2910	41010029	POWER UNIT      			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN)   IN CRUISE AFTER APPROXIMATELY 1.5 HOURS IN FLIGHT, YELLOW HYDRAULIC FLUID LEVEL WENT LOW LEVEL. AIRCRAFT DIVERTE	D AND LANDED IN WINNIPEG. POWER TRANSFER UNIT (PTU) REPLACED. OPERATION CHECKED SERVICEABLE AS PER AIRCRAFT MAINTENANCE 	MANUAL REFERENCE 29-23-41-870-051.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002041100014	20020411	00014	EA  	2002	4	11	CA020328007      	1	20020316	G	2742	AC94A0855	SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					STAB TRIM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STABILIZER TRIM AND MACH TRIM TRIPPED OFF IN FLIGHT, WOULD NOT RE-ENGAGE. REPLACED CAPTAINS STAB TRIM DISCONNECT S	WITCH, FUNCTIONAL TEST CARRIED OUT.  AIRCRAFT FOUND SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041100015	20020411	00015	NM  	2002	4	11	CA020328009      	1	20020320	G	3246	BACB30MT826	TIE BOLT        			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					MLG WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A "RAMP 1 CHECK" ONE TIE BOLT WAS FOUND BROKEN ON NR  6 MAIN WHEEL ASSY. MAINTENANCE REPLACED THE MAIN WHEE	L ASSY.I.A.W. MM 33-45-01.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2002041100016	20020411	00016	CE  	2002	4	11	CA020328011      	1	20020315	G	3232		ACTUATOR        			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10000								(CAN) AT ROUTINE END PLAY CHECK, FOUND EXCESS END PLAY AFTER ONLY 1004 CYCLES.ACTUATOR REPLACED.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002041100018	20020411	00018	SO  	2002	4	11	CA020401002      	1	20020328	G	2430	VR15283B	VOLT REGULATOR  			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					LT GENERATOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LEFT GENERATOR SYSTEM FAILED DURING CLIMB.						1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2002091800002	20020918	00002	SO  	2002	9	18	CA020401003      	2	20020325	G	8520	628752	CONNECTING ROD  			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					LT ENGINE	FAILED          	W				A				UNSCHED LANDING         				K	E	Y	FLUID LOSS                	VIBRATION/BUFFET          	ENGINE STOPPAGE           	CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS IN A CRUISE CONFIGURATION WHEN A SEVERE VIBRATION, NOISE, AND OIL LEAK WAS OBSERVED FROM THE LEFT HAN	D ENGINE OF THE AIRCRAFT.AIRCRAFT ENGINE WAS SHUT DOWN, PROP FEATHERED, AND THE AIRCRAFT MADE A SAFE LANDING. INITIAL EX	TERNAL EXAMINATION OF THE FAILED ENGINE REVEALED A LARGE HOLE IN THE TOP FRONT OF THE ENGINE CASE THAT WASCAUSED BY A MA	SSIVE FAILURE OF THE NR 5 (FRONT INBOARD) CYLINDER CONNECTING ROD.  ONCE THE CONNECTING ROD HAD BROKEN, THE REMAINING AS	SOCIATED PIECES OF IT DESTROYED THE AFFECTED CYLINDER AND ENGINE CASE. PIECES OF THE REMAINING CONNECTING ROD WERE ATTAC	HED TO THE PISTON AND THE CRANKSHAFT. THE ENGINE WILL BE ANALYISED FOR THE CAUSE OF THE FAILURE.	1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2002041100019	20020411	00019	SO  	2002	4	11	CA020401006      	2	20020325	G	8520	628752	CONNECTING ROD  			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS IN A CRUISE CONFIGURATION WHEN A SEVERE VIBRATION,NOISE, AND OIL LEAK WAS OBSERVED FROM THE LEFT HAND	 ENGINE OF THE AIRCRAFT.AIRCRAFT ENGINE WAS SHUT DOWN, PROP FEATHERED, AND THE AIRCRAFT MADE A SAFE LANDING. INITIAL XTE	RNAL EXAMINATION OF THE FAILED ENGINE REVEALED A LARGE HOLE IN THE TOP FRONT OF THE ENGINE CASE THAT WAS CAUSED BY A MAS	SIVE FAILURE OF THE NR 5 (FRONT INBOARD) CYLINDER CONNECTING ROD.ONCE THE CONNECTING ROD HAD BROKEN, THE REMAINING ASSOC	IATED PIECES OF IT DESTROYED THE AFFECTED CYLINDER AND ENGINE CASE. PIECES OF THE REMAINING CONNECTING ROD WERE ATTACHED	 TO THE PISTON AND THE CRANKSHAFT. THE ENGINE WILL BE ANALYISED FOR THE CAUSE OF THE FAILURE.	1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2002041100020	20020411	00020	EU  	2002	4	11	CA020402001      	1	20020323	G	3230		SELECTOR SWITCH 			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					MLG	FAILED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON MAR 23,2002 DURING LDG PHASE IN WILMINGTON, OHIO (KILN) PILOT INITIATED DEPLOYMENT OF LDG GEAR. COCKPIT INDICAT	OR SHOWED 3 RED LIGHTS IDENTIFYING FWD GEAR DOOR LATCH UNLOCKED & NO GREEN LIGHTS TO CONFIRM THAT GEAR DOORS WERE FULLY 	OPENED & GEAR DOWN & LOCKED.  THE CAUSE OF THE MALFUNCTION WAS IDENTIFIED BY OUR CONTRACTEDAMO AS MOISTURE WITHIN THE GE	AR DOOR MICRO-SWITCHES, WHICH PREVENTED THE SELECTOR SOLENOID VALVE TO OPEN AND CONSEQUENTLY THE LANDING GEAR DID NOT RE	LEASE.  ALL SWITCHES WERE INSPECTED AND RE-SEALED.		2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2002050300023	20020503	00023	NM  	2002	5	3	CA020402002      	1	20020402	G	5270	654583042	WIRE            			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					DOOR WARNING	BROKEN          	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF OUT OF YWG, A/C WOULD NOT PRESSURIZE. NON NORMAL AUTO-FAIL CHECKLIST EXECUTED BUT DID NOT CORRECT PR	OBLEM. A/C LEVELED OFF AT 9,000 FT AND RETURN TO BASE.  LANDED IN YWG W/O INCIDENT. MAINTENANCE INSPECTION DISCOVERED E/	E SERVICE DOOR OPEN AND DOOR WARNING LIGHT UNSERVICABLE. MAINT FOUND BROKEN WIRE TERMINAL ON E/E DOOR WARNING SWITCH.  W	IRE REPLACED IAW MM 52-71-00 AND GROUND CHECKED SERVICEABLE.  SERVICE DOOR CLOSED AND  RETURNED TO SERVICE WITH NO FURTH	ER INCIDENTS TO REPORT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002041700084	20020417	00084	NE  	2002	4	17	CA020402007      	2	20020320	G	8500	NAR7B18	CARBURETOR      			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			CA											(CAN) (AIRCRAFT ON FLOATS) DURING TAXI OUT FOR TAKE OFF, ENGINE STARTED TO POP AND BACKFIRE WHICH CREATED ENGINE FAILURE	.  CARB REPLACED AND IS CURRENTLY BEING INVESTIGATED.  (NOTE: RT MAGNETO ALSO REPLACED)					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002041100023	20020411	00023	NM  	2002	4	11	CA020403001      	1	20020329	G	3230	65445815	ISOLATION VALVE 			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA											(CAN) A/C ON ROUTINE FLT ON APPROACH PLANNED FLAPS FOR LDG & SELECTED FLAPS ON SCHEDULE. AFTER FLT CREW SELECTED FLAP TO	 25 DEGS, MASTER CAUTION HYDRAULIC WARNING LIGHT FLASHED. AT TIME CREW NOTICED 'A' SYS HYDRAULIC QUANTITY READING ZERO -	 HYDRAULIC PRESSURE HELD STEADY AT 300 PSI. CREW ELECTED TO LAND A/C WITH FLAPS AT 25 - LDG UNEVENTFUL.MAINT INSP FOUND 	HYDRAULIC LEAK IN LT MLG WHEEL WELL- MLG MANUAL ISOLATION VALVE. MAINT REPLACED VALVE, & REPLENISHED SYS 'A' HYDRAULICS.	 LEAK CHECK PERFORMED AS PER MM 32-32-111 & MAINT FOUND NR 1 ENGINE DRIVEN PUMP HAD NO PRESSURE: MAINT REPLACED PUMP,&CA	RRIEDOUT LEAK CHECK AS PER MM 29-11-31, NO FAULT	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002041100024	20020411	00024	CE  	2002	4	11	CA020403002      	1	20020326	G	3244	114800115	TIRE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					NLG	UNBONDED        	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED PRINCE GEORGE,PILOTS FELT VIBRATION THRU AIRFRAME. AS IT DID NOT DIMINISH THEY ELECTED TO RETURN	. MAINTENANCE INSPECTED AIRCRAFT AND WITH NO VISIBLE DEFECTS THE AIRCRAFT WAS TEST FLOWN. NO NOTICEABLE VIBRATION WAS FE	LT AND AIRCRAFT RETURNED TO SERVICE. NEXT DAY ON ROLL OUT PILOTS FELT VIBRATION AND ABORTED TAKEOFF. AIRCRAFT WAS AGAIN 	INSPECTED AND TEST FLOWN.ONLY IF AIRCRAFT WAS ON LONG HIGH SPEED ROLLCUT DID DEFECT REOCCUR. THE NOSE WHEEL WAS DISASSEM	BLED AND THE BALANCE WEIGHT ON THE INNER PORTION OF THE TIRE WAS FOUND UNBONDED. THE TIRE WAS REPLACED AND A SATISFACTOR	Y TEST FLIGHT COMPLETED.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2002050300025	20020503	00025	EU  	2002	5	3	CA020403003      	1	20020325	G	5280	SD3101059XA	BOSS            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					NLG DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROUTINE INSPECTION REVEALED EXTRA PLAY IN NOSE GEAR DOORS. FURTHER INVESTIGATION SHOWED THAT 4 BOLTS HAD SHEARED. 	 THIS WAS LIKELY DUE TO THE FACT THAT THE BOSS HAD SEIZED ON THE TUBE THAT GOES THROUGH IT. THE INTERNAL SURFACE OFTHE B	OSS WAS HIGHLY CORRODED. THERE IS NO SCHEDULED MAINTENANCE FOR THIS AREA. NO GREASE NIPPLE IS PROVIDED FOR LUBRICATION A	ND TO KEEP MOISTURE OUT.			2	H	7	2 	4T	4	T	 	A41EU   	E4EA				 
2002041100025	20020411	00025	SO  	2002	4	11	CA020403004      	1	20020320	G	2140	84251003	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	HEATER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING AT AD 2001-17-13 (JANAERO SOLENOID/SHUTOFF VALVE LEAK CHECK) THE HEATER FUEL PUMP WAS FOUND TO BE L	EAKING OUT OF THE POWER WIRE GROMMET. THIS PUMP IS UNDER THE CENTRE FLOOR BOARD IN THE CABIN AND ALTHOUGH THERE IS A DRA	IN UNDER THE PUMP FUEL WAS RUNNING ALONG THE BELLY SKIN INSIDE THE AIRCRAFT.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2002041100026	20020411	00026	SO  	2002	4	11	CA020403005      	1	20020401	G	6120		DRIVE UNIT      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROP GOVERNOR	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) A/C DEPARTED AT APPROX 02:00 ZULU ON APR 2 ON IFR FLT TO VANCOUVER. DURING INITIAL STAGE OF CLIMB, RT ENGINE RPM B	EGAN TO FLUCTUATE & OVERSPEED. PILOTS TRIED TO CONTROL IT WITH THROTTLE & PROPELLER CONTROLS BUT WHERE UNSUCCESSFUL & CH	OOSE TO FEATHER ENGINE & RETURN TO PENTICTON. UPON INSPECTION MAINT CREW DISCOVERED THAT DRIVE ON PROP GOVERNOR BROKEN. 	GOVERNOR HAS APPROX 800 HRS SINCE OVERHAUL. GOVERNOR REMOVED FROM ENGINE & OVERHAULED GOVERNOR INSTALLED. A/C GROUND RUN	 & FOUND ACCEPTABLE FOR RETURN TO SERVICE.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002041700088	20020417	00088	CE  	2002	4	17	CA020403006      	1	20020320	G	5210	1014300291	LATCH           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					AIRSTAIR DOOR	FAILED          	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF CALGARY (CYYC), CLIMBING THROUGH 14,000 FEET, THE CREW AND PASSENGERS HEARD A LOUD BANG, THEN THE CA	BIN AIRSTAIR DOOR DROPPED OPEN. THE CREW DECLARED AN EMERGENCY TO ATC, INSTITUTED AN EMERGENCY DESCENT AND TURNED BACK F	OR CALGARY WHERE THEY LANDED WITHOUT FURTHER INCIDENT. THE CAUSE OF THIS DOOR FAILURE IS NOT FULLY KNOWN AT THIS TIME, B	UT IT DOES APPEAR THAT THE FORWARD UPPER LATCH HOOK ASSEMBLY FAILED. REPORTS ON THE EXACT CAUSE WILL FOLLOW AFTER INVEST	IGATION.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002050300026	20020503	00026	NM  	2002	5	3	CA020403007      	1	20020327	G	2421		DRIVE SHAFT     	LUCAS       	31708001A   	DHAV  	DHC8  	DHC8*       	       	NM  										AC GENERATOR	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA						326					(CAN) DRIVE SHAFT SPINS FREE.  INTERNAL SPLINES OF THE ROTOR AND EXTERNAL SPLINES OF THE DRIVE SHAFT WORN OUT (FAILED) .	 PROBABLE CAUSE IS OIL ORIFICE IN THE ROTOR PLUGGED WITH VARNISH PREVENTING LUBRICATION OF ROTOR AND DRIVE SHAFT SPLINES	.				2	H	7	2 	4T			RT	A13NM   					 
2002041100027	20020411	00027	SW  	2002	4	11	CA020403008      	1	20020321	G	5320	206033110189	STIFFENER       			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16300								(CAN) CRACKED VERTICAL STIFFENER. CUTOUT IN HORIZONTAL STIFFENER WAS TOO SMALL WHICH PUT PRESSURE ON VERTICAL STIFFENER 	CAUSING IT TO CRACK.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002041100028	20020411	00028	SW  	2002	4	11	CA020403009      	1	20020326	G	6320	6871064	RING            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BALANCE RING WAS PARTIALLY CRACKED. (MAIN GEARBOX TORQUE GEAR "BALANCE RING" FOUND CRACKED)						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002041100029	20020411	00029	NM  	2002	4	11	CA020404001      	1	20020328	G	3211	654581945	GUSSET          			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAINTENANCE INSPECTION - SERVICE CHECK DURING REGULAR SCHEDULED MAINTENANCE, ENGINEER FOUND NOSE LANDING GEAR UPPE	R SUPPORT AT ACTUATOR ATTACH BRACKETS CRACKED.  MAINTENANCE REPLACED UPPER DRAG BRACE, GUSSET AND 'T' EXTUSION FOR NOSE 	LANDING GEAR ACTUATOR. NDT INSPECTION OF EXPOSED STRUCTURE AND SUPPORT FITTING CARRIED OUT WITH NO DEFECTS NOTED. AIRCRA	FT RETURNED BACK TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002041100030	20020411	00030	EU  	2002	4	11	CA020404002      	1	20020402	G	3297	622800200	WIRE            			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	MLG	BROKEN          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE PILOT NOTICED THAT THE NOSE GEAR WAS NOT INDICATING DOWN AND LOCKED.  AFTER CYCLING THE GEAR WITH 	NO CHANGE IN THE INDICATION, A FLY PAST WAS CARRIED OUT TO DETERMINE THE GEAR STATUS.  AFTER DECIDING THAT THE GEAR WAS 	LIKELY DOWN AND LOCKED A LANDING WAS ATTEMPTED WITH ERS ON STANDBY.  THE LANDING WAS SUCCESSFUL.ON INVESTIGATION A WIRE 	WAS FOUND TO BE BROKEN ABOUT 12 INCHES FROM THE SWITCH.			2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL	 
2002041100031	20020411	00031	NM  	2002	4	11	CA020405001      	1	20020330	G	3211		STRUCTURE       			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SCHEDULED MAINTENANCE;DURING REGULAR SCHEDULED MAINITENANCE INSPECTION, MAINTENANCE ENGINEER SUSPECTED A CRACK AT 	THE NOSE LANDING GEAR ACTUATOR ATTACH SUPPORT BRACKET (FORWARD SIDE UPPER R/H SIDE). NDT CALLED IN AND 3/8 INCH CRACK CO	NFIRMED BY HFEC METHOD IAW 51-00-00.MAINTENANCE REPLACED NLG TEE P/N: 65-45819-551 BELOW WL207 AT BLO.OO, STN 259.5 IAW 	BOEING DRAWING 65-45819 REV.G. AIRCRAFT LANDING GEAR SYSTEM GROUND CHECKED SERVICEABLE.AIRCRAFT RETURNED BACK TO SERVICE	 WITH NO FURTHER INCIDENTS TO REPORT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002041700097	20020417	00097	CE  	2002	4	17	CA020405003      	1	20020327	G	2820	11892000029	LINE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	FUEL TRANSFER	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) THE L/H FUEL CROSS TRANSFER TUBE WAS FOUND CHAFED THROUGH AND SEEPING FUEL. THE WEAR MARK ON THE TUBE MEASURED APP	ROXIMATELY 5/16 INCH IN LENGTH X 1/8 INCH IN WIDTH. REF: IPC 28-20-00. WEAR OCCURRED FROM THE WIRE BUNDLE COVERING OF TH	E GEAR UPLOCK MICROSWITCH. THE BUNDLE WAS SECURED CLEAR AFTER FUEL TUBE REPLACEMENT. SUGGEST OPARATORS CHECK THIS AREA. 	THE FUEL TUBE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002041100032	20020411	00032	SO  	2002	4	11	CA020405005      	1	20020326	G	3246	AN620A	BOLT            			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					MGL WHEEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAIN WHEEL ASSEMBLY TIRE REPLACEMENT, THREE TIE BOLTS OUT OF EIGHT SHEARED WHEN RECOMMENDED TORQUE WAS APPL	IED. PRIOR TO ASSEMBLY ALL BOLTS WERE VISUALLY INSPETED AND NO EVIDENCE OF CRACKS WERE NOTED. ALL EIGHT BOLTS WERE REPLA	CED.				1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2002050300046	20020503	00046	NE  	2002	5	3	CA020405027      	2	20020331	G	7230	LK69554	TUBE            			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					P3 AIR	BROKEN          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) WHILE CLIMBING THROUGH FLT LEVEL 290 , NR 2 ENGINE POWER WENT DOWN TO IDLE POWER ONLY. ABNORMAL CHECK LIST CARRIED	 OUT WITH NO SUCCESS. A/C RETURNED TO YMX.  NO THROTTLE RESPONSE AT ALL. MAINT REPLACED THE FUEL FLOW REGULATOR IN ACCOR	DANCE WITH MM.  FOUND TO BE SERVICEABLE. VERIFICATION FLT CARRIED OUT&POWER WENT TO IDLE PAST FLT LEVEL 240 AND EVERYTHI	NG WENT BACK TO NORMAL WHEN POWER APPLIED AT FLT LEVEL 180.  AFTER INSPECTION,  MAINT FOUND ALTITUDE SWITCH NOT WITHIN L	IMIT WITH TEST NR 1 AND REPLACED IT		2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002041700119	20020417	00119	EU  	2002	4	17	CA020405028      	1	20020331	G	7603	4261212	THROTTLE CABLE  			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2*    	 	GL  					NR 2 ENGINE	CONTAMINATED    	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN)  ENGINE NR 2 THROTTLE JAMMED IN DESCENT , IN IDLE POSITION. MAINTENANCE FOUND THE THROTTLE CONTROL CABLE ASSEMBLY 	 WATER SOAKED AND ALSO FOUND THE ELASTOMER SLEEVE RIPPED OPENED. BOTH PARTS WERE REPLACED ; THE THROTTLE CONTROL CABLE A	SSY.REPLACED I.A.W. MM 76-11-41 AND THE ELASTOMER SLEEVE , I.A.W. SB A310-76-2012.A VERIFICATION FLIGHT WAS CARRIED SERV	ICEABLE.			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2002050300047	20020503	00047	SW  	2002	5	3	CA020408001      	1	20020308	G	7332	209062608001	VENT            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL PRESSURE	CLOGGED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) FUEL PRESSURE FLUCTUATED, FUEL PRESSURE TRANSMITTER PORT AND VENT FOUND ALMOST CLOGGED BY MUDDY SUBSTANCE.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002050300048	20020503	00048	EA  	2002	5	3	CA020408002      	2	20020319	G	7321		SEAL            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) MANUAL FCU LEAKS AT CONTROL SHAFT SEAL, INTERCONNECT SIDE.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002050300049	20020503	00049	SW  	2002	5	3	CA020408003      	1	20020308	G	7714	209075326	CONTROL BOX     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					RPM WARNING	CORRODED        	W				A				UNSCHED LANDING         				N			FALSE WARNING             			HO	HOVERING       	1			CA											(CAN) WHILE HOVERING OVER WATER ALL KINDS OF WARNING LIGHTS AND HORNS CAME ON. PARAMETERS LOOKED NORMAL, AIRCRAFT WAS FL	OWN TO THE CLOSEST AIRPORT, RPM BOX WAS OPENED AND FOUND CORRODED, WAS SUBSEQUENTLY REPLACED.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002050300050	20020503	00050	SW  	2002	5	3	CA020408004      	1	20020307	G	2822	2050606063	PUMP            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL BOOST	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN FLIGHT, FUEL PRESSURE FLUCTUATED AND WENT TO ZERO ON LT FUEL PUMP,  CIRCUIT BREAKER POPPED.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002050300051	20020503	00051	GL  	2002	5	3	CA020408005      	2	20020402	G	7240	6870992	COMBUSTION LINER			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE PERFORMANCE DETERIORATED, POWER CHECK CARRIED OUT, ENGINE DID NOT MEET SPECIFICATIONS. VISUAL INSPECTION RE	VEALED A CRACK IN LT ARMPIT OF THE OUTER COMBUSTION CAN. THE CAN WAS REPLACED.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300092	20020503	00092	SW  	2002	5	3	CA020408006      	1	20020311	G	3213	22041	AXLE            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2B     	41508	EA  					MLG	SHEARED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING THE TAKEOFF RUN ON ICE THE AIRCRAFT CROSSED OVER SOME SMALL SNOWMOBILE TRACKS. WHEN THE AIRCRAFT BECAME AIR	BORNE THE RIGHT SKI SEPARATED. THE SKI, STILL ATTACHED BY THE SAFETY WIRE, FLAILED AROUND CAUSING SUBSTANTIAL DAMAGE TO 	THE BELLY AND RT STRUTS. EVENTUALLY THE FORWARD SAFETY WIRE FAILED AND THEN SWUNG AROUND TO BECOME LODGED BEHIND THE LT 	SKI, BUT NOT BEFORE STRIKING THE REAR FUSELAGE AND DAMAGING THE FABRIC AND REAR BULKHEADS. SUBSTANTIAL AIRCRAFT DAMAGE U	PON LANDING AND RESULTING GROUND LOOP.		1	H	7	1 	3O	3	O	NC	A759    	E274				 
2002050300094	20020503	00094	EA  	2002	5	3	CA020408007      	1	20020321	G	2910	200809271	LINE            			CNDAIR	CL600 	CL600*      	       	EA  										HYD SYSTEM	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING, HYDRAULIC FLUID NOTICED STEAMING FROM NR 3 BRAKE UNIT AND DRIPPING FROM NR 3 & 4 BRAKE UNIT.  LEAK 	CHECK REVEALED FLUID LOSS FROM NR 4 (RT OUTBOARD) BRAKE UNIT PIPE 1/8 INCH FORWARD OF BANJO FITTING LOCATED ON TOP OF BR	AKE.  IMPROVEMENTS IN THAT SECTION OF LINE TO GET AWAY FROM RIGID PIPE IN SUCH A HARSH ENVIRONMENT OF VIBRATION.  ALSO N	EW REPLACEMENT LINES NEED TO BE REFORMED TO FIT APPLICATION CORRECTLY AND BANJO DOES NOT SIT PERFECTLY FLAT ON BRAKE UNI	T WHICH INDUCES A TORSIONAL STRESS ON THE LINE TO BANJO JOINT. SUPPORTING THE BANJO DURING BOLT MOVEMENT IS CRITICAL. OC	CURRENCES IN THIS EXACT AREA ARE NOT UNCOMMON.	2	L	7	2 	4F			RT	A21EA   					 
2002050300095	20020503	00095	EU  	2002	5	3	CA020408008      	1	20020318	G	3250	Z4242170001	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) A STUDENT PILOT REPORTED EXCESSIVE MOVEMENT IN THE NOSE GEAR STEERING SYSTEM. A MAINTENANCE CHECK REVEALED THAT TH	E LT NOSE GEAR STEERING SPRING WAS BROKEN. THE SPRING WAS REPLACED USING THE MINIMUM COIL DISTANCE SETTING ON THE L/H & 	R/H SPRINGS. THE PROBLEM MAY BE RELATED TO NOT HAVING THE AIRCRAFT ROLLING BEFORE STEERING THE AIRCRAFT LEFT OR RIGHT.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002050300096	20020503	00096	EU  	2002	5	3	CA020408009      	1	20020319	G	7810	L24266701320	STRUT           			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					EXHAUST MANIFOLD	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION THE EXHAUST STAY STRUT WAS FOUND BROKEN AT THE THREADED PART OF THE EYE END. A NEW ST	RUT AND EYE END ASSEMBLY WAS INSTALLED AND POSITIONED FOR PROPER FIT. THIS EYE END IS SECURED BY THE UPPER RIGHT HAND NU	T THAT ALSO SECURES THE FUEL INJECTION SERVO. IF THE NUT HAD LOOSENED OFF THE EYE END COULD HAVE SWUNG DOWN AND INTERFER	ED WITH THROTTLE MOVEMENT.IT IS RECOMMENDED THAT THE NUT BE CHECKED FOR SECURITY EVERY INSPECTION AND THE STRUT ASSEMBLY	 BE INSTALLED WITH THE MINIMUM AMOUNT OF TENSION.		1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002050300098	20020503	00098	EU  	2002	5	3	CA020408011      	1	20020325	G	3242	16402201	DISK            			BNORM 	BN2   	BN2B27      	7080227	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	BRAKE	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN)        BRAKE DISC FAILED.  THE DAY OF THE FAILURE HAD SLUSH ON THE TAXI WAY, IT GOT IN AROUND THE DISC AREA. MAY B	E A PART OF THE FAILURE IS DUE TO THERMAL SHOCK COOLING (HOT DISC, COLD SLUSH).					1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920	 
2002050300103	20020503	00103	EA  	2002	5	3	CA020408012      	1	20020402	G	7830	CN6241242005	VANE            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  					LT ENGINE T/R	MISINSTALLED    	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN)    DURING CUSTOMER ACCEPTANCE FLT, UPON TOUCH DOWN & AFTER APPLICAITON OF FULL THRUST REVERSER POWER, A/C VEERED T	O RT APPROX. 30 TO 40 DEGS FROM RWY HEADING. CORRECTIVE ACTION TO STOW THRUST REVERSERS & CONTROL DIRECTIONAL CONTROL US	ING RUDDER. INVESTIGATION REVEALED THAT THRUST REVERSER OF LT ENGINE INCORRECTLY INSTALLED. THRUST REVERSER CASCADE VANE	S WERE NOT POSED AT APPROPRIATE LOCATION FOR LT ENGINE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002041700120	20020417	00120	WP  	2002	4	17	CA020408013      	1	20020402	G	2520	1103080100	CONTROL BOX     			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					PAX SEAT	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) SEAT ELECTRONIC BOX POSITIONED AT ROW 25 DE , STARTED SMOKING. THE SEB WAS DICONNECTED BY THE CREW. MAINTENANCE RE	PLACED THE UNIT.					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002050300105	20020503	00105		2002	5	3	CA020408014      	4	20020313	G	3420		GYRO            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) TAKEOFF RUNWAY CLIMBING THROUGH 4,500 FT. THE PILOT REPORTED A COMPLETE AVIONICS FAILURE, AND THEN A RETURN TO NOR	MAL OPERATION. CONDUCTING AN I.F.R. APPROACH TO RUNWAY.  THE PILOT REPORTED AN ERRATIC HSI CDI. TOWER GRANTED A CONTACT 	APPROACH. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INSTALLED A SERVICEABLE HSI AND CARRIED OUT EXHAUSTI	VE TROUBLE SHOOTING TEST FLIGHT BUT, COULD NOT DUPLICATE THE CONDITIONS REPORTED BY THE PILOT. THE AIRCRAFT WAS RETURNED	 TO SERVICE.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002050300106	20020503	00106	EA  	2002	5	3	CA020408015      	1	20020408	G	5610	601R330339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ENROUTE AT 33,000 FEET, THE LEFT WINDSHIELD SHATTERED. FLIGHT DIVERTED TO JFK.WINDSHIELD REPLACED AND AIRCRAFT RET	URNED IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050300107	20020503	00107	EA  	2002	5	3	CA020408016      	1	20020329	G	3320	9906813004	CONTROLLER      			CNDAIR	CL604 	CL604       	1900301	EA  										CABIN	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA						01110012333					(CAN) IT HAS BEEN FOUND DURING DEVELOPMENT OF A CABIN MANAGEMENT SYSTEM. IT DID NOT MEET THE MANUFACTURER'S SPECIFICATIO	NS. THE UNIT IS USED TO SWITCH CABIN LIGHTS. THE SPECIFICATION WAS MENTIONING CAPACITY FOR MAX CONTINUOUS RATING OF 7.5 	AMPS, THE CONTROLLED CURRENT MEASURED 6.5 AMPS FOR THE CABIN LIGHTS WHICH IS WITHIN SPECS. DURING GROUND TESTING THE SWI	TCHING UNIT FAILED AND GENERATED A LOT OF SMOKE IN THE CABIN. AFTER INVESTIGATION, WITHIN THE UNIT IT WAS FOUND THAT THE	 PRINTED CIRCUIT BOARDS WERE BURNED.		2	L	7	2 	4F			RT	A21EA   					 
2002041700121	20020417	00121	NM  	2002	4	17	CA020408017      	1	20020405	G	3246	26015711	WHEEL           			BOEING	737   	737297      	1384480	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLIGHT CREW REPORTED ON TAXI THE AIRCRAFT SEEMED TO REQUIRE MORE POWER THAN NORMAL - AIRCRAFT DEPARTED WITHOUT INC	IDENT.ON NEXT LANDING THE CREW NOTICED THE SAME AND REPORTED TO YLW MAINTENANCE. INSPECTION FOUND THE MAIN BRAKE ON NR 2	 MAIN WHEEL ASSEMBLY SEIZED AND THE NR 2 TIRE RIM CRACKED/DETACHED FROM ASSEMBLY. MAINTENANCE REPLACED THE MAIN WHEEL AS	SY, P/N: 2601571-1, THE NR 2 MAIN GEAR BRAKE ASSY. MAIN LANDING GEAR SYSTEM AND AIRCRAFT GROUND CHECKED SERVICEABLE - AI	RCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002050300114	20020503	00114	NE  	2002	5	3	CA020409001      	3	20020324	G	6114	PRP0119026	O-RING          			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  	PROPELLER	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) PROP REPLACED ON AIRCRAFT AFTER TROUBLESHOOTING PROPELLER CONTROL SYSTEM AND INSPECTING OIL PUMP AND LINES.  NO DE	FECTS FOUND IN PUMP,  LINES OR WITH GOVERNOR ASSY.  REPLACING PROP SOLVED PROBLEM.   DISASSEMBLY  REVEALED DAMAGED SEAL 	IN FRONT OF PITCH CHANGE PISTON CAUSING OIL PRESSURE TO BUILD UP ON BACKSIDE OF PISTON, AND FORCING PROP TO COARSE PITCH	. THIS OIL PRESSURE WAS GREATER THAN RETURN SPRING PRESSURE AND THE HUB HAS NO DUMP PROVISION IN THIS AREA TO ALLOW OIL 	TO RETURN TO THE ENGINE.		1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO	 
2002091800003	20020918	00003	SW  	2002	9	18	CA020409003      	1	20020322	G	6730		ACTUATOR        			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ROTARY	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROTARY ACTUATOR SEIZED AND HAS NO SCHEDULED MAINTENANCE OR CHECK INTERVAL.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002041700122	20020417	00122	CE  	2002	4	17	CA020410001      	1	20020408	G	3230	903610373	DOWNLOCK SWITCH 			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					MLG	OPEN            	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING DESCENT APPROACH FOR LANDING, PILOTS SELECTED GEAR DOWN AND RECEIVED A DOWN LOCK INDICATION FOR NOSE GEAR A	ND LT MAIN GEAR, NO DOWN LOCK INDICATION FOR RT MAIN GEAR. WITH THROTTLES AT FLIGHT IDLE THERE WAS NO GEAR HORN, NO IN T	RANSIT LIGHT. PILOTS RESELECTED GEAR SEVERAL TIMES WITH THE SAME RESULTS. IT WAS DETERMINED BY MAINTENANCE THAT THE GEAR	 PROBLEM WAS INDICATION ONLY. THE PILOTS HAD TOWER CONFIRM THAT THE RT GEAR WAS DOWN AND LANDED WITHOUT INCIDENT. INVEST	IGATION BY MAINTENANCE FOUND THE DOWNLOCK SWITCH CONTACTS RESPONSIBLE FOR INDICATION HAD FAILED, (OPEN CIRCUIT).		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002050300120	20020503	00120	CE  	2002	5	3	CA020410002      	1	20020410	G	2710	ASABOVE	BELLCRANK       			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					AILERON	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   DURING INSPECTION THAT REQUIRED REMOVAL IT WAS NOTICED THAT THE HOLE IN THE OUTPUT ARM (AILERON PUSHROD ATTACH P	OINT) HAD BEEN INCORRECTLY DRILLED TO 5/16 INCH INSTEAD OF 1/4 INCH.  THIS ALLOWED LOST MOTION BETWEEN THE PUSHROD AND B	ELLCRANK.  THE BORE OF THE HOLE SHOWED PRIMER EXISTING FROM MANUFACTURE.  MANUFACTURER WAS CONTACTED AND WILL BE SHOWN T	HE DEFECT AND IT WAS HINTED THAT THIS PROBLEM HAD BEEN SEEN BEFORE.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002050300122	20020503	00122	EA  	2002	5	3	CA020410003      	1	20020409	G	2820	700246C	HOUSING         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					VALVE BODY	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) INSPECTED FUEL LEAK IN BELLY TANKS.  FOUND AFT MOTIVE FLOW VALVE LEAKING DUE TO CRACKED BODY. HIGH TORQUE (50 FOOT	 LBS.) USED TO ASSEMBLE UNIT.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002050300141	20020503	00141	SW  	2002	5	3	CA020411001      	1	20020408	G	5210	2724044010	SKIN            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ROUTINE DAILY INSPECTION A CRACK WAS DISCOVERED IN LOWER FWD CORNER OF PASSENGER DOOR, EMMINATING FROM RIVET HO	LES IN CORNER BRACKET WHERE IT SPLICES TO LOWER FRAME CHANNEL. CRACK CONTINUED 1.5 IN ALONG EDGE OF THE BRACKET & ALSO U	NDER DOOR'S OUTER SKIN. DOOR REMVD&SKIN LIFTED FROM CORNER TO FIND THAT CRACK CONTINUED ALONG ATTACHMENT FLANGE FOR 3.5 	IN. NEW -12 CORNER BRACKET FITTED THAT IS FACTORY UPGRADED TO THICKER MATERIAL. WEB OF OLD CORNER BRACKET IS DEFORMED IN	 AREA OF CRACK AS IF SOMETHING HAS BEEN CAUGHT BETWEEN DOOR & FRAME IN PAST.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2002050600001	20020506	00001	NE  	2002	5	6	CA020411002      	2	20020323	G	7310	2193340	LINE            			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502L     	41580	NE  					FUEL CONTROL	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, CREW RECEIVED LT ENGINE FIRE WARNING.  WARNING WENT OUT AFTER ENGINE THROTTLED BACK,  BUT THEN ITT B	EGAN CLIMBING. CREW SHUTDOWN ENGINE AND PERFORMED SINGLE ENGINE LANDING.  SUBSEQUENT INSPECTION REVEALED THAT FUEL LINE 	BETWEEN FLOW DIVIDER AND MANIFOLD CRACKED AT BRAZED JOINT CAUSING FUEL TO LEAK AND SUBSEQUENTLY FIRE THAT BURNED THROUGH	 EXHAUST NOZZLE. ENGINE REMOVED AND REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2002050600002	20020506	00002	NM  	2002	5	6	CA020411003      	1	20020320	G	2910	82920010169	LINE            			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) -DURING APPROACH PILOT SELECT GEAR DOWN. THEN PILOT NOTICE MANY CAUTION LIGHTS: SPOILER, ISOVALVE, STEERING AND HY	D TANK NR 2 LEVEL EMPTY. BUT GEAR LOCK DOWN OK 3 GREEN LIGHTS.  AIRCRAFT LAND NORMALLY AND SAFELY.  MAINTENANCE FOUND AL	UMINIUM HYDRAULIC LINE FOR LANDING GEAR DOWN PRESSURE CRACK IN A RADIUS (LINE IS IN THE WING TO FUSELAGE BOX)(CRACK LOOK	ED LIKE A FATIGUE CRACK). LINE REPLACED SYSTEM SERVICED, NO MORE LEAK.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002050600010	20020506	00010	NE  	2002	5	6	CA020411004      	1	20020221	G	6320		LOCK            			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					M/R GEARBOX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT FREEWHEEL CHANGE LOCKS WERE LOOSE. GEARS WERE REPLACED FOR FURTHER INSPECTION IN SHOP.  PARTS WERE REMOVED FROM	 MAIN GEARBOX.					2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2002050600011	20020506	00011		2002	5	6	CA020411005      	4	20020313	G	6113	055032111	BULKHEAD        	CESSNA      	055032111   	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) SECOND PART FAILURE IN THE SAME AREA HEARD REPORTS OF THIS PART FAILING FROM OTHER OPERATORS.  SPINNER AND AFT BUL	KHEAD HAVE A VERY POOR FIT.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002050600013	20020506	00013	CE  	2002	5	6	CA020411007      	1	20020402	G	2720	03101965	SPRING          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					RUDDER	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14032								(CAN) DURING THE PRE-FLIGHT INSPECTION, THE FLIGHT INSTRUCTOR NOTICED A COMPLETE DEFLEXION OF THE RUDDER CONTROL (TOWARD	S THE RIGHT) WHEN THE NOSEWHEEL WAS CENTERED.  AS WELL, THE PEDALS WERE NOT EVEN. DURING MAINTENANCE,   NOTICED THAT THE	 FRONT PART OF THE SPRING WAS UNHOOKED.  INSPECTED THE AFFECTED PARTS AND REPLACED THE SPRING,  EVEN THOUGH IT WAS NOT B	ROKEN.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002050600014	20020506	00014	CE  	2002	5	6	CA020411008      	1	20020402	G	5510	04320041	BRACKET         	CESSNA      	043200161   	CESSNA	150   	A150K       	2071824	CE  	CONT  	O200  	O200A       	17020	SO  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BRACKET WAS FOUND TO BE CRACKED. AIRCRAFT IS BEING REBUILT AFTER AN ACCIDENT.						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002051300015	20020513	00015	NE  	2002	5	13	CA020411009      	3	20020224	G	6197	L195A12KU1C22	WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ZONE 521	CHAFED          	W				A				UNSCHED LANDING         				B	B		SMOKE/FUMES/ODORS/SPARKS  	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA											(CAN) AFTER DEPARTURE, CREW NOTICED FAINT ODOUR AND SAW AUTOFEATHER CB WAS POPPED.  ELECTED TO RETURN AND DURING DECENT 	ODOUR INCREASED ACCOMPANIED BY SMOKE. DEPLOYED AND DONNED O2 MASKS. WENT THRU EMERGENCY PROC: SMOKE DISSIPATED,  UNEVENT	FULL LANDING. DURING MAINT INSPECTION,  WIRES BEHIND AUTOFEATHER SWITCH GOING TO PRINTED CCT BOARD WERE FOUND MELTED. PC	B ALSO HAD BURNED SOLDER TRACKS. TRACING WIRES OUT TO ENGINE NACELLES RT HAD NO DEFECTS BUT IN ZONE 521 BEHIND LT ENGINE	 WIRES FOR AUTOFEATHER SYS AND KU1C22 FOR LDG LIGHT SYS HAD CHAFED TOGETHER ENOUGH TO SHORT.  ALLOWED 35 AMPS FROM LIGHT	ING TO ENTER 5 AMP AUTOFEATHER SYS.  A TOTAL OF 21 WIRES WHERE REPLACED AND REROUTED.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002050600015	20020506	00015	WP  	2002	5	6	CA020411010      	1	20020409	G	2612	356680900	FIRE LOOP       			CVAC  	580   	580         	2422806	WP  	ALLSN 	501D  	501D13      	03004	GL  					NR 2 ENGINE	OUT OF POSITION 	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) NR 2 ENGINE ZONE 1 FIRE ALARM WARNING AND BELL SOUNDED ENROUTE YYC YVR.  ENGINE SHUT DOWN FOLLOWING EMERGENCY PROC	EDURE.  MAINTENANCE CONTACTED VIA RADIO AND WAS ADVISED TO LAND IN YLW.  LANDING UNEVENTFUL NO EMERGENCY DECLARED.  MAIN	TENANCE FOUND AND REPOSITIONED FIRE WIRE, AND GROUND TESTED SERVICEABLE.  A/C RELEASED FOR FURTHER FLIGHT TO YVR.NEXT DA	Y FIRE WIRE REPLACED AS A PRECAUTION.			2	L	7	2 	4T	4	T	RT	        	E282				 
2002050600016	20020506	00016	EA  	2002	5	6	CA020412001      	1	20020409	G	2782		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LE FLAPS	FAILED          	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) "FLAP FAIL" WHEN FLAPS WERE SELECTED TO 8 DEG DURING APPROACH.  EMERGENCY DECLARED AND LANDED.  SYSTEM WOULD NOT R	ESET.  FERRIED A/C , R&R'D LT INBD FLAP NR 1 AND 2 ACTUATORS FOR FAILING THEIR TORQUE CHECK.  "FLAP FAIL" AT ZERO DEG AT	 205 KNOTS ON DESCENT TO CVG. RT OUTBOARD FLAP PANEL TWISTED.  RT FLEXSHAFT NR 4 TWISTED OFF WHERE IT ENTERS SWAGE ON IN	BOARD SIDE OF NR 4 RT ACTUATOR. R&R'D ALL 5 RT FLEXSHAFT, R&R'D RT OUTBOARD FLAP PANEL, R&R'D RT NR 3 AND 4 ACTUATORS. R	IGGED SYSTEM, FECU POTS, OHMED AND MEGGED BPSU HARNESS. RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050600017	20020506	00017	EA  	2002	5	6	CA020412002      	1	20020409	G	2721	601R5122623	CONTROL PANEL   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					RUDDER TRIM	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			13176	10769							(CAN) CREW REPORTED THAT RUDDER TRIM INPUT (NOSE RIGHT) WAS APPLIED BUT, WHEN TRIM SWITCH WAS RELEASED, THE AIRCRAFT CON	TINUED TO YAW PROGRESSIVELY MORE. THE RUDDER TRIM INDICATOR CONFIRMED THAT TRIM WAS STILL BEING APPLIED. THE TRIM SWITCH	 WAS THEN MOVED TO THE 'NOSE LEFT' DIRECTION AND, AFTER SEVERAL ATTEMPTS, THE YAW WAS ARRESTED. MAINTENANCE REPLACED THE	 RUDDER TRIM PANEL AND THE PROBLEM HAS NOT BEEN REPORTED SINCE. AIRCRAFT BACK IN SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050600018	20020506	00018	EA  	2002	5	6	CA020412003      	1	20020409	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING DESCENT FOR APPROACH, THE LT SIDE WINDOW CRACKED. WINDOW REPLACED AND AIRCRAFT RETURNED IN SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050600019	20020506	00019	EA  	2002	5	6	CA020412006      	1	20020409	G	5610	601R350339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE CAPTAIN'S FRONT WINDSCREEN PLY CRACKED. EMERGENCY DESCENT AND LANDING MADE AT NEAREST AIRPORT AFTER 	CAPTAIN'S WINDSCREEN PLY SHATTERED DURING CRUISE. AIRCRAFT MADE SAFE LANDING. WINDSCREEN REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050600020	20020506	00020	EA  	2002	5	6	CA020412008      	1	20020409	G	2741	70607	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZONTAL STAB	FAILED          	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) "AFTER T/O MACH TRIM & STAB TRIM CAUTION MESSAGES ILLUMINATED. DECLARED EMERGENCY AND LANDED. "PERFORMED OPS CHECK	.  NO  DEFECTS FOUND.  RESET PER FIM AND OPS CHECKED GOOD. RETURNED TO SERVICE.  2ND FLT "AFTER T/O MACH TRIM & STAB TRI	M CAUTION MSGS ILLUMINATED. WOULD NOT RESET. DECLARED EMERGENCY AND LANDED BACK AT TUL. "SENT ROAD CREW FROM CVG.  COULD	 NOT DUPLICATE PROBLEM.  R&R'D HSTCU & MCU AS PRECAUTIONARY MEASURE: FOUND BOTH LEFT & RIGHT HORIZONTAL STAB VISORS CRAC	KED. R&R'D VISORS. ON FERRY FLT BACK AFTER ABOVE MAINT ACTION PROBLEM DID NOT REOCCUR.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050600021	20020506	00021	EA  	2002	5	6	CA020412009      	1	20020409	G	2432		CONNECTOR       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					APU BAT CHARGER	DAMAGED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			13192								(CAN) APU BATTERY CHARGER CONNECTOR P12PA BURNED. REPLACED CONNECTOR PINS, CHARGER AND BATTERY. ALL TESTS SATISFACTORY.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050600022	20020506	00022	EA  	2002	5	6	CA020412010      	1	20020404	G	5730	601R10004	SKIN            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ACCESS HOLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10461								(CAN) CRACKS FOUND ON THE WIND LOWER CENTRE WING PLANK ACCESS HOLE 540FB, BETWEEN WS 127.25 AND 148.19 ACCESS PANEL.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050600023	20020506	00023	EA  	2002	5	6	CA020412011      	1	20020404	G	5320	601R3111357	FLOOR SUPPORT   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND AT LONGITUDINAL FLOOR SUPPORT LT AND RT BL9.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002050600024	20020506	00024	SW  	2002	5	6	CA020412012      	1	20020406	G	6330		BUSHING         	BELL        		BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					STOP MOUNT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TRANSMISSION STOP MOUNT HAS WORN BUSHINGS. REPLACED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050600025	20020506	00025	NM  	2002	5	6	CA020412013      	1	20020408	G	5230		HINGE PIN       	BOEING      	727260      	BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					CARGO DOOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						22759					(CAN) DURING B CHECK INSPECTION, MAIN CARGO DOOR HINGE PIN WAS FOUND MIGRATING AFT APROX. 6 INCHES. HINGE PIN REPOSITION	ED AND SAFETIED.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002051300016	20020513	00016	CE  	2002	5	13	CA020415001      	1	20020408	G	3233	993880081	ACTUATOR        			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					LT MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED BASE AND THE GEAR WOULD NOT RETRACT WHEN THE GEAR HANDLE WAS SELECTED UP.  AIRCRAFT RETURNED TO 	TO BASE.  GEAR ACTUATOR WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002050600026	20020506	00026	NM  	2002	5	6	CA020415002      	1	20020326	G	2910	82950010307	LINE            			DHAV  	DHC8  	DHC8*       	       	NM  										HYD SYSTEM	LEAKING         	W				L				ABORTED APPROACH        				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			28712								(CAN) ON SELECTION OF FLAPS NR 1 HYD PRESSURE CAUTION LIGHT ILLUMINATED AND STANDBY AND  MAIN PRESSURES WENT TO ZERO. FL	APS STOPPED AT 4 DEGREES. RUNWAY LENGTH IN YSB NOT SUFFICIENT DIVERTED TO YYB.					2	H	7	2 	4T			RT	A13NM   					 
2002050600027	20020506	00027	EA  	2002	5	6	CA020416002      	1	20020411	G	2750	C6CT10461	ROD             			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					TE FLAP CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER COMPLETING AD CF-80-03 & SB6/390 THE TRIM ROD WAS BEING ADJUSTED AT INSTALLATION WHEN IT WAS FOUND THAT THE 	FORWARD SWAG WAS ALLOWING THE ROD END FITTING TO ROTATE. THE ROD WAS REPLACED.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002050600028	20020506	00028	CE  	2002	5	6	CA020416003      	1	20020415	G	3340	68417066530	LENS            			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					NAV LIGHT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON WALKAROUND AFTER A FLIGHT A CREW MEMBER NOTICED THE RT NAV LIGHT LENS COVER MISSING. REPLACED WITH NEW AND CONT	INUED FLIGHT TO HOME BASE.					1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2002050600029	20020506	00029	EA  	2002	5	6	CA020416004      	2	20020416	G	7322		FLOAT           			FRCHLD	M62   	M62A3       	3371618	EA  	FCD   	6440  	6440C5      	26003	EA  					CARBURETOR	DAMAGED         	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) AIRCRAFT SUFFERED SIGNIFICANT DAMAGE DUE TO A FORCED LANDING CAUSED BY ENGINE POWER FAILURE.  ENGINE CEASED TO RUN	 DUE TO AN OVER-RICH MIXTURE CONDITION CAUSED BY A CARB. FLOAT WITH A HOLE IN IT.					1	L	7	1 	3I	3	I	 	A724    	E216				 
2002050600030	20020506	00030	CE  	2002	5	6	CA020416005      	1	20020415	G	2440		CONNECTOR       			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					EXTERNAL POWER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOTS REPORTED THAT THEY COULD NOT START EITHER ENGINE USING EXTERNAL POWER BUT ENGINES STARTED FINE USING BATTER	Y POWER. MAIN POWER CABLES AND GROUND CABLE FOUND LOOSE AT GPU CONNECTOR. BOTH THE CONNECTOR STUDS AND THE POWER CABLE E	NDS BURNED AND MELTED.  PARTS REPLACED AS REQUIRED.				1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2002050600031	20020506	00031	EU  	2002	5	6	CA020416006      	1	20020412	G	2750	2F11645	TORQUE TUBE     			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					TE FLAP CONTROL	SHEARED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) THE EMERGENCY FLAP HANDLE FAILED AT 3 DEGREES.  THE TORQUE TUBE WAS FOUND SHEARED AT THE UPPER CRANK ADAPTER FITTI	NG JUST BELOW THE FLOORBOARD.  THE TORQUE TUBE WAS REPLACED AND THE SYSTEM WAS TESTED SERVICEABLE.					2	L	7	2 	3T	4	T	 	A24EU   	A196				 
2002050600032	20020506	00032	EU  	2002	5	6	CA020417002      	1	20020417	G	2434	5243212137	SHAFT           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 GENERATOR	SHEARED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CREW LOST NR 2 GENERATOR IN FLIGHT.  AIRCRAFT RETURNED TO BASE AND THE SHAFT WAS FOUND SHEARED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002050600033	20020506	00033	CE  	2002	5	6	CA020417003      	1	20020401	G	3233	2327100506	ACTUATOR        			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			CA											(CAN) ON GEAR EXTENSION, 3 GREENS, 1 UNSAFE ON RT SIDE.  ON RETRACTION, NO  GREENS LIGHTS, THREE UNSAFE. TWO MORE EXTENS	IONS CARRIED OUT WITH SAME RESULT. GEAR EXTENDED AS PER EMERGENCY CHECK LIST(BLOWN DOWN). GEAR SWING CARRIED OUT ON JACK	S, FOUND RT GEAR ACTUATOR LEAKING INTENALLY, REPLACED ACTUATOR. CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2002050600034	20020506	00034	EA  	2002	5	6	CA020417004      	2	20020312	G	7230	3018389	SPACER          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11300								(CAN) AT ROUTINE ENGINE INSPECTION OF COMPRESSOR FIRST STAGE, FIRST STAGE DISK MADE SCRAPING NOISE AND JAMMED WHEN ROTAT	ED.  VISUAL INSPECTION FOUND FIRST STAGE SPACER HEAVILY RUBBED WITH LEADING EDGE METAL PIECES CURLED OUTWARD FROM INERTI	AL FORCE. ENGINE REMOVED FOR REPAIR.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002050600035	20020506	00035	CE  	2002	5	6	CA020418001      	1	20020416	G	2730	MS276416	BEARING         			LEAR  	45    	45LEAR      	5170805	CE  										ELEVATOR HINGE	SHIFTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRING OUT INSPECTION ON THE ELEVATOR,  FOUND EXCESSIVE PLAY ON RT ELEVATOR.  UPON FUTHER INSPECTION FOUND 	OUTBOARD HINGE BEARING HAD SHIFTED CAUSING ELEVATOR TO BIND.  THIS CAUSED WEAR ON THE CENTER HINGE PICK-UP, PUSH-ROD AND	 DISCONNECT ASSY.				2	L	7	2 	4F			RT	T00008WI					 
2002050600036	20020506	00036	CE  	2002	5	6	CA020418002      	1	20020416	G	5210		BEARING         			LEAR  	45    	45LEAR      	5170805	CE  										DOOR HANDLE BC	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) LOWER DOOR HANDLE BELLCRANK BEARING FOUND NOT SECURED DURING INSPECTION.						2	L	7	2 	4F			RT	T00008WI					 
2002050600037	20020506	00037	NE  	2002	5	6	CA020418003      	2	20020418	G	7261		FILTER          								PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) 2 OIL FILTERS  WERE FOUND INSTALLED IN GEARBOX. FILTERS ARE NOT GENUINE,  NOT APPROVED AND WERE NEVER RELEASED UND	ER THE ENGINE / GEARBOX TYPE DESIGN. THE FILTER SHOWS AN IC NUMBER WHILE IT SHOULD INDICATE THE VENDOR P/N AND THE FILTE	RING CAPACITY. THE SEATING FLANGE DOES NOT MATCH THE ORIGINAL DESIGN SINCE IT IS BUILD FROM 2 ALUMINUM PIECES THAT ARE S	POT WELDED TOGETHER. PWC HAS PLACED THIS PART IN QUARANTINE FOR 21 DAYS.								4	U			E22EA				 
2002091800004	20020918	00004	CE  	2002	9	18	CA020418004      	1	20020408	G	5753	3516505084	RIB             			BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  					RT TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RIB WAS CRACKED AND BROKEN IN THE NOSE AREA AND THE FORWARD ANCHOR NUT FOR THE FLAP ACTUATOR ATTACH BRACKET WA	S BROKEN. WITH THE FLAPS UP THE AME STEPED ON THE FLAP WALKWAY AND A LOUD NOISE WAS HEARD. HE APPLIED UP AND DOWN LOADS 	TO THE FLAP AT THE TRAILING EDGE AND THE ACTUATOR ATTACH BRACKET FORWARD ANCHOR NUT AND A PORTION OF THE RIB PULLED THRO	UGH THE SKIN. THE RIB AND BRACKET WERE REPLACED WITH FACTORY NEW PARTS AND THE SKIN WAS REPAIRED WITH A FLUSH PATCH USIN	G STANDARD SHEET METAL PRACTICES.		1	L	7	2 	3O	3	O	 	3A16    	1E10				 
2002051300017	20020513	00017	NM  	2002	5	13	CA020418005      	1	20020416	G	2432	BACC18W7	CIRCUIT BREAKER 			BOEING	737   	7372A3      	138448A	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					BATTERY CHARGER	OVERHEATED      	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) A/C ON GROUND AND ALL PAX BOARDED WHEN F/A INFORMED CAPTAIN SMOKE COMING FROM FLOOR VENTS AT ROW 1. AT SAME TIME C	REW NOTICED SMOKE ON FLIGHT DECK. STAIRS WERE STILL ATTACHED TO A/C AND DOORS OPEN. CAPTAIN INFORMED F/A TO DEPLANE PAX.	 GROUND SUPPORT, MAINT CONTROL WAS NOTIFIED.  FIRE TRUCKS RESPONDED. MAINT ISOLATED VARIOUS ELECT. SYS EVENTUALLY FINDIN	G CAUSE. NORMAL EQUIP COOLING FAN CCT BREAKER POPPED (FAN OVERHEATING); MEL 21-27-1 ISSD. BATTERY CHARGER CCT BREAKER PO	PPED - BATTERY CHARGER OVER HEATED; UNIT REPLACED. A/C SYSS GROUND CHECKED SERVICEABLE AND A/C RETURNED TO SERVICE WITH 	NO FURTHER INCIDENTS.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002051300018	20020513	00018	CE  	2002	5	13	CA020419001      	1	20020419	G	3242	1338932CHNGD	STATOR          	BFGOODRICH  	215286      	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2899					(CAN) DISASSEMBLED BRAKE UNIT AFTER 488 LANDINGS FOUND 1 STATOR DISC CRACKED ALMOST ALL THE WAY THROUGH, AND 2ND STATOR 	WITH SMALLER CRACKS.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002051300019	20020513	00019	SO  	2002	5	13	CA020422001      	1	20020422	G	3220	NAS464P427	BOLT            	PIPER       	8628003     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	DRAG LINK	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SCHEDULED INSPECTION OF THE AIRCRAFT NOSE LANDING GEAR REVEALED THAT THE DRAG LINK ATTACH BOLT WAS PARTIALLY BACKE	D OUT ON BOTH SIDES. FURTHER INVESTIGATION CONFIRMED THAT THE BOLT HAD SHEARED IN SERVICE AND WAS WORKING ITS WAY OUT.					1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002051300020	20020513	00020	GL  	2002	5	13	CA020422002      	2	20020422	G	7250	23059694	SHAFT           			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					LP TURBINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING INSPECTION OF THE LPT ASSEMBLY IT WAS DISCOVERED THAT THE LPT SHAFT  HAD A SEVERE RUB AND HEAT DISCOLORATI	ON ON THE OUTSIDE DIAMETER, LOCATED IN THE AREA OF THE HPT SLEEVE ALSO RUBBED AT FOUR LOCATION. THE SLEEVE IS ASSEMBLED 	INSIDE THE HPT SHAFT. THIS UNUSUAL CONDITION WAS NOTED FOR THE FIRST TIME AT RRC, THE LP SHAFT IS A CRITICAL PART. NO VI	BRATION WAS REPORTED FROM THE LAST CUSTOMER, ENGINE CAE 330085 IS A LOANER ENGINE. THE LPT SHAFT, HPT SHAFT AND HPT SHAF	T SLEEVE HAVE BEEN RETURNED TO INDIANAPOLIS FOR INVESTIGATION.		2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2002051300021	20020513	00021	CE  	2002	5	13	CA020422003      	1	20020307	G	3211	S21381	BOLT            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE ATTEMPTING TO REMOVE THE LT MLG LEG TO FACILITATE A REPAIR TO AN ADJACENT AREA, IT WAS DETERMINED THAT THE M	AIN ATTACH BOLT WAS SOMEHOW SEPARATED AS INSTALLED THROUGH THE INBOARD SUPPORT AND THE GEAR LEG. EVENTUAL REMOVAL OF THE	 BOLT REVEALED THAT IT HAD BEEN SHEARED AND WAS SOMEWHAT SIEZED BUT ALSO HELD IN PLACE BY THE NATURAL LOAD OF THE GEAR A	S INSTALLED IN THE SUPPORTS. THE AIRCRAFT WAS INSPECTED FURTHER AND NO RELATED DAMAGE WAS FOUND. THE BOLT WAS REPLACED A	ND THE AIRCRAFT WAS RELEASED TO SERVICE. AIRCRAFT TOTAL TIME WAS 15945.7 HOURS WITH NO RECORD FOUND OF PREVIOUS REPLACEM	ENT.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002091800005	20020918	00005	CE  	2002	9	18	CA020422004      	1	20020411	G	5314	1149800227	KEEL            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	FUSELAGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13799	13799							(CAN) DURING INVESTIGATION OF A DC LOAD SHARE PROBLEM BETWEEN BOTH GENERATOR FOUND FOUR WIRES CHAFFED IN THE LT NACELLE 	ON THE OUTBOARD KEEL WEB ASSY. THE DAMMAGE ON THE KEEL WEB WAS DUE TO ELECTRICAL ARCING BETWEEN THE WIRE AND THE KEEL WE	B ASSY. NO PROTECTION WAS FOUND ON THE WIRE BUNDLE AND ON THE KEEL WEB. THE BIGGER WIRE IS  6 GAGE AND TRANSMIT THE CURR	ENT FROM THE LT GEN BUS TO TRIPLE FEED BUS WIRE.  THE THREE OTHER CHAFFED WIRE WAS , AVIONIC BUS WIRE,  THE STBY FUEL PU	MP WIRE,  AND THE FORWARD AIR CONDITIONNING BLOWER WIRE.  IN ALL CASE NO CIRCUIT BREAKER OR CURRENT LIMITTER OPENED.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002051300022	20020513	00022	NM  	2002	5	13	CA020422005      	1	20020418	G	3246	2601913	BOLT            			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SERVICE CHECK, NR 2 MAIN WHEEL TIRE FOUND DEEPLY CUT AND ONE TIE BOLT BROKEN ON MAIN WHEEL HUB ASSY.  NR 2 	MAIN WHEEL ASSY REPLACED PER MM.  MAIN WHEEL ASSY TSO: 472.9 HRS. CSO: 354 CYCLES MAIN WHEEL ASSY TO BE SENT TO OVERHAUL	 FACILITY FOR TEAR DOWN REPORT FOR PROBABLE CAUSE OF BROKEN TIE BOLT.FURTHER REPORTS TO FOLLOW.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002050700111	20020507	00111	NM  	2002	5	7	CA020422006      	1	20020415	G	5523	657378414	STRUCTURE       	BOEING      	657378414   	BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BN126					(CAN) DURING REGULAR SCHEDULED MAINTENANCE INSPECTION (AD:02-01-01)THE RT ELEVATOR FAILED THE TAB HINGE FREEPLAY CHECK A	T THE NR 2 ELEVATOR TAB HINGE POSITION - SUSPECTED CRACK AT ELEVATOR REAR SPAR. EDDY CURRENT INSPECTION CARRIED OUT ON R	T ELEVATOR REAR SPAR - TWO CRACKS DETECTED AT THE OUTBOARD OF HINGE. RT ELEVATOR REPLACED IAW MM.27-313-11, AIRCRAFT RET	URNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002051300023	20020513	00023	EA  	2002	5	13	CA020422007      	2	20020417	G	8520	76786	GEAR            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					CRANKSHAFT	BROKEN          	W				A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN)  DURING CLIMB,  RT ENGINE SUDDENLY LOST POWER AND FEATHERED. CREW RETURNED FOR LANDING. MAINT CREW DISPATCHED AND 	REPLACED ENGINE WITH OVERHAULED ENGINE.  A/C RETURNED TO SERVICE. THE REAR CASE OF FAILED ENGINE REMOVED, CRANKGEAR FOUN	D TO HAVE FAILED. IT APPEARS TO HAVE LOST ONE TOOTH,  WHICH WOULD HAVE MISS TIMED ENGINE, THEN REMAINING TEETH WERE SUBS	EQUENTLY ALL REMOVED, RESULTING IN ALL ACCESSORIES BEING DISCONNECTED FROM CRANKSHAFT. MATING GEARS WERE ALL INTACT AND 	SUSTAINED ONLY VERY MINOR COLLATERAL DAMAGE. ALL OF ACCESSORIES WERE FOUND TO BE SERVICEABLE WHEN REMOVED AND NOT A FACT	OR IN FAILURE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002051300024	20020513	00024	WP  	2002	5	13	CA020422008      	2	20020228	G	7230	31071102	IMPELLER        								GARRTT	TPE331	TPE33111U   	01514	WP  					COMPRESSOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CUSTOMER REPORTED LOUD SQUEALING NOISE COMING FROM ENGINE. ENGINE WAS REMOVED. TEARDOWN REVEALED THAT REWORKED IMP	ELLER HAD A PIECE BROKEN OUT OF ONE VANE.										4	T			E4WE				 
2002051300025	20020513	00025		2002	5	13	CA020423001      	4	20020418	G	6122	F624Z	GOVERNOR        	HARTZL      	HCE3YR2ATF  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA						DJ8047					(CAN) ON TAKE-OFF THE CREW REPORTED THAT THE LT ENGINE EXPERIENCED A POWER LOSS AS NOTED BY A REDUCED MANIFOLD PRESSURE 	AND RPM. VISUAL INSPECTION OF THE ENGINE, FUEL SYSTEM, IGNITION SYSTEM, INDUCTION SYSTEM, AND COMPRESSION CHECK DID NOT 	REVEAL ANY OBVIOUS CAUSE. THE PROBLEM COULD NOT BE DUPLICATED WITH EXTENSIVE GROUND RUNS. THE PROPELLER GOVENOR WAS SUSP	ECT AND WAS REPLACED. THE AIRCRAFT COMPLETED A LOCAL CHECK FLIGHT WITH NO FAULTS AND ALL ENGINE PARAMETERS WITHIN NORMAL	 OPERATING RANGE.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002051300026	20020513	00026		2002	5	13	CA020424001      	4	20020423	G	3422	6226136002	GYRO            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					COCKPIT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ON DEPARTURE GOT YELLOW HEADING FLAG,  WHICH WAS CLEARED,  HAPPENED AGAIN AT TOC,  CLEARED. IN CRUISE GOT RED HEAD	ING ON NR 1 SYSTEM,  SWITCHED TO HDG ALL ON NR 2 REVERSION PANEL.  RETURNED TO YYC.  MAINTENANCE REPLACED THE NR 1 DIREC	TIONAL GYRO,  TESTED THE SYSTEM SERVICABLE AND RETURNED THE AIRCRAFT TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2002051300027	20020513	00027	EU  	2002	5	13	CA020424002      	1	20020321	G	6220	704A33633208	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON POST FLIGHT INSPECTION IT WAS FOUND THAT THE OUTBOARD ENDS OF THE SHPERICAL THRUST BEARINGS HAD BECOME DELAMI	NATED BEYOND SERVICEABLE LIMITS. THIS WAS DETERMINED BY INSERTING A FEELING GAUGE INTO THE VISIBLE CRACK IN THE ELASTOME	R. PARTS WERE REPLACED WITH NEW ONES, NO FURTHER ACTION REQUIRED.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002051300028	20020513	00028	NM  	2002	5	13	CA020424003      	1	20020418	G	2910	82950010303	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			31038								(CAN) DURING SERVICE CHECK HYDRAULIC LEAK FOUND. TRACED TO LINE IN RT WING ROLL SPOILER SYSTEM.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051300029	20020513	00029	NM  	2002	5	13	CA020424004      	1	20020423	G	2913	570717	SHAFT           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD PUMP	SHEARED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			22720								(CAN) NR 1 ENGINE DRIVEN HYDRAULIC PUMP FAILED IN FLIGHT, SHEARING SHAFT ASSEMBLY IN TWO.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051300030	20020513	00030	NM  	2002	5	13	CA020424005      	1	20020416	G	3260	82410306001	CIRCUIT CARD    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			31584								(CAN) AFTER FLIGHT WAS AIRBORNE,  CREW HAD A NOSEGEAR UNSAFE LIGHT IN GEAR SELECTOR HANDLE. GEAR CYCLED, NOSE GEAR LIGHT	 WENT OUT, BUT THEN RT MLG SHOWED DOWN AND LOCKED INDICATION ALTHOUGH GEAR WAS UP.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051300031	20020513	00031	GL  	2002	5	13	CA020425001      	2	20020404	G	7412	6899093	EXCITER         			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				D				RETURN TO BLOCK         				H	L		ELECT. POWER LOSS-50 PC   	NO TEST                   		TX	TAXI/GRND HDL  	1			CA											(CAN) NO LIGHT OFF DUE TO FAULTY PART.  CAN CAUSE A REAL PROBLEM IN REMOTE AREA.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002051300032	20020513	00032	CE  	2002	5	13	CA020425003      	1	20020404	G	5540	05310081	RUDDER HORN     			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	TAIL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13329								(CAN) DURING ROUTINE INSPECTION THE RUDDER HORN ASSY AT THE AREA WERE THE HORN STRIKES THE RUDDER STOPS HAD BEEN DAMAGED	.  WE BELIEVE BY GUSTY WINDS WITHOUT THE RUDDER LOCK ON. THE RUDDER STOP SCREW HAD ACTUALLY ROLLED THE ALUMINIUM BACK ON	 THE HORN WHICH MADE FOR A HAZARDOUS SITUATION DUE TO THE FACT THAT THE STOP SCREW COULD HAVE JAMED OVER THE ROLLED ALUM	.THE RUDDER HORN AND RIB ASSY. HAVE BEEN REPLACED WITH NEW UNITS. NO DAMAGE WAS FOUNDS IN THE STOP ATTACHEMENT AREA.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002051300033	20020513	00033	NM  	2002	5	13	CA020425004      	1	20020424	G	2910	82950010273	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FLUID LEAK NOTED FROM LT WHEEL WELL UPON ARRIVAL. TRACED TO LT LIFT DUMP PRESSURE LINE CRACKED AT RADIUS.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051300034	20020513	00034	NM  	2002	5	13	CA020425005      	1	20020404	G	5230		LINK            			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CARGO DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28011								(CAN) CARGO DOOR WILL NOT CLOSE. HANDLE LINK ASSEMBLY DISCOVERED BROKEN.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051300035	20020513	00035	NE  	2002	5	13	CA020425006      	2	20020401	G	7530	MS274081N	SWITCH          			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	HBOV BLEED	BENT            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) OVER TORQUE ON LT ENGINE WITH BLEEDS SELECTED ON.  SUSPECT LEFT BLEED SELECTED TO HBOV FOR TAKEOFF. LT BLEED SWITC	H BENT AND NOT STOPPING AT DETENT. OVERTORQUE FOR APPROX.  ONE SECOND. SWITCH REPLACED AND FDR READOUT WITHIN LIMITS.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051300036	20020513	00036	NE  	2002	5	13	CA020425008      	2	20020330	G	7200		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2	FAILED          	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			CA			27969	15774							(CAN) ON TAKEOFF ROLE AS POWER WAS APPLIED, NOISE HEARD FROM NR 2 ENGINE. TORQUE ROLLBACK TO 50 PERCENT AND ENGINE VIBRA	TION. ENGINE SHUTDOWN DUE TO INTERNAL FAILURE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051300037	20020513	00037	EU  	2002	5	13	CA020426001      	1	20020422	G	7933		INDICATOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENG OIL TEMP	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT,  PILOTS NOTICED QUICK RISE OF OIL TEMP, POWER WAS THEN REDUCED WHICH LOWERED THE OIL TEMP SHORTL	Y AFTER, NEW RISE IN OIL TEMP (LIMITS EXCEEDED), RISE AND FALL OF OIL PRESSURE (WITHIN LIMITS). PILOTS DECLARED EMERGENC	Y AND LANDED SAFELY. AFTER TROUBLESHOOTING, PROBLEM FOUND TO BE IN THE INDICATION SYSTEM. CONTACTS CLEANED AT THE FIREWA	LL CONNECTOR AND CONNECTOR SECURED. ENGINE STARTED TO VERIFY PROPER OPERATION OF THE INDICATION SYSTEM. DURING START, UN	COMMANDED ACCELERATION OCCURED. DATA RETRIEVED FROM ECTM PROCESSOR REVEALED NO LIMITS EXCEEDED. FCU REPLACED. ENGINE OPE	RATE NORMALLY.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002051300082	20020513	00082	NE  	2002	5	13	CA020426003      	2	20020424	G	7261	626447	REGULATOR VALVE 			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					NR 1 ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) NR 1 ENGINE OIL PRESS RED LINED DURING T/O CLIMB.  THROTTLE RETARDED TO IDLE, OIL PRESS BELOW RED LINE.  A/C RETUR	NED TO BASE.OIL PRESS RELIEF/REGULATING VALVE REPLACED. ( O-RING FOUND DAMAGED,  COMPLETE ASSY REPLACED)					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002051300083	20020513	00083	NM  	2002	5	13	CA020426004      	1	20020403	G	3520	119001302	LATCH           			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D17      	52049	NE  					OXYGEN SYSTEM	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) CABIN OXYGEN PSUS NR 9 RT AND NR 14 RT, NO FLOW FOUND DURING FUNCTIONAL TEST. BOTH UNITS ARE FROM THE SAME BATCH N	R. BATCH NR 99795 REPLACED LATCH ASEMBLIES.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002051300085	20020513	00085	WP  	2002	5	13	CA020426005      	1	20020420	G	7110	NAS1335S3S09	PIN             		1607740115  	LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					GLOVE FAIRING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING WALK AROUND , FOUND NR 3 ENGINE GLOVE FAIRING ADRIFT. GLOVE FAIRING FOUND RETAINED BY TWO LANYARD AND PIP P	IN NOT IN PLACE FOR SECURITY. THE PIN WAS FOUND CORRODED AND THE PIN LOCKING MECHANISM WAS JAMMED DUE TO CORROSION. .IT 	WAS NOT POSSIBLE TO USE THE PIN FOR LOCKING THE GLOVE FAIRING IN PLACE. THE AIRCRAFT WAS RELEASED UNDER CDL 54-51. THE P	IN WAS LATER REPLACED.			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002051300087	20020513	00087	NM  	2002	5	13	CA020426006      	1	20020420	G	2120		SMOKE           			BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					COCKPIT	DETECTED        	W				O				OTHER                   				R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) CROSSING TOP THURDERSTORM, APPLIED MAX CONTINUOUS FOR 30 SEC. SPEED DROP TO M.72 AT FL 360.  SMELL OF OIL BURNED F	OR 3 MINS ALL PARAMETERS NORMAL ACTION TAKEN LMWS 51130 ITEM 1,2 BVCU BITE CHECK, MCD'S INSPECTED ON BOTH ENGINE.  BOTH 	ENGINE TEST C/O AS PER MM 71-00-00 TEST 6 VIBRATION SURVEY, TEST II, ACC/DLC, TEST 13 T/O POWER BOTH ENGINE GENERAL EXTE	RNAL INSPECTION C/O CHECK SERVICEABLE RII C/O BY TA114. THE DFDR WAS SENT, WAS REPLACED AND SENT FOR ANALYSIS. WAITING F	OR RESULTS.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2002051300089	20020513	00089	CE  	2002	5	13	CA020429001      	1	20020423	G	5524		BRACKET         			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					ELEVATOR HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLIED WITH CESSNA CUSTOMER LETTER NO 0423 DATED APRIL 23, 02.  (INSPECTION OF LT AND RT ELEVATOR INBD HINGE BRA	CKETS) ONE BRACKET HAS TWO SURFACES: INBD AND OUTB.FOUND LEFT ELEVATOR INBD HINGE BRACKET CRACKED. INBD CRACK DIMENSION 	:. 062 INCH OUTB CRACK DIMENSION : .125 INCH,   RT ELEVATOR INBD HINGE BRACKET CRACKED. INBDNONE OUTB CRACK DIMENSION: .	180 INCH. ACTION: RE-INSPECT IN 100 HRS			2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2002051300092	20020513	00092	NM  	2002	5	13	CA020429002      	1	20020426	G	3246	2601913	TIE BOLT        			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MAIN WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AIRCRAFT SERVICE CHECK FOUND NR 3 MAIN WHEEL ASSEMBLY WITH ONE SHEARED TIE BOLT NR 3 MAIN WHEEL ASSEMBLY. R	EPLACED IAW MM 32-45-1.  MAIN WHEEL ASSEMBLY TO BE SENT TO OVERHAUL FACILITY FOR INVESTIGATION AND TEAR DOWN REPORT.  FU	RTHER REPORT(S) TO FOLLOW.  PROCEDURES FOR REPLACEMENT OF ALL TIE BOLTS WITH NEW AT OVERHAUL AND TRACKING OF THESE BOLTS	 IS UNDER REVIEW AT THIS TIME.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2002051300097	20020513	00097	NM  	2002	5	13	CA020429003      	1	20020429	G	2150		A/C PACK        			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AIR CON SYS	SMOKE           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKOFF, F/A NOTIFIED CREW BOTH SMOKE DETECTORS HAD ACTIVATED AND THERE WAS A SMELL OF SMOKE IN THE C	ABIN. AIRCRAFT IMMEDIATELY RETURNED TO YYC AND DID AN OVERWEIGHT LANDING - MAINTENANCE INSPECTION FOUND CAUSE OF ODOUR F	RON LEFT HAND AIR CONDITIONING PACK - SYSTEM DECONTAMINATED IAW MM. 21-00-01. AIR CONDITIONING SYSTEM GROUND CHECKED SER	VICEABLE - AIRCRAFT RETUNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002051300103	20020513	00103	WP  	2002	5	13	CA020429004      	1	20020419	G	3233	1535927111	ACTUATOR        			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					MLG	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) WHEN LOWERING THE LANDING GEAR CONTROL LEVER A LOUD BAG WAS HEARD, LT GEAR CONFIRMED DOWN AND LOCK WITH THE OVERWI	NG GEAR POP-UP INDICATOR AND AIRCRAFT LANDED SAFELY.  UPON INVESTIGATION ON THE GROUND, THE F/E REPORTED A COMPLETE FRAC	TURE OF THE LT MLG RETRACT ACTUATOR AND A BROKEN JURY BRACE.  GEAR DOOR FOUND DAMAGED ALSO AND WAS REPLACED, GEAR SWING 	PERFORM AND AIRCRAFT SERVICEABLE. THE DAMAGED PARTS WERE SENT TO LOCKHEED FOR ANALYSIS.			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002051300105	20020513	00105	EA  	2002	5	13	CA020430001      	2	20020421	G	7310	500991	FUEL FILTER     			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A6       	52043	EA  	HARTZL	HCB5M	HCB5MA3     	GL  	FIREWALL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WHILE DE-INHIBITING ENGINE FCU,  FUEL FOUND LEAKING FROM FIREWALL MOUNTED FUEL FILTER AT BASE OF CANISTER O-RING. 	 FILTER CANISTER REMOVED, NEW FILTER ELEMENT AND O-RING WERE INSTALLED, FILTER ASSY TORQUED IAW AT-802 MM AND PRESSURE T	ESTED SERVICEABLE.  A/C GROUND RUN FOR APPROX 2 HRS OVER ONE WEEK PERIOD. DURING TEST FLT PILOT NOTED FUEL SMELL IN COCK	PIT. A/C RETURNED TO BASE. FUEL PRESSURE CHECK ACCOMPLISHED AND FUEL FOUND LEAKING FROM CANISTER TO BASE O-RING LOCATION	.  FILTER CANISTER SECURING BOLT LOCK WIRE REMOVED AND TORQUE CHECK WAS COMPLETED.		1	L	7	1 	3T	3	T	NC	A19SW   	E4EA	6	C	P44GL	 
2002051300107	20020513	00107	EA  	2002	5	13	CA020430002      	2	20020408	G	8530	LW16740	EXHAUST VALVE   			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NR 6 CYLINDER	SEPARATED       	W				E				ENGINE SHUTDOWN         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		AP	APPROACH       	1			CA											(CAN) UPON FINAL THE PILOT NOTICED THE RT ENGINE STARTED TO RUN ROUGH & MAP CLIMB WITH A CHT DECREASE. WHEN THE POWER WA	S REDUCED TO IDLE AT LANDING THE ENGINE STOPPED.  THE PILOT RESTARTED THE ENGINE & TAXIED IN, BUT NOTICED THE RT ENGINE 	TO BE RUNNING ROUGH. UPON INSPECTION THE NR 6 CYLINDER EXHAUST VALVE WAS MISSING. DAMAGE TO THE PISTON AND CYLINDER HEAD	 HAD OCCURRED. THE ENGINE WAS REMOVED FOR OVERHAUL.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002051300108	20020513	00108	CE  	2002	5	13	CA020430003      	1	20020410	G	5712	07221981	RIB             			CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	D3A34	D3A34C401   	GL  	RT WING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT WING  STA 172.00 - DURING INSTALATION OF AUXILIARY WING TANKS, AN INSPECTION ACCESS HOLE WAS CUT IN LOWER RING 	SKIN AT STA. 169.00 SURVEILLANCE INSPECTON OF THE WING RIB AT STA 172.00 REVEALED AN EXTENSIVE COMPRESSION FAILURE ALONG	 THE ENTIRE LENGTH OF PART UPPER RETURN FLANGE & WEB SECTION.- THERE WERE NO VISIBLE SIGNS OF EXTERNAL DAMAGE TO WING UP	PER OR LOWER SKIN.			1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P47GL	 
2002051300109	20020513	00109	WP  	2002	5	13	CA020430004      	1	20020318	G	6720	369H75319	TORQUE TUBE     		369A7500501 	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					T/R PEDAL	CRACKED         	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) -PILOT NOTICED LOSS OF T/R AUTHORITY WITH A SPONGY FEEL JUST AS HE WAS PULLING INTO A HOVER. HELICOPTER WAS LANDED	 AND SHUTDOWN.- T/R PEDAL ASSEMBLY WAS FOUND CRACKED ALMOST 360 DEGREES.- CRACK ORIGINATED FROM UNDER 369A7511 FITTING W	HERE THE ATTACH HOLE IS LOCATED.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002051300110	20020513	00110	WP  	2002	5	13	CA020430005      	1	20020222	G	6310	369D25351	SPRAG CLUTCH    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON THE 300 HOUR INSPECTION OF THE SPRAG ASSEMBLY IT WAS FOUND THAT ONE OF THE SPRAGS WAS BROKEN. THE BREAK WAS A	T THE FAR END OF THE SPRAG WHERE THE PROFILE CHANGES.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002051400001	20020514	00001	CE  	2002	5	14	CA020430006      	1	20020328	G	2435		BEARING         	LUCAS       	6608458005  	LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					STARTER GEN	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						991168					(CAN) BEARINGS ROUGH AND NOISY.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2002051400002	20020514	00002	SW  	2002	5	14	CA020430007      	1	20020410	G	2435		SHAFT           		23032018    	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					STARTER GEN	WORN            	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA						11754					(CAN) GENERATOR FAILED. GENERATOR INSPECTED, FOUND AFT SHAFT WORN.THIS PORTION OF SHAFT ENGAGES TO THE COMMUTATOR.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050700112	20020507	00112	GL  	2002	5	7	CA020430008      	2	20020410	G	7323	206062708007	TORQUE TUBE     	BENDIX      	23065121    	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						17314					(CAN) THE TORQUE TUBE P/N 206-062-708-007 WAS FOUND CRACKED IN THE SHEAR AREA. THE CAUSE OF THE CRACKS WERE DETERMINED T	O BE CAUSED BY THE GOVERNOR BECAUSE THE ARM WAS EXTREMELY HARD TO MOVE. NO COMPLAINTS FROM PILOT TO INDICATE A N2 PROBLE	M. BOTH PARTS REPLACED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002051400003	20020514	00003	NE  	2002	5	14	CA020430009      	2	20020410	G	7321	7257255	FUEL CONTROL    			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) AT 3.9 HOURS AFTER ENGINE INSTALLATION THE ENGINE PARTIALLY DECELERATED IN FLIGHT. THE ENGINE RESPONDED TO EMERGEN	CY THROTTLE AND WAS LANDED SAFELY. FUEL CONTROL WAS REPLACED.					2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2002051400004	20020514	00004	EA  	2002	5	14	CA020430010      	1	20020326	G	3246	901230602	FITTING         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					MLG FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION AND STRESS CRACK DEVELOPED ON TAPER HOLE OF THE SPREADER ATTACH FITTING RT FLOAT TOWARD SPREADER ATTCH P	/N 901-23060-2 WAS REMOVED AND QUARANTINED. REPLACEMENT PART SI 901-23060-2 WAS INSTALLED AS PER STC SF-97-2.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002050700113	20020507	00113	SW  	2002	5	7	CA020430011      	1	20020327	G	6320	214040118001	BEARING         	BELL        	212040263107	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR G/B	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						A124					(CAN) INFLIGHT ILLUMINATION OF TRANSMISSION OIL PRESSURE LIGHT, CONFIRMED BY VISUAL INDICATION OF LOW OIL PRESSURE INDIC	ATION (40PSI). EMERGENCY PROCEDURES INITIATED, PRESSURE INDICATION WENT TO ZERO AFTER A FURTHER 6 MINS OF FLIGHT. EMERGE	NCY LANDING CARRIED OUT TO NEARBY SEA VESSEL. TRANSMISSION/DRIVE TRAIN SEIZED FOLLOWING ENGINE SHUT DOWN AND APPLICATION	 OF ROTOR BRAKE. TEARDOWN INSPECTION OF TRANSMISSION 26-APR-02 AT HELIPRO FACILITY IN LANGLEY BC IDENTIFIED FAILURE OF Q	UILL ASSY AND QTY.2 LOWER PLANETARY GEAR BEARING WHICH WERE SEIZED.		1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002051400005	20020514	00005	EU  	2002	5	14	CA020430012      	1	20020425	G	2612	3001230117530014	FIRE LOOP       			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					RT ENGINE	INTERMITTENT    	W				F	E			ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         			N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) WHILE ON DESCENT CREW HAD FIRE INDICATION RT ENGINE. EMERGENCY PROCEDURES INITIATED WHERE BOTH FIRE BOTTLES WERE B	LOWN TO EXTINGUISH POSSIBLE FIRE AND ENGINE SHUT DOWN. LIGHT WENT OUT. LANDED WITH CRASH TRUCKS STANDING BY UNEVENTFULL.	 DURING TAXI IN, LIGHT CAME BACK ON, CREW SHUT DOWN AND EVACUATED AIRCRAFT. INSPECTION REVEALED NO FIRE. TROUBLESHOOTING	 FOUND FIRE LOOP INTERMITTENT. NEW LOOP ORDERED AND INSTALLED.			2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2002051400006	20020514	00006	EU  	2002	5	14	CA020430013      	1	20020401	G	5210		HANDLE          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PAX DOOR	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING CLOSING OF DOOR THE HANDLE BROKE IN HALF.THIS IS THE 3RD ONE BROKEN.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002073100111	20020731	00111	EU  	2002	7	31	CA020501001      	1	20020409	G	5210	SWF653150214P3H	STRUT           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					PAX DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GAS STRUTS FAIL TO HOLD DOOR OPEN.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002073100112	20020731	00112	SW  	2002	7	31	CA020501002      	1	20020411	G	6330	2090313441	FITTING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					M/R TRANSMISSION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND AT BOTTOM OF BEAM (FITTING HOUSING) WHERE 5TH MOUNT IS HOUSED, 3/4 INCH LONG.  BELL MAINTENANCE MANUAL	 SPECIFIES NO CRACKS IN THIS AREA.					1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002051400007	20020514	00007	EU  	2002	5	14	CA020501003      	1	20020417	G	7931	1103P0954	SWITCH          			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					OIL PRESSURE	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) ON SHUTDOWN,  LT ENGINE LOW OIL PRESSURE ANNUNCIATOR LIGHT DID NOT COME ON. INDICATOR LIGHT TEST FOUND SERVICEABLE	. PRESSURE CHECKING OF SWITCH WITH NITROGEN FOUND ANNUNCIATOR COMING ON AT 60 PSI AND OFF AT 51 PSI AS MARKED ON SWITCH.	 SWITCH ASSY REINSTALLED AND GROUND RUN FUCNTION. LEAK CHECKED SERVICEABLE. NEW SWITCH ORDERED FOR ANY RECURRANCE (279.3	 HRS & 142 CYCLES).8 FLTS LATER, THE RT ENGINE LOW OIL PRESSURE LIGHT DID NOT COME ON WHEN ENGINE SHUTDOWN. INDICATOR LI	GHTS TEST WORKED OKAY. RT LOW OIL PRESSURE SWITCH REPLACED WITH NEW (297.0 HRS & 150 CYCLES). FUNCTION AND LEAK CHECKED 	SERVICEABLE.	2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2002050700114	20020507	00114	WP  	2002	5	7	CA020501009      	1	20020413	G	5610		WINDSHIELD      	SIERRACIN   	1634896101  	LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA						3923LR					(CAN) CAPTAIN WINDSHIELD HAD MAJOR DELAMINATION IN FLIGHT . THE CREW PROCEDURES WERE CARRIED OUT BY PULLING THE CIRCUIT 	BREAKER TO DEACTIVATE THE WINDSHIELD HEAT SYSTEM. MAINTENANCE REPLACED THE WINDSHIELD AND ALSO REPLACED THEWINDSHIELD HE	AT CONTROL UNIT.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002051400008	20020514	00008	CE  	2002	5	14	CA020501011      	1	20020220	G	5542	04330106	SKIN            	CESSNA      	043301015   	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKIN CRACKED AT UPPER LIGHTNING HOLE.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002051400009	20020514	00009	EA  	2002	5	14	CA020501013      	2	20020401	G	7414	M3100	IMPULSE COUPLING		4372        	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						97020756					(CAN) AS A RESULT OF 2 RECENT CATASTROPHIC MAGNETO IMPULSE COUPLING FAILURES ON OTHER AIRCRAFT IN OUR FLEET THAT RESULTE	D IN ENGINES BEING REPLACED, THIS MAGNETO WAS REMOVED AND INSPECTED FOR CONDITION OF THE IMPULSE COUPLING. ONE OF THE TW	O PAWLS AND IT'S ATTACHMENT RIVET WAS FOUND TO BE EXTREMELY LOOSE AND HAD WORN THE PAWL MOUNTING BACKING PLATE AT THE RI	VET ATTACHMENT AREA. A NEW IMPULSE COUPLING WAS INSTALLED AND THE MAGNETO RETURNED TO SERVICE.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002051400010	20020514	00010	EA  	2002	5	14	CA020501014      	2	20020328	G	7414	M3100	IMPULSE COUPLING			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	BROKEN          	W				D				RETURN TO BLOCK         				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING AN ENGINE START, AN UNUSUAL NOISE WAS HEARD COMING FROM THE ENGINE. INVESTIGATION BY MAINTENANCE PERSONNEL 	REVEALED THAT THE LT MAGNETO HAD FAILED AND THAT IT'S IMPULSE COUPLING HAD COME APART. THE PARTS MISSING FROM THE IMPULS	E COUPLING ENTERED INTO THE ENGINE AND CAUSED CONSIDERABLE DAMAGE TO THE MAGNETO AND ENGINE. THE ENGINE HAD TO BE REPLAC	ED AS A RESULT OF THE DAMAGE AND RESULTING OIL SYSTEM CONTAMINATION. THE FAILED IMPULSE COUPLING HAD 882.0 HOURS TIME SI	NCE NEW. NO DEFECTS WERE NOTED DURING THE LAST 500 HOUR INTERNAL INSPECTION  (SLICK SB 2-80C) COMPLETED 389.7 HOURS PREV	IOUS TO FAILURE.	1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002051400011	20020514	00011	NE  	2002	5	14	CA020501015      	2	20020419	G	7310	LK30233	LINE            			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					FUEL SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								41123			(CAN) WHILE THE AIRCRAFT WAS IN FOR AN ENGINE CHANGE , FOUND ON NR 1 ENGINE , THAT THE FUEL TUBE ASSY LINE DISCONNECT TO	 HP PUMP WAS DENTED. ONCE REMOVED, FOR REPLACEMENT , NOTICED THAT THE FERRULE, THE FERRULE SEAL CARRIERS WERE WORN AND P	ITTED AND ALSO THE CONNECTOR HAD 2 GROOVES AND WERE ALSO PITTED.				1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002051400012	20020514	00012	NM  	2002	5	14	CA020502001      	1	20020430	G	2821	3038454	FILTER          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUEL SYSTEM	CONTAMINATED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) APPROX 1/2 HR INTO FLT, FLT CREW NOTICED "IMPENDING FUEL BYPASS" WARNING LIGHT ILLUMINATED ON RT ENGINE. A/C RETUR	NED TO MAINT BASE. INSPECTION OF LOW PRESSURE FILTER REVEALED CONTAMINATION OF SMALL PARTICLES OF PRC & HARDENED SEALANT	. THESE ORIGINATED FROM FUEL TANK ACCESS PANELS. INSP OF HIGH PRESSURE FILTER SHOWED NO SIGNS OF CONTAMINATION. A/C HAD 	RECENTLY UNDERGONE MAINT IN FUEL TANKS. FUEL TANKS WERE CLEANED PRIOR TO CLOSING OF THE  TANK PANELS. FUEL FILTER ON LT 	ENGINE CHANGED AS PRECAUTIONARY MEASURE: CONTAMINATION OBSERVED ON LOW PRESSURE FILTER TO LESSER DEG. FILTERS WERE WELL 	WITHIN ALLOWABLE TIME IN SERVICE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002051400013	20020514	00013	NE  	2002	5	14	CA020502002      	3	20020502	G	6111	SFA13SIOA1	BLADE           			CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A DAILY INSPECTION, A CRACK ON A PROP BLADE APPROX 5 LONG, NO REPORT FROM THE PILOT AND NO SIGN OF IMPACT W	AS FOUND DURING THE VISUAL INSPECTION. IT WAS REPORTED THAT A FEW DAYS BEFORE PAINT STARTED PEELING OFF FROM THAT BLADE 	AND KEPT PROGRESSING EACH DAY UNTIL A CRACK WAS FOUND.  FURTHER INVESTIGATION REVEAL AFTER TAB TEST INSPECTION SOME DELA	MINATION AROUND THE CRACK.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2002051400014	20020514	00014	CE  	2002	5	14	CA020502003      	1	20020407	G	7120		TUBE            			BEECH 	18    	3TM         	1151046	CE  	PWA   	R985  	R985AN14B   	52008	NE  					MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15292								(CAN) DURING INITIAL INSPECTION OF AIRCRAFT COMPLETED AD CF-63-08 WAS INSPECTED AND FOUND TO BE BROKEN AS ATTACHED INDIC	ATES. FURTHER INVESTIGATION SHOWED THAT A PREVIOUS CRACK HAD JUST BEEN WELDED SHUT. THIS CRACK WELDED HAD CRACKED AGAIN 	AND GONE UNNOTICED.				1	L	7	2 	3R	3	R	 	A765    	5E1				 
2002051400015	20020514	00015		2002	5	14	CA020502004      	4	20020427	G	8300		FITTING         			BOEING	737   	737297      	1384480	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 1 ENGINE G/B	MISSING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	Y	K	WARNING INDICATION        	ENGINE STOPPAGE           	FLUID LOSS                	CR	CRUISE         	1			CA											(CAN) ENROUTE PILOT NOTICED THE OIL QUANTITY WAS AT ZERO ON THE NR 1 ENGINE - BOTH OIL PRESSURE AND OIL TEMPERATURE WERE	 NORMAL. SHORTLY THERE AFTER THE OIL PRESSURE STARTED TO FLUCTUATE AND THE OIL PRESSURE WARNING LIGHT ILLUMINATED.FLIGHT	 CREW SHUTDOWN NR 1 ENGINE. AIRCRAFT DIVERTED AND PERFORMED AN ABNORMAL LANDING - AIRCRAFT LANDED WITHOUT INCIDENT. MAIN	TENANCE INSPECTION REVEALED THE BANJO FITTING BLOWN OUT FROM THE GEARBOX CAUSING THE OIL LEAK.MAINTENANCE REPLACED THE G	EARBOX, GROUND CHECKED THE ENGINE AS SERVICEABLE - NO LEAKS TO REPORT.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCID	ENTS TO REPORT.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002051400016	20020514	00016	EA  	2002	5	14	CA020502005      	2	20020405	G	7414	M3100	IMPULSE COUPLING		4372        	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	FAILED          	W				D				RETURN TO BLOCK         				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA						96010043					(CAN) THE LT MAGNETO FAILED DURING ENGINE START UP. MAGNETO IMPULSE COUPLING HAD COME APART AND LOOSE PIECES FROM COUPLI	NG CAUSED MAJOR DAMAGE TO MAGNETO AND ENGINE. ENGINE REPLACED AND A/C RETURNED TO SERVICE.					1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002050700116	20020507	00116	EA  	2002	5	7	CA020502007      	1	20020411	G	4990	49100011	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU BAY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) AIR TURN BACK, AIRCRAFT CABIN FILLED WITH SMOKE, RETURN TO ST-LOUIS.  AIRCRAFT DEPARTED WITH THE APU UNDER MEL DUE	 TO LOW OIL QUANTITY & APU SHUTDOWN (APU FAILURE) OIL FROM THE APU WENT IN THE LT PACK CAUSING THE SMOKE.  REPLACED THE 	APU AND THE PACK.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002051400017	20020514	00017	EA  	2002	5	14	CA020502008      	1	20020413	G	2750	1104SD1002011	CONTROL CABLE   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT TE FLAP ACT	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) FLAPS FAIL MESSAGE ON EICAS AFTER TAKEOFF WITH FLAPS SELECTED AT 8, AIR TURN BACK. REPLACED FLEX CABLE ACTUATOR BE	TWEEN NR 1 AND 2 ACTUATORS ON THE LT SIDE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002051400018	20020514	00018	NM  	2002	5	14	CA020502012      	1	20020323	G	2780	285T004953	CONTROL UNIT    			BOEING	767   	767383      	1385214	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					LE SLATS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) FLAP DISAGREE MESSAGE ON EICAS WHEN FLAP SELECTED TO RETRACT FROM 5 DEGREE TO 1 DEGREE ON TAKEOFF. ALTERNATE TE FL	AP EXTENSION USED FOR LANDING. FOUND TO BE THE FSEU AT FAULT (FLAP SLAT CONTROL UNIT). REPLACED ELECT FLAP SLAT UNIT.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2002051400019	20020514	00019		2002	5	14	CA020502014      	4	20020417	G	2200	285T0015116	ASYMMETRY SWITCH			BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					AUTOFLIGHT SYS	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AT 400 FEET AFTER TAKEOFF CREW REPORTED AN AILERON LOCKOUT MESSAGE, RUDDER RATIO MESSAGE AND NONE OF THE 3 AUTOPIL	OTS COULD BE ENGAGED. AIRCRAFT RETURNED TO AIRPORT.BOTH LT AND RT STABILIZER TRIM/ELEVATOR ASYMMETRY MODULES (SAM) REPLA	CED AS PER AMM 27-09-00.SYSTEM TESTED SERVICEABLE.CHECK FLIGHT CARRIED OUT AND NO FAULT FOUND.				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2002051400020	20020514	00020	NM  	2002	5	14	CA020502018      	1	20020404	G	5610	58935722	WINDOW          			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON GROUND FOUND FIRST OFFICER NR 4 WINDOW SHATTERED. RELACED NR 4 WINDOW.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002050700121	20020507	00121	NM  	2002	5	7	CA020502019      	1	20020401	G	3150	285T03855	MODULE          			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					AURAL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) REJECTED TAKEOFF AT 120 KNOTS DUE TO CONFIGURATION WARNING (FIRE WARNING BELL).  NO OTHER INDICATIONS OF ANY FAULT	S, FOUND TO BE THE AURAL WARNING BELL/CHIME MODULE AT FAULT. REPLACED THE AURAL WARNING BELL/CHIME MODULE.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2002051400021	20020514	00021	EA  	2002	5	14	CA020502023      	1	20020502	G	2820	CC670622581	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF34*       	 	NE  					FUEL SENSE	LEAKING         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL330, BOTH FUEL PUMPS ON- INTERMITTENTLY AT FIRST, AND THEN PERMANENTLY. RT MAIN EJECTOR FLICKER	ING YELLOW ON SYNMOPTIC PAGE. FUEL BALANCE REMAINED OK BUT 65-70 KG IN CENTRE TANK.  CENTRE TANK WAS ACCESSED AND THE SE	NSE LINE FROM RT MAIN EJECTOR TO LP SWITCH FOUND TO HAVE BROKEN AT THE FERRULE (AT PRESSURE SWITCH END OF PIPE), ALLOWIN	G FUEL TO LEAK FROM THE EJECTOR INTO THE CENTRE TANK. REPLACEMENT PIPE WAS FITTED AND THE AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002051400023	20020514	00023	EA  	2002	5	14	CA020502025      	1	20020426	G	2820	CC670622581	LINE            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF34*       	 	NE  					FUEL SENSE	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) WHILE ON DESCENT, THE R MAIN EJECTOR CAUTION MESSAGE BECAME APPARENT TO THE CREW. AT THE POINT OF SHUTDOWN, THERE 	WAS 80 LBS OF FUEL IN THE CENTRE TANK.MAINTENANCE FOUND THE RT MAIN EJECTOR PRESSURE SWITCH SENSE LINE (CC670-62258-1) T	O BE BROKEN JUST AT THE FERRULE GOING INTO THE "B" NUT. AFTER OBTAINING THE APPROPRIATE AUTHORIZATION, THE AIRCRAFT WAS 	FERRIED FOR INSTALLATIION OF A REPLACEMENT PART.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002051400024	20020514	00024	EA  	2002	5	14	CA020502026      	1	20020428	G	5610	NP1393215	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT'S SIDE WINDOW CRACKED IN FLIGHT.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002051400025	20020514	00025	CE  	2002	5	14	CA020502027      	1	20020429	G	2720	666000178	SERVO           			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					RUDDER	MALFUNCTIONED   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING A PHASE INSPECTION, THE AUTO-PILOT SERVO CABLE AND THE SECONDARY RUDDER CABLE WERE FOUND CROSSING EACH OTHE	R BETWEEN THE LOWER AFT RUDDER SECTOR AND PULLEYS AT THE 63 PERCENT VERTICAL SPAR IN ZONE 340.THE AUTO-PILOT SERVO CABLE	 HAS BEEN RE-ROUTED AS PER MAINTENANCE MANUAL.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2002051400026	20020514	00026	SO  	2002	5	14	CA020503002      	1	20020403	G	5751	3564016	DOUBLER         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	3D36C	B3D36C424   	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN UNSCHEDULED MAINTENANCE EVENT (AILERON ADJUSTMENT), WE DISCOERED THAT THE LT AILERON OUTBOARD DOUBLER WA	S CRACKED ON THE INBOARD TOP CORNER. THE CRACK WAS 1 INCH LONG.					1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P58GL	 
2002061200008	20020612	00008	SO  	2002	6	12	CA020503003      	1	20020326	G	7810	MVT69183200	COUPLING        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	MCAULY	3DF36C	B3DF36C526  	GL  	EXHAUST PIPE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TOUBLESHOOTING OF HIGHER THAN NORMAL E.G.T. INDICATION, (CAUSED BY MAGNETO), THE RT EXHAUST PIPE COUPLING A	T THE TRANSITION WAS FOUND LOOSE. COUPLING P/N MVT69183-200 WAS REMOVED FOR DETAILED INSPECTION, A CRACK APPROXIMATELY 1	.5 INCHES LONG WAS DETECTED IN THE LOWER FLAT SURFACE OF THE MIDDLE SEGMENT.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	 	 
2002051400027	20020514	00027	CE  	2002	5	14	CA020503004      	1	20020409	G	5320	04102362	STIFFENER       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11095								(CAN) PART FAILED IN THE CUT-OUT OF THE LOAD-BEARING MEMBER.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002061200009	20020612	00009	EA  	2002	6	12	CA020503005      	2	20020411	G	8520	LW13820	CRANKCASE       			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A 50 HOUR INSPECTION, AN OIL LEAK WAS NOTED ON THE CRANKCASE HOUSING. FURTHER INSPECTION REVEALED A CRACK O	N THE FORWARD LEFT HAND PART OF THE CASE.					1	L	7	1 	3O	3	O	 	A1CE    	E286				 
2002051400028	20020514	00028	EU  	2002	5	14	CA020503006      	1	20020429	G	5240	F5348614400200	DOOR            			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					WATER SERVICE	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) POTABLE WATER SERVICE PANEL MISSING ON ARRIVAL IN YYZ. MAINTENANCE RELEASED THE AIRCRAFT IN ACCORDANCE WITH CDL 52	-7.					2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002061200017	20020612	00017	EU  	2002	6	12	CA020507003      	2	20020412	G	8500		ENGINE          			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  					NACELLE	FAILED          	W				O				OTHER                   				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	IN	INSP/MAINT     	1			CA											(CAN) -PILOT REPORTED 'PROP NOT CYCLING DURING RUN-UP, ALL INDICATIONS NORMAL'.- LINEMAN ATTEMPTED RUN-UP & TRIED TO REA	CH MAX RPM'S & CYCLE PROP.  ENGINE REPORTEDLY LOST POWER & LINEMAN INCREASED THROTTLE, HE KEPT DOING SO UNTIL ENGINE RAN	 ROUGH, AT WHICH POINT HE RETARDED THROTTLE. ENGINE SEIZED AT IDLE. LINEMAN SUBSEQUENTLY CONTACTED MTC CONTRACTOR & CALL	ED FOR HELP. COMPANY ENGINEER ARRIVED. AMO CONTRACTOR ARRIVED & PROCEEDED TO INSPECT THE ENGINE. NOSE CASE CHIP PLUG FOU	ND COVERED IN STEEL FILINGS, WITH VAST & EXCESSIVE QUANTITY OF BRASS, ALUMINUM & STEEL IN THE OIL FILTER. ENGINE REMOVED	 FOR TEARDOWN BY ROTECH RESARCH CANADA.	1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2002061200021	20020612	00021	SW  	2002	6	12	CA020507008      	1	20020417	G	3250	9937	SHOE            			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					NLG STEERING	DIRTY           	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ANTI-SHIMMY FRICTION SHOE HAD DIRT OR SAND IN IT THAT WAS CAUSING MORE DRAG THEN NECESSARY. SAND MAY HAVE BEEN PIC	KED UP IN PARKING AREA. AIRCRAFT WAS ATTEMPTING TO TAKEOFF, A STEERING CORRECTION WAS MADE AND STEERING COULD NOT BE CEN	TERED. AIRCRAFT WENT OFF RUNWAY INTO GRASS. AIRCRAFT SUFFERED NO DAMAGE.				1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2002091800006	20020918	00006	EA  	2002	9	18	CA020507016      	1	20020502	G	5101	C6TE105329	HINGE           			DHAV  	DHC6  	DHC6        	2802606	EA  											MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) HINGE HALF - MISMANUFACTURED.  PLEASE NOTE RMA RECEIVED TWO C6WFM1218-27 CLEATS FROM DIFFERENT SUPPLIERS, 1 MAY 4/	01 FOR RMA INVENTROY AND 1 APRIL 23/02 FOR A WORK ORDER. BOTH CLEATS ARE MISMANUFACTURED. THE CLEAT FROM C6WFM1218-27 AP	RIL 23/02 IS LOT 0007 FROM BRAD.				1	H	7	2 	3T			RT	A9EA    					 
2002061200035	20020612	00035	SW  	2002	6	12	CA020507018      	1	20020425	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT FLAP UPPER CABLES FRAYED AT WING ROOT PULLEYS.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002061200036	20020612	00036	EA  	2002	6	12	CA020507019      	1	20020422	G	5711	22840111	SPAR CAP        			ARONCA	15    	15AC        	0191202	EA  	CONT  	C145  	C1452       	17012	SO  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INTERGRANULAR CORROSION FOUND ON TOP SPAR CAP (ANGLE) BOTH WINGS. REQUIRED REPLACEMENT (FOUND AT ANNUAL INSPECTION	).					1	H	7	1 	3O	3	O	 	A802    	E253				 
2002061200039	20020612	00039	EU  	2002	6	12	CA020507022      	1	20020421	G	6120	1530650012	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV3BC      	EU  	PROP CONTROL	BROKEN          	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) A STUDENT PILOT REPORTED TO MAINTENANCE THAT ON A GROUND RUN OF THE AIRCRAFT THAT THE PROPELLER WOULD NOT CYCLE WH	EN THE CONTROL WAS PULLED OUT TO PUT THE PROP INTO COARSE PITCH. INVESTIGATION FOUND THAT THE PROP CONTROL FLAT SPRINGS 	THAT HOLD THE PROP CONTROL SYSTEM RIGID HAD BROKEN. THESE SPRINGS GO THROUGH MANY CYCLES AND BREAK WHEN THEY ARE STRESSE	D. NEW SPRINGS WERE INSTALLED WITH NO STRESS BETWEEN THE BRACKET AND THE SUPPORT, AND THE PROP FUNCTIONED PROPERLY ON TH	E RUN-UP.		1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	USSR	 
2002061200050	20020612	00050	EU  	2002	6	12	CA020508003      	1	20020422	G	3250	Z4242170001	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON TAXI A STUDENT PILOT NOTICED AN EXCESSIVE AMOUNT OF PLAY IN THE NOSE STEERING SYSTEM. MAINTENANCE WAS NOTIFIE	D AND THE RT STEERING SPRING WAS FOUND TO BE BROKEN. THE SPRING WAS REPLACED USING THE MINIMUM SPACING FOR PRELOAD TENSI	ON. STUDENT REMINDED OF GETTING THE AIRCRAFT MOVING BEFORE TURNING THE NOSE WHEEL TO REDUCE STRESS ON THE NOSE GEAR STEE	RING SPRINGS.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002061200052	20020612	00052	EU  	2002	6	12	CA020508004      	1	20020423	G	3250	Z4242170001	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON TAXI A STUDENT PILOT NOTICED AN EXCESSIVE AMOUNT OF PLAY IN THE NOSE STEERING SYSTEM. MAINTENANCE WAS NOTIFIE	D AND THE RT STEERING SPRING WAS FOUND TO BE BROKEN. THE SPRING WASREPLACED USING THE MINIMUM SPACING FOR PRELOAD TENSIO	N. STUDENT REMINDED OF GETTING THE AIRCRAFT MOVING BEFORE TURNING THE NOSE WHEEL TO REDUCE STRESS ON THE NOSE GEAR STEER	ING SPRINGS.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002061200055	20020612	00055	EU  	2002	6	12	CA020508005      	1	20020419	G	3250	Z4242170001	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON TAXI A STUDENT PILOT NOTICED AN EXCESSIVE AMOUNT OF PLAY IN THE NOSE STEERING SYSTEM. MAINTENANCE WAS NOTIFIE	D AND THE LT STEERING SPRING WAS FOUND TO BE BROKEN. THE SPRING WAS REPLACED USING THE MINIMUM SPACING FOR PRELOAD TENSI	ON. STUDENTS WERE ONCE AGAIN REMINDED OF GETTING THE AIRCRAFT MOVING BEFORE TURNING THE NOSE WHEEL TO REDUCE STRESS ON T	HE NOSE GEAR STEERING SPRINGS.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002061200095	20020612	00095	NM  	2002	6	12	CA020508011      	1	20020327	G	3320	B0330211150	SOCKET          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					CABIN	ARCED           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AURCRAFT CARRIED OUT AN AIR-RETURN WITH AN APPARENT BURNING SMELL IN THE CABIN. UPON ENGINEERING INVESTIGATION, TH	E BURNING SMELL WAS TRACED TO THE CABIN LHS NR 2 FLUROESCENT TUBE LAMP HOLDER P/N BV03302-11-150. THE LAMP HOLDER WAS RE	PLACED AND THE AIRCRAFT RETURNED TO SERVICE. NO FURTHER DEFECT HAS BEEN REPORTED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2002061200096	20020612	00096	NM  	2002	6	12	CA020508012      	1	20020501	G	3233	8300101	ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	CONTAMINATED    	W				L				ABORTED APPROACH        				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING A FLT ON FINAL DESCENT LDG GEAR WAS SELECTED "DOWN". NLG FAILED TO EXTEND WITH BOTH DOOR & UNSAFE LIGHT ILL	UMINATED. A MISSED APPROACH WAS CARRIED OUT BY FLT CREW WITH GEAR SELECTION NOT CHANGED. DURING MISSED APROACH, APPROX O	NE MIN AFTER GEAR WAS SELECTED DOWN NLG EXTENDED & LOCKED DOWN WITH NO INPUT FROM FLT CREW.FROM GO-AROUND AIRCRAF T MADE	 ANOTHER APPROACH FOLLOWED BY A LDG W/O INCID.. SUBSEQUENT ENGINEERING INVEST. REVEALED THAT NLG ACTUATOR WAS UNSERVICEA	BLE DUE TO A CONTAMINANT BEING FOUND INTERNALLY IN ACTUATOR. ACTUATOR WAS REPLACED, GROUND RETRACTIONS CARRIED OUT SATIS	FACTORILY, & A/C WAS RT-SRV.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002061200108	20020612	00108	SO  	2002	6	12	CA020508015      	1	20020503	G	5730		SKIN            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT WAS STORED IN COLLINGWOOD SINCE NOVEMBER AND FLOWN TO TORONTO IN APRIL FOR ITS ANNUAL.  UPON INSPECTI	ON SECTION OF LOWER WING SKIN WAS PEELED BACK, ABOUT EIGHT INCHES, DUE TO SLIPSTREAM. THE INITIAL CRACK HAD BEEN STOP DR	ILLED.THIS SECTION IS POSSIBLY PRONE TO CRACKING AS A RESULT OF WING FLEXING DURING FLIGHT.  THERE ARE OTHER CRACKS STOP	 DRILLED IN THIS AREA SO A MORE FREQUENT INSPECTION SHOULD BE INITIATED.			1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2002061200110	20020612	00110	EA  	2002	6	12	CA020508016      	2	20020507	G	8530	3813	STUD            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					CYLINDER	BROKEN          	W				E				ENGINE SHUTDOWN         				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) MAY 7, 2002.  THE AIRCRAFT DEPARTED YVR ON A NORMAL POSITIONING FLIGHT TO YYJ. ABOUT 15 MILES OUT OF YYJ, THE CREW	 NOTED A ROUGHNESS IN THE LT ENGINE FOLLOWED BY OIL COMING OUT OF THE COWLING, AND ELECTED TO PERFORM A PRECAUTIONARY SH	UTDOWN. LANDED IN YYJ WITHOUT FURTHER INCIDENT.  INVESTIGATION REVEALED THAT THE 3/8 INCH DIAMETER STUD P/N 38-13 AT THE	 1:00 POSITION ON THE NR 2 CYLINDER HAD FAILED JUST BELOW THE CASE SURFACE UNDER THE CYLINDER MOUNTING FLANGE. LOSS OF T	HIS STUD CAUSED RAPID FAILURE OF THE OTHER 3 STUDS ON THE UPPER FLANGE OF THIS CYLINDER, UNSEATING THE BASE SEAL AND REL	EASING OIL. THE LOWER STUDS WERE ALL INTACT AND HOLDING THE CYLINDER IN PLACE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002061200175	20020612	00175	NM  	2002	6	12	CA020509012      	1	20020310	G	3320	338210	SOCKET          			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					CABIN	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) AFTER ENGINE START SMOKE IN REAR PART OF CABIN WAS REPORTED BY CABIN CREW. THE THIN WHITE SMOKE NEAR SIDEWALL AT R	OW 20AC WAS ACCOMPANIED BY A SMELL LIKE BURNED PLASTIC. ON GROUND EMERGENCY WAS PERFORMED. EMERGENCY EVACUATION THROUGH 	FORWARD ENTRANCE DOOR WAS PERFORMED. LAMP HOLDER REPLACED AND AIRCRAFT RELEASED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002061200179	20020612	00179	NM  	2002	6	12	CA020509016      	1	20020204	G	3260		SENSOR          			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					LANDING GEAR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT, GEAR DOWN SEQUENCE STARTED WITHOUT ANY PILOT INPUT. GEAR RETURNED TO UP POSITION AND NO FURT	HER INCIDENT RESULTED. SPEED REDUCED TO 200 KIAS AND FLIGHT CONTINUED WITH AN UNEENTFUL LANDING.MAINTENANCE PERSONNEL CH	ECKED AND ADJUSTED ALL SENSORS. LANDING GEAR CYCLED SEVERAL TIMES AFTER ADJUSTMENT WITHOUT ANY REMARKS. AIRCRAFT RETURNE	D TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002061300012	20020613	00012	SO  	2002	6	13	CA020510016      	2	20020427	G	8530	654961C	CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	ENGINE	WORN            	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											(CAN)  ENGINE INDICATING SYS & PARAMETERS WERE OP NORMALLY.AT 164.1 HRS OF OP, A CYLINDER DIFFERENTIAL CHECK WAS CARRIED	 OUT. ALL CYLINDERS WERE FOUND TO BE IN 60/80 RANGE. A/C CONTINUED TO FLY & AT 260.6 HRS OF OP, A 2ND DIFFERENTIAL CHECK	 SHOWED READINGS OF LOW 50'S WITH ONE CYLINDER 24/80. 2 CYLINDERS SHOWED EXHAUST VALVE LEAKS. TCM WAS CONTACTED & ALL CY	LINDERS WERE REMOED & SENT TO A REPAIR STATION FOR INVESTIGATION. THOSE CYLINDERS WERE REPAIRED & INSTALLED. A/C WAS GRO	UND RUN & TEST FLOWN, PRODUCING ADEQUATE POWER IN ALL FLT CONDITIONS.		1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2002061300015	20020613	00015	SO  	2002	6	13	CA020510019      	1	20020501	G	3233	AN517A	BOLT            			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					LT MLG ACTUATOR	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN, THE RIGHT MAIN & NOSE GEAR LOCKED DOWN CORRECTLY BUT THE LEFT MAIN	 DID NOT. THE CREW THEN SELECTED EMERGENCY GEAR EXTENSION AND LANDED SAFELY. UPON INSPECTION THE LEFT ACTUATOR UPPER BOL	T WAS FOUND TO BE SHEARED.				1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2002061300016	20020613	00016	GL  	2002	6	13	CA020510020      	3	20020415	G	6110	31561	CLAMP           			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  	COUNTERWEIGHT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COUNTERWEIGHT CLAMP FOUND TO BE CRACKED IN THE MIDDLE MID-WAY BETWEEN THE CLAMP RETAINING BOLTS.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P5EA	 
2002061300017	20020613	00017	NE  	2002	6	13	CA020510021      	2	20020430	G	7414	1021488	RETAINER        	BENDIX      	SF14RN8     	DOUG  	DC4   	C54EDC      	3021528	WP  	PWA   	R2000 	R2000*      	52023	NE  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						214343					(CAN) RETAINER FOR VERNIER DRIVE COUPLING WORN ON ITS FLATS, ALLOWING VERNIER TO SLIP AND THEREFORE (ENGINE) TIMING TO C	HANGE. OVERHAUL SHOPS HAVE BEEN NOTIFIED.					2	L	7	4 	4R	4	R	 	A762    	5E5				 
2002061300018	20020613	00018	GL  	2002	6	13	CA020510022      	3	20020508	G	6110	A0014B	THRUST LINK     			UNIVAR	108   	1083        	9230408	NM  	LYC   	O435  	O435C       	41516	EA  	HARTZL	HC12X	HC12X208    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE PROPELLER WAS OVERHAULED ON JULY 18, 1996, WAS REMOVED FOR AD 97-18-02 WITH 42.4 HRS. TSO. ON JUNE 29, 1999 TH	E AD WAS COMPLETED AND THE PROPELLER INSTALLED ON JULY 2, 1999. ON APRIL 19, 2000 THE PROPELLER WAS REMOVED FROM THE AIR	CRAFT WITH 88.3 HRS. TSO. UPON OUR DISASSEMBLY OF THE PROPELLER WE FOUND CORROSION IN ONE OF THE BEARINGS ON ONE SIDE OF	 THE PROPELLER, AND EXTREME CORROSION ON THE BEARING SURFACES AND THE INNER SURFACE OF THE CLAMP ASSEMBLY. BOTH OF THE B	EARINGS AND THE ONE CLAMP REQUIRE REPLACEMENT.		1	H	7	1 	3O	3	O	 	A767    	E228	5	C	P845	 
2002052400086	20020524	00086	NM  	2002	5	24	CA020510025      	1	20020509	G	2910	DCS252840124	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA			29504								(CAN) NR 2 HYD ISOLATION  VALVE CAUTION LIGHT CAME ON WHEN GEAR EXTENSION SELECTED. ALTERNATE GEAR EXTENSION CARRIED OUT	. LANDED WITHOUT FURTHER EVENT. MAINTENANCE FOUND NLG ACTUATOR HYD PRESSURE LINE SPLIT 1INCH FROM ACTUATOR FITTING					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002061300023	20020613	00023	EU  	2002	6	13	CA020514002      	2	20020513	G	7322	961215	NEEDLE          			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					CARBURETOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE NUMBER 3 CARBURETOR NEEDLE POSITION WAS FOUND TO BE WORN TO 1/16 INCH						1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002061300024	20020613	00024	EU  	2002	6	13	CA020514003      	2	20020510	G	7322	961215	NEEDLE          			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  					CARBURETOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NEEDLE POSTION 3 WAS FOUND TO BE WORN TO 3/32 AN INCH.						1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2002052400088	20020524	00088	SO  	2002	5	24	CA020515003      	2	20020506	G	7421	URHB32E	SPARK PLUG      	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	CYLINDER	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						570567					(CAN) ENGINE DEVELOPED A KNOCK ON RETURN FLIGHT IN CRUISE.  REELED LOWER SPARK PLUG ON NR 6 CYLINDER BROKEN FLUSH WITH T	HE OUTSIDE OF THE CYLINDER. REMAINDER OF SPARK PLUG WAS FOUND HANGING ON THE LEAD. SPARK PLUG WAS REPLACED.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002061700061	20020617	00061	CE  	2002	6	17	CA020516011      	1	20020516	G	5311		FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11484								(CAN) FUSELAGE RIGHT HAND FRAME AT STA 177.50, STRINGER 8 CRACKED. SHEET METAL REPAIR TO BE DONE PRIOR TO FURTHER FLIGHT	.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002061700086	20020617	00086	CE  	2002	6	17	CA020517006      	1	20020515	G	3260	4532303016001	CLEVIS          	LEAR        	66323030043 	LEAR  	45    	45LEAR      	5170805	CE  										MLG UPLOCK	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						0108					(CAN) AIRCRAFT ROLL ON TAKE-OFF.  DURING CLIMB FLIGHT CREW SELECTED GEAR UP.  MAIN LANDING DOOR CYCLES UP AND DOWN,  UNT	IL THE PILOT RE-SELECTED GEAR IN DOWN POSITION.  AIRCRAFT CAME BACK LANDING AT IT'S MAINTENANCE BASE. MAINTENANCE PERSON	NEL FOUND THAT THE LT FREE FALL CLEVIS CABLE ON THE UPLOCK ASSY HAD'NT RESET TO IT'S PROPER POSITION. CABLE WAS RESET AN	D FUNCTION CHECK SERVICEABLE ON GROUND.			2	L	7	2 	4F			RT	T00008WI					 
2002061700092	20020617	00092	SO  	2002	6	17	CA020521005      	2	20020513	G	8530	CL66P15	CYLINDER        			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) STEEL BARREL CRACKED AROUND CIRCUMFERENCE JUST BELOW HEAD ATTACH AREA. 90 PERCENT.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002061700109	20020617	00109	SO  	2002	6	17	CA020522000      	1	20020517	G	5312	764028	PLATE           			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  					BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BULKHEAD REINFORCEMENT PLATE (KIT P/N 764 028)WAS FOUND CRACKED AT AFT FUSELAGE STA 317.75 WITHIN THE SAME INS	PECTION AREA OUTLINED ON PIPER SB 636A.  THE REINFORCEMENT PLATE IS A PART OF PIPER KIT 764 028 INSTALLED UNDER AD96-12-	12 WITH ABOUT 2000 HOURS SINCE INSTALLATION.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002061700122	20020617	00122	CE  	2002	6	17	CA020522006      	1	20020521	G	3245	0923150	TUBE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					TIRE	DEFECTIVE       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FAILURE OF CENTER SEAM OF 600 X 6 - 6 PLY TIRE TUBE.  THIS HAS OCCURED ON 2 OTHER SEPERATE OCCASIONS.  SUPPLIER HA	S BEEN NOTIFIED AND HAS INDICATED THAT HE WAS GOING TO CONTACT MICHELIN AND INQUIRE ABOUT THE PROBLEM.  PICTURES OF DEFE	CT ARE ON FILE AND MAY BE E-MAILED IF REQUESTED.  SUPPLIER HAS BEEN ASKED FOR CREDIT FOR THESE TIRE TUBES.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002061800014	20020618	00014	CE  	2002	6	18	CA020523017      	1	20020516	G	3213	6960298	FORK            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOTH BOW WHEEL FORKS HAVE TWO CRACKS EACH UP TO 1.5 INCHES LONG LOCATED ON THE AFT UPPER EDGE OF FORK.  THE CRACKS	 ARE RUNNING FROM EDGE OF THE FORK FORWARD THE TWO 5/16 INCH REAR MOUNTING BOLT HOLES.  ONE OF THE CRACK HAD GONE BEYOND	 THE HOLE.				1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2002061800019	20020618	00019	SW  	2002	6	18	CA020524006      	1	20020524	G	2750	19023	CABLE           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RT & LT TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT UPPER FLAP CABLES FRAYED AT WING ROOT PULLEYS WITH 2ND NOTCH OF FLAP SELECTED.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002061800026	20020618	00026	SO  	2002	6	18	CA020527009      	1	20020514	G	5330		SKIN            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10480	10480							(CAN) PIPER SB 1045 ISSUED TO INSPECT FORWARD WING SPAR ATTACH BRACKETS. INSPECTION REVEALED CRACKING IN FUSELAGE STRUCT	URE AND SKIN. REPAIRS CARRIED OUT AS PER SB AND PIPER SERVICE MANUAL AND AC 43-13-1B/2A FIG 4-16. ALL PARTS REQUIRED AS 	PER SB 1045 WERE AVAILABLE AT PIPER.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002061300094	20020613	00094	CE  	2002	6	13	CA020528003      	1	20020211	G	2435	23078019	STARTER GEN     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT ENGINE	CRACKED         	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) NR 1 GENERATOR SHUT DOWN IN FLIGHT. AFTER LANDING THE ENGINE WAS SHUTDOWN AND TRIED TO RE-START.  STARTER WOULD NO	T ENGAGE.INSPECTED LT STARTER GENERATOR, FOUND THAT THE COOLING FAN WHICH IS PART OF UNIT HAD ITS BLADES ALL CRACKED UP.	  SUSPECTED BEARING FAILURE.  REPLACED STARTER GENERATOR,  ENGINE RUNS CARRIED OUT AND CHECKED SERVICEABLE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002061800112	20020618	00112	CE  	2002	6	18	CA020529003      	1	20020514	G	5744	122005311	HINGE           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					CONTROL SURFACE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN LOWER ATTACH FLANGE DURING SPECIAL INSPECTION PER CESSNA CONTINUED AIRWORTHINESS PROGRAM.THIS WAS L	EFT HAND INBOARD HINGE. ALSO FOUND RIGHT HAND INBOARD HINGE CRACKED. OUTBOARD LEFT HAND HINGE HAD BEEN RECENTLY REPLACED	.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2002080600071	20020806	00071	CE  	2002	8	6	CA020529004      	1	20020520	G	5320	50420014230	CHANNEL         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20868								(CAN) FOUND CHANNEL CRACKED AT FORWARD O/B RADIUS AND AFT O/B RADIUS DURING SPECIAL CYCLE REPETETIVE INSPECTION. THE LEF	T (OPPOSITE) CHANNEL WAS ALSO FOUND CRACKED IN THE AFT AREA. BEECH CONTACTED. PARTS BEING REPLACED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002073000129	20020730	00129	CE  	2002	7	30	CA020529005      	1	20020529	G	5230	260120413	LATCH           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	CARGO POD DOOR	LOOSE           	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) WHILE ON A BIRD DOGGING MISSION OVER A FIRE. THE AIRCRAFT WAS IN A TURN OVER THE TARGET, A THUMP WAS HEARD, AN INI	TIAL SEVERE VIBRATION WAS FELT, ON CLIMBING TO ALTITUDE THE VIBRATION BECAME INTERMITTENT. THE AIRCRAFT RETURNED TO BASE	, UPON ARRIVAL AT THE TANKER BASE IT WAS DISCOVERED THAT THE FORWARD CARGO POD DOOR HAD OPENED IN FLIGHT. THE AIRCRAFT W	AS INSPECTED FOR DAMAGE, AND THE DOOR LATCHES WERE ADJUSTED TO ENSURE A POSITIVE LOCK. THE AIRCRAFT WAS RETURNED TO SERV	ICE. THE OTHER C208B AIRCRAFT WERE INSPECTED AND FOUND TO BE SERVICEABLE.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002061800121	20020618	00121	CE  	2002	6	18	CA020530006      	1	20020516	G	5320	05130633	BRACKET         			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300C       	17022	SO  					PAX DOOR FRAME	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE,  IT WAS DISCOVERED THAT THE BELLCRANK BRACKET P/N 0513063-3 IN THE BULKHEAD ASSEMBLY	,  FRONT DOOR POST WAS CRACKED.  THE FORWARD FLANGE OF THE BRACKET WAS CRACKED.  A NEW PART WAS INSTALLED USING THE EXIS	TING RIVET SIZE AND PATTERN.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002053100126	20020531	00126	EU  	2002	5	31	CA020530007      	1	20020527	G	2910	NAS161212	SEAL            		114080003   	AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					MLG DOOR MANIF	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) GREEN HYDRAULIC FLUID LEVEL FELL IN YELLOW RANGE. AIRCRAFT DIVERTED TO YYZ RESULTING IN AN OVERWEIGHT LANDING.  SE	AL FOUND LEAKING ON LANDING GEAR DOOR MANIFOLD ASSY. SEAL REPLACED AND SYSTEM LEAK CHECKED SERVICEABLE. OVERWEIGHT LANDI	NG CHECK COMPLETED, NO FAULTS FOUND.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002061800123	20020618	00123	CE  	2002	6	18	CA020530008      	1	20020522	G	2750	0512128	PULLEY BRACKET  			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					TE FLAPS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) WHEN SELECTING FLAPS FOR LANDING, LEFT FLAP WOULD NOT COME DOWN. AIR PRESSURE KEPT IT UP. PILOT SELECTED FLAPS UP,	 AND LANDED.					1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2002061800124	20020618	00124	SO  	2002	6	18	CA020530009      	2	20020509	G	8520	646255	PISTON          			CESSNA	172   	172B        	2072406	CE  	CONT  	O300  	O300C       	17022	SO  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE RAN WELL NO VISIBLE PROBLEM. PIECE OF PISTON SKIRT BROKEN LOOSE HELD IN BY OIL RING AND CYLINDER CURVE ONLY	.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002061800126	20020618	00126	CE  	2002	6	18	CA020530010      	1	20020517	G	5751	122005311	HINGE BRACKET   			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	LT & RT AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON BRACKETS WERE LOOSE ON SPAR AND IN SKIN ATTACH. UPON EXAMINATION FOUND BOTH BRACKETS CRACKED AT REAR AND B	OTTOM FLANGES. IT APPEARS THAT THE BRACKETS HAD BEEN LOOSE PREVIOUSLY AND REPAIRED BY SUBSTITUING CHERRY MAX THROUGH BOT	TOM SKIN WHICH DID NOT SOLVE PROBLEM. RT & LT AILERON HINGE BRACKETS P/N 1220053-11 & 1220053-18.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2002061800132	20020618	00132	SW  	2002	6	18	CA020530014      	1	20020516	G	2432	206075295053	WIRE            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					BATTERY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF BATTERY COMPARTMENT, THE POSITIVE BATTERY WIRE AT THE SOLONOID WAS FOUND BROKEN.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002061800134	20020618	00134	EA  	2002	6	18	CA020530016      	2	20020525	G	7414		MAGNETO         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CONTAMINATED    	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT RAN ROUGH WHEN RT MAG SELECTED. OIL CONTAMINATION WAS FOUND IN BREAKER COMPARTMENT. MAGNETO WAS REPLACED 	AND A/C GROUND RUNS COMPLETED.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002061300095	20020613	00095	NE  	2002	6	13	CA020531005      	2	20020531	G	7250	71500171	ENGINE          		71500171    	BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 1	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA						P674234B					(CAN) PRELIMINARY REPORT,  NR 1 ENGINE SHUT DOWN , ENGINE STARTED ROUGH WITH VIBRATION , ANTI-SELECTED OFF  WITH NO CHAN	GE,AIRCRAFT LANDED WITHOUT ANY INCIDENT. FOUND ENGINE TURBINE DAMAGED					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002061300096	20020613	00096	EU  	2002	6	13	CA020604009      	1	20020602	G	5220		DOOR            	FOKKER      	A20401411   	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					EMERGENCY EXIT	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA						TARLH					(CAN) LT EMERGENCY EXIT OPENED UPON LANDING INTO YYC. AIRCRAFT SWAPPED.  RECTIFICATION THE OVER WING EXIT WAS INSPECTED 	WITH NO FAULTS FOUND.  OVER CENTER SPRINGS WERE REPLACED AND DOOR WAS RIGGED AS PER THE MAINTENANCE MANUAL. THE FORCE RE	QUIRED TO OPEN THE DOOR WAS MEASURED TO ESTABLISH A GUIDELINE AS THE AIRCRAFT WILL BE INSPECTED EVERY MAINTENANCE OVER N	IGHT UNTIL AN SIO IS ISSUED.			2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002061900147	20020619	00147	SW  	2002	6	19	CA020604010      	1	20020530	G	7500	88027687	LINE            			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					BLEED AIR	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE AIRCRAFT WOULD NOT PRESSURIZE. THERE WAS A LOUD WHISTLING SOUND COMING FROM THE ENTRANCE DOOR ARE	A, INDICATING NO PRESSURIZATION. THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION IT WAS NOTED THAT THE FLARE END OF ON	E CONNECTION HAD PULLED THROUGH THE B-NUT. THE BLEED AIR LINE WAS REPLACED WITH A SERVICEABLE UNIT. AIRCRAFT WAS GROUND 	RUN BLEED AIR SYSTEM WAS LEAK CHECKED SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE.			1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2002080600073	20020806	00073	CE  	2002	8	6	CA020606003      	1	20020416	G	7100		GEAR            			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	CAMSHAFT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ENGINE WAS PUT TOGETHER WITH THE WRONG CAMSHAFT GEAR. THE ENGINE WOULD RUN BUT THE MAGNETO DROP WAS HIGH. ALSO IF 	YOU EXERCISED THE PROP AT ABOUT 1700 RPM THE ENGINE WOULD STALL OUT. THROTTLE RESPONSE AT LOWER RPMS WAS SLUGGISH AND WO	ULD MAKE THE ENGINE SPIT AND SPUTTER. HIGHER RPMS SEEMED NO PROBLEM.				1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2002061300097	20020613	00097	NM  	2002	6	13	CA020606006      	1	20020527	G	2760	ZRV873	RESTRICTOR VALVE			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119C      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	SPOILERS	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA						90213160					(CAN) LEFT OUTBOARD GROUND SPOILER FAILED TO DEPLOY ON LANDING. REPACED R/H RESTRICTOR VALVE P/N ZRV 87-3, S/N 90213160 	AND CHECK VALVE P/N ZCV 157-1, S/N 80356276. AIRCRAFT RETURNED TO SERVICE AND GROUND SPOILER SYSTEM CHECKED SERVICEABLE.	 ALL PARTS SENT TO VENDOR FOR TEAR DOWN REPORT AND EVALUATION.				2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2002061900170	20020619	00170	CE  	2002	6	19	CA020606008      	1	20020523	G	5500	07120487	ANGLE           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					TAILCONE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE,  IT WAS DISCOVERED THAT THE ANGLE - TAILCONE REINFORCEMENT RT IN THE TAILCONE BULKHE	AD ASSEMBLY WERE CRACKED.  NEW PARTS 0712048-7 (LT) AND 0712048-6 (RT) WERE INSTALLED USING THE EXISTING RIVET SIZE AND 	PATTERN.				1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2002061900171	20020619	00171	SO  	2002	6	19	CA020606009      	2	20020419	G	8520	639195	COUNTERWEIGHT   	CONT        	639134      						CONT  	O520  	IO520D      	17032	SO  					CRANKSHAFT	SEPARATED       	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA						D995					(CAN) ROLLER RETAINING PLATE VIBRATED THROUGH SIDE OF COUNTERWEIGHT ALLOWING ROLLER TO FALL OUT. COUNTERWEIGHT THEN STRU	CK CRANKCASE CAUSING NOISE. CRANKSHAFT CRACKED AT OPPOSITE BUSHING FROM OVERLOAD. CRANKCASE AND TWO PISTONS DESTROYED.										3	O			E5CE				 
2002061900182	20020619	00182		2002	6	19	CA020606017      	4	20020603	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT SPINNER BULKHEAD FAILED AT RADIUS OF FLANGE AT CUTOUT FOR PROPELLER. SPINNER DISTORTED AS RESULT OF THE BULKHE	AD FAILURE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002080700002	20020807	00002	CE  	2002	8	7	CA020607002      	1	20020526	G	3210	804184200651	GUSSET          			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13460								(CAN) DURING INITIAL INSPECTION OF AIRCRAFT AD CF-63-08 INSPECTED AND LT INBOARD AND RT INBOARD LANDING GEAR CLUSTER VIS	UALLY CRACKED.BOTH CLUSTERS HAD BEEN CRACKED AND WERE WELDED SHUT. CRACKS WERE THRU WELD AND PROGRESSING ALONG GUSSETS A	ND THRU GUSSETS.				1	L	7	2 	3R	3	R	 	A765    	5E1				 
2002070800011	20020708	00011	SO  	2002	7	8	CA020607006      	1	20020530	G	5720		COVER           			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					RT WING	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STAIN LEAKS WERE FOUND AT THE INBOARD MOST PANEL OF THE RIGHT WING HEADER TANK. THE PANEL IS UNDERNEATH THE WHEEL 	FAIRING DEFLECTOR. PANEL WAS REMOVED AND RESEALED. SEALER MIGHT HAVE BEEN SLIGHTLY DRY.					1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2002080700003	20020807	00003	CE  	2002	8	7	CA020607008      	1	20020516	G	2497		CONNECTOR       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	PROP DEICE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23600	23600							(CAN) CESSNA SERVICE BULLETIN CAB00-11. THIS SERVICE BULLETIN, WHICH IS OPTIONAL, WAS OUT ON OUR AIRCRAFT AND A SEVERELY	 BURNT CONNECTOR WAS FOUND.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002091800008	20020918	00008	EA  	2002	9	18	CA020607018      	2	20020606	G	8500		ENGINE          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					RIGHT	FLUCTUATES      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) JUNE 6, 2002. DURING CRUISE FLIGHT BETWEEN YVR & YYJ, THE RT ENGINE FLUCTUATED SLIGHTLY AND LOST POWER, HOWEVER, T	HE R/H TACH SHOWED OVERSPEED AS THE CREW SHUT THE ENGINE DOWN. THE CREW CONTINUED TO VICTORIA AND LANDED. INVESTIGATION 	REVEALED THE ENGINE TO BE INTACT WITH NO O UTWARD SIGNS OF FAILURE, HOWEVER, DRIVE BETWEEN THE PROPELLER AND REAR CASE H	AS BEEN AFFECTED. THE ENGINE WAS REPLACED WITH A SERVICEABLE ENGINE. THE ENGINE IS IN OUR SHOP AND SHOULD BE OPENED NEXT	 WEEK TO DETERMINE THE CAUSE OF THE POWER LOSS.ONCE DETERMINED, SUPPLEMENTAL DATA WILL BE SUPPLIED.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002061900218	20020619	00218	EA  	2002	6	19	CA020610004      	2	20020521	G	7314	LW15473	PUMP            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING THE SB OF THE CESSNA 01-73-01A, A NEW MECHANICAL FUEL PUMP WAS INSTALLED. WE BELIEVE THE PUMP WAS DEFECT	IVE, BECAUSE IT WAS NOT POSSIBLE FOR US TO HAVE RPM HIGHER THAN 1900. MOREOVER, AT 1900 RPM, A REDUCTION IN FUEL FLOW WA	S NOTICED. FOR NOW, WE INSTALLED THE OLD PUMP UNTIL THE NEW PUMP ARRIVES.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002061900224	20020619	00224	EU  	2002	6	19	CA020610007      	1	20020608	G	5524	NB310077	HINGE           			BNORM 	BN2   	BN2B21      	7080221	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING POST FLIGHT WALKAROUND A CRACK WAS NOTICED IN THE ELEVATOR OUTBOARD-HINGE, INBOARD-BRACKET. THIS BRACKET IS	 THE SUBJECT OF A 100 HOUR REPETITIVE INSPECTION UNDER BN2/SB.259. THE PREVIOUS INSPECTION 90 HOURS EARLIER SHOWED NO PR	OBLEMS.  THE CRACK EXTENDED FROM THE LOWER FORWARD CORNER TO THE LOWEST FORWARD RIVET ON THE DISTANCE PIECE.AS WELL UPON	 REMOVAL OF THE ELEVATOR THE RIVETS HOLDING THE DISTANCE PIECE ON THE OUTBOARD SIDE OF THE HINGE WERE FOUND PULLED THROU	GH THE RIB.		1	H	7	2 	3O	3	O	 	A17EU   	1E4				 
2002080700005	20020807	00005		2002	8	7	CA020610009      	4	20020524	G	3421		GYRO            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					COCKPIT	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER INSTALLATION OF A NEW OVERHAULED GYRO HORIZON, IT HAD BEEN FOUND UNSERVICABE. THAT GYRO HAD BEEN OVERHAULED 	BY AERONEUF INSTRUMENTS LTEE APPROVAL 27-91 ON RELEASE NOTE 28017 DATED FEB. 05, 2002					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002080700006	20020807	00006		2002	8	7	CA020610010      	4	20020531	G	3421		GYRO            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					COCKPIT	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER INSTALLATION OF A NEW OVERHAULED GYRO HORIZON, IT HAD BEEN FOUND UNSERVICABE. THAT GYRO HAD BEEN OVERHAULED 	BY AERONEUF INSTRUMENTS LTEE APPROVAL 27-91 ON RELEASE NOTE 28244 DATED MAY 27, 2002. IT IS THE SECOND SDR SUBMIT FOR TH	E SAME PROBLEM. ON RECEIP OF THESE INSTRUMENTS, THE SHIPPING BOX WAS FOUND IN AN PERFECT SHAPE				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002080700007	20020807	00007	CE  	2002	8	7	CA020611002      	1	20020516	G	5751		RIB             			HELIO 	H395  	H395A       	4300206	CE  	LYC   	O435  	GO435C2B2   	41516	EA  					AILERON	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RIB LACING THAT SECURES FABRIC ONTO AILERON RIBS FOUND TO BE SERIOUS CHAFED ALONG RIB EDGES WHICH COULD LEAD TO FA	ILURE OF FABRIC SECURITY ONTO RIBS AND POTENTIAL AILERON FLUTTER, ON BOTH RIGHT AND LEFT AILERON ASSEMBLIES.					1	H	7	1 	3O	3	O	 	1A8     	E228				 
2002070800013	20020708	00013	CE  	2002	7	8	CA020611004      	1	20020526	G	2410		BEARING         		DOFF10300E  	CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	ALTERNATOR	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						630601533					(CAN) ALTERNATOR FAILURE. REAR ROLLER BEARING SEIZED SHAFT CAUSING SHAFT TO SHEAR IMMEDIATELY AFT OF THE DRIVE ASSEMBLY.	NO EVIDENCE OF OR ADEQUATE LUBRICANT IN AFFECTED BEARING. OTHER PARTS OF THE ALTERNATOR APPEARED IN GOOD CONDITION EXCEP	T FOR THE BRUSHES WHICH WERE DAMAGED BY LOOSE ROLLERS AND DEBRIS FROM BEARING.				1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA	 
2002080700008	20020807	00008	EA  	2002	8	7	CA020611005      	2	20020425	G	8500		CASE            			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ENGINE BUILD-UP TO INSTALL THE PROP DEICE BRUSH BLOCK BRACKET ASSEMBLY. ONE OF THE BOLTS THAT GO THROUGH THE CA	SE HAD TO BE REMOVED. THE THREADS OF THE BOLT WERE MARKED UP. ON FURTHER INVESTIGATION IT WAS FOUND THAT THE BOLT HAD BO	TTOMED OUT IN THE HELICOIL INSERT. TOO LONG OF A BOLT WAS USED. NEW HELICOIL WAS INSTALLED AND PROPER BOLT LENGTH WAS US	ED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002071700185	20020717	00185	SO  	2002	7	17	CA020611006      	2	20020603	G	8540	632617	BEVEL GEAR      	CONT        	646220A38   	CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	STARTER ADAPTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) - VACUUM PUMP DRIVE NOT TURNING.- INSPECTION REVEALS NO TEETH ON DRIVE BEVEL GEAR.- METAL CONTAMINANTS CONTAINED I	NSIDE STARTER ADAPTER.- TCM SB 01-5 ADDRESSES PROBLEM.- TCM WARRANTS FULL REPLACEMENT.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2002071700207	20020717	00207	EA  	2002	7	17	CA020611007      	2	20020514	G	7414	1052947	MAGNETO         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					RIGHT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE 500 HOUR INSPECTION OF THE MAGNETO, SMALL CRACKS (1/4 INCH OR SHORTER) WERE FOUND IN THE ROTOR HO	USING WHERE THE MAGNET PROTRUDES THRU AT THE CORNERS (8 LOCATIONS). WERE ADVISED THIS WAS NOT RARE AND IS COMMON TO THE 	O-540 ENGINE SERIES AND PREDOMINENTLY TO THE O-540 INSTALLED IN R44 AIRCRAFT.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002080700009	20020807	00009	EA  	2002	8	7	CA020611008      	2	20020514	G	7414	1052947	ROTATING MAGNET 	BENDIX      	106006163   	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					LT MAGNETO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						C159918E					(CAN) DURING A ROUTINE 500 HOUR INSPECTION OF THE MAGNETO, SMALL CRACKS (1/4 INCH OR SHORTER) WERE FOUND  IN THE ROTOR H	OUSING WHERE THE MAGNET PROTRUDES THROUGH. TECH REP WAS CONTACTED AND WE WERE ADVISED THAT ALTHOUGH NOT COMMON, THIS WAS	 NOT RARE AND IS COMMON TO THE O-540 ENGINE SERIES AND PREDOMINENTLY TO THE O-540 INSTALLED IN R44 AIRCRAFT.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002070800014	20020708	00014	CE  	2002	7	8	CA020612002      	1	20020603	G	2910	CM3690A60XXX	HOSE            			CESSNA	441   	441         	2076020	CE  										HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC FLUID LEAK, FROM BELLY THE MAIN LANDING GEAR RETRACTION LINE WAS RUBBING AGAINST A SCREW, THAT WAS HOLDI	NG TWO CLAMPS AROUND TWO OTHER HYDRAULIC LINES UNDER THE RELAY BOX IN THE BELLY.					1	L	7	2 	3T			RT	A28CE   					 
2002070800015	20020708	00015	CE  	2002	7	8	CA020612005      	1	20020610	G	3212	8AO2195006	FITTING         		8000        	CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	LEFT STRUT	ELONGATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REINSTALLATION OF FLOATS,  BOTH LT FORWARD STRUT ATTACH FITTINGS WERE NOTED TO HAVE ELONGATED BOLT HOLES. A	T CLOSER EXAMINATION YOU COULD SEE THAT THE HOLES WERE NOT WORN ELONGATED BUT THE POUNDING FORCE OF LANDING HAD ACTUALLY	 DISTORTED THE METAL AND PUSHED IT AWAY. RIGHT SIDE FITTINGS INSPECTED FOR SIMILAR DAMAGE (NO FAULTS FOUND) AND FLOATS I	NSPECTED FOR OTHER SIGNS OF STRESS. PARTS REPLACED WITH NEW AND AIRCRAFT RETURNED TO SERVICE.			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002080700012	20020807	00012	GL  	2002	8	7	CA020612008      	1	20020611	G	7603		LEVER           			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	S3H1        	52016	NE  					TROTTLE	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) PILOT RETURNED AIRCRAFT TO AIRPORT UNEVENTFULLY AFTER THROTTLE CONTROL GRIP BROKE OFF THROTTLE LEVER.  PILOT WAS A	BLE TO RETAIN CONTROL USING THE STUB OF LEVER REMAINING, HOWEVER SITUATION COULD HAVE BEEN VERY SERIOUS HAD THE LEVER BR	OKEN IN A DIFFERENT LOCATION.LEVER BROKE OFF DUE TO A WEAKNESS IN A DESIGN OF THE PART (NARROWED DOWN AREA), PROBABLY VI	BRATION FATIGUE.			1	L	7	1 	3R	3	R	 	EXPA1L71	E143				 
2002070800016	20020708	00016	EA  	2002	7	8	CA020613001      	1	20020613	G	2750	C3WF24	FITTING         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					CENTER FOREFLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PUSH PULL ROD ATTACH POINT ON THE FOREFLAP HAD PLAY. UPON INSPECTION WE FOUND THAT THE RIBS HOLDING THE BRACKET FO	R THE PUSH PULL ROD WAS CRACKED AND HAD LOOSE RIVETS.					1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2002070800017	20020708	00017	NM  	2002	7	8	CA020613002      	1	20020528	G	3233		ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WHEN LANDING GEAR RETRACTION SELECTED LT MLG DID NOT LOCK UP, DOORS DID NOT CLOSE. UNCONFIRMED THAT THE DOORS INDI	CATED CLOSED, ALSO UNCONFIRMED THAT THE NOSE GEAR DOOR DID NOT CLOSE. SUBSEQUENT TEST FLIGHTS INDICATED DIFFERENT SCENAR	IOS WITH NLG SOMETIMES UNLOCKED SOMETIMES ALL OKAY. MLG WAS CONSISTENT IN THAT IT NEVER SHOWED LOCKED. RT MLG BEHAVED NO	RMALLY. UNABLE TO REPRODUCE THE FAULT ON THE GROUND/ON JACKS. THE RETRACTION ACTUATOR BRACKET WAS BROKEN CREATING THE PR	OBLEM.  BRACKET REPLACED. AIRCRAFT RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2002073000130	20020730	00130		2002	7	30	CA020613004      	4	20020612	G	2562		G SWITCH        	POINTER     																ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						408833					(CAN) WHILE IN THE SHOP FOR ANNUAL RECERTIFICATION IT WAS FOUND THAT THE ELT WOULD ACTIVATE WITH ANY SLIGHT BUMPING. UNI	T WAS RETURNED TO THE MANUFACTURER FOR REPAIR.																		 
2002070800020	20020708	00020	EU  	2002	7	8	CA020614002      	1	20020612	G	7700	5D3	DETECTOR        			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 1 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) AFTER DEPARTING FROM FORT SEVERN, THE NR 1 ENGINE OVERHEAT LIGHT CAME ON.  THE PILOT SHUT DOWN AND FEATHERED THE E	NGINE, CONTINUING TO MAIN BASE. MAINTENANCE CHECKED THE OVERHEAT DETECTOR AND FOUND TO BE GOING OFF EARLY.  THE DETECTOR	 WAS REPLACED AND THE AIRCRAFT GROUND RUN AT MAX POWER FOR 4 MINUTES WITH NO FURTHER INDICATION.AIRCRAFT RETURNED TO SER	VICE.			2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899	 
2002070800022	20020708	00022	CE  	2002	7	8	CA020617002      	1	20020613	G	5511		SPAR            			CESSNA	172   	172G        	2072420	CE  	LYC   	O320  	O320E2D     	41508	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A RECENT PAINT SHOP VISIT IT WAS DISCOVERED THAT A SIGNIFICANT NUMBER OF SERIOUS STRUCTURALLY DAMAGED AREAS	 WERE AHMMERED OUT WITH A DOLLY, NOT REINFORCED, AND EITHER FILLED IN WITH BODY PUTTY OR COERED OER WITH A PATCH. THE LE	FT WING MAIN SPAR APPEARS TO HAVE BEEN STRAIGHTENED AND NOT REINFORCED. BLIND FASTENERS WERE USED TO ATTACH A PORTION OF	 THE LEADING EDGE CONTRARY TO THE MAINTENANCE MANUAL. THE HORIZONTAL STABILIZER SPAR WAS FOUND TO BE CRACKED AND BUNCKLE	D, ETC. ETC..... THE 'REPAIRS' APPEAR TO HAE BEEN DONE SOME 20 YEARS AGO. THE AIRCRAFT HAS BEEN REMOVED FROM THIS LOCATI	ON AND WILL BE REPAIRED AT SOME UNKNOWN FACILITY.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002070800137	20020708	00137	EA  	2002	7	8	CA020617003      	2	20020514	G	8520	LW13865	CONNECTING ROD  			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	ENGINE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CONNECTING ROD APPEARS TO HAVE BROKEN 1 INCH OUT FROM CRANKSHAFT JOURNAL. THIS WRAPPED ITSELF AROUND UNTIL THE CON	NECTING ROD CAP DEPARTED AND THE PIECES BROKE THE CASE 60 PERCENT OF THE WAY AROUND THE ENTIRE CASE AND DESTROYED THE CA	MSHAFT AND JAMMED UP THE ENTIRE ENGINE. ENGINE WAS REMOVED AND SENT TO MANUFACTURER FOR ANALYSIS.				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2002070800025	20020708	00025	SO  	2002	7	8	CA020617005      	1	20020604	G	2510	7634700	BELLCRANK       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION, THE LOWER SEAT FORWARD RT BELLCRANK ASSEMBLY WAS FOUND DETACHED LEAVING THE SEAT BOTTOM 	ATTACHED IN ONLY 3 CORNERS. THE BELLCRANK WAS FOUND DETACHED IN 3 WELDS. THE WELDS WERE ONLY "TACK" WELDS. THE 3 OTHER B	ELLCRANKS HAVE WELDS NEARLY THE ENTIRE WAY AROUND THE TUBE. THIS APPEARS TO HAVE BEEN DONE ON MANUFACTURE. AS WELL, THER	E SHOULD BE A SMALL GUSSET TO STRENGTHEN THE BELLCRANK THAT WAS ALSO MISSING.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002080700013	20020807	00013	SO  	2002	8	7	CA020618002      	1	20020606	G	7810	9907704	EXHAUST PIPE    			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PIPE FAILED IN FLIGHT, UNIT REPAIRED AND RESTALLED  TIME SHOWN ON PART IS T.T ON AIRCRAFT TIME ON PART IS UNKOWN.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002080700014	20020807	00014	CE  	2002	8	7	CA020618005      	1	20020613	G	2133		SOLENOID VALVE  			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					CABIN PRESSURE	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) A/C FAILED TO PRESSURIZE AFTER TAKEOFF.  UPON RETURN TO BASE THE  A/C STILL WOULD NOT PRESSURIZE ON "TEST" POSITIO	N. MAINTENANCE DETERMINED THAT THE CABIN PRESSURE SAFTEY VALVE SOLENOID (DESIGNATOR E 105) WAS FAILED OPEN, NOT ALLOWING	 THE SAFTEY VALVE TO CLOSE AFTER TAKEOFF. THE SOLENOID VALVE WAS REPLACED AND THE A/C WAS TEST FLOWN WITH PRESURRIZATION	 SERVICEABLE.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002070800041	20020708	00041	CE  	2002	7	8	CA020619002      	1	20020618	G	3252	05421011	SHAFT           	CESSNA      	04425121    	CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					MLG DAMPENER	SHEARED         	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) INVESTIGATION OF A SEVERE NOSEWHEEL SHIMMY REPORT REVEALED THAT THE SHIMMY DAMPENER SHAFT HAD SHEARED. BOTH HALVES	 OF THE ASSEMBLY REMAINED ATTACHED BUT THE UNIT COULD NO LONGER FUNCTION AS DESIGNED. THE FAULTY UNIT WAS REMOVED FROM S	ERVICE AND REPLACED WITH A SERVICEABLE UNIT. CAUSE OF DEFECT IS UNKNOWN AT THIS TIME.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002070800042	20020708	00042	CE  	2002	7	8	CA020619003      	1	20020508	G	3252	05421011	SHAFT           	CESSNA      	04425121    	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					SHIMMY DAMPENER	SHEARED         	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) SEVERE NOSEWHEEL SHIMMY REPORTED AFTER LANDING. INSPECTION OF THE DEFECT BY MAINTENANCE REVEALED THAT THE SHAFT WA	S SHEARED. THE DAMPENER UNIT REMAINED ATTACHED BUT IN TWO SEPARATE PARTS PREVENTING IT FROM FUNCTIONING AS DESIGNED. NO 	FURTHER DAMAGE WAS FOUND AND THE UNIT WAS REMOVED FROM SERVICE. A REPLACEMENT UNIT WAS INSTALLED.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002070800043	20020708	00043	CE  	2002	7	8	CA020619004      	1	20020619	G	3221	04425037	FORK            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					MLG STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION WE TOOK A CLOSE LOOK AT THE OLEO ASSEMBLY BASED ON PREVIOUS FINDINGS OF LIKE PARTS. THE 	PRIMARY REASON FOR THIS DETAILED INSPECTION IS BASED UPON THE KNOWN HIGH TIME AND OPERATING ENVIRONMENT OF THESE UNITS. 	WE DETECTED A CRACK ON THE OUTER TOP SURFACE WHERE THE FORK CURVES. THE PART WAS REMOVED FROM SERVICE AND REPLACED WITH 	A SERVICEABLE UNIT.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002070800044	20020708	00044	CE  	2002	7	8	CA020619005      	1	20020605	G	3240	95440265	STRUCTURE       			LEAR  	24    	24D         	5170311	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					BRAKE ASSY	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING, A "TANG" ON THE WHEEL THAT ENGAGES WITH THE ROTATING BRAKE DISCS BROKE OFF. TIRE DID NOT DEFLATE. WHIL	E TAXIING, A RHYTHMIC SOUND COULD BE HEARD IN THE COCKPIT.					2	L	7	2 	4J	4	F	 	A10CE   	E6WE				 
2002070800045	20020708	00045	CE  	2002	7	8	CA020619006      	1	20020610	G	5330	05135212	SKIN            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12312								(CAN) DURING A T.C. AUDIT INSPECTION INTERGRANULAR CORROSION WAS OBSERVED. THE AREA IS THE TOP SKIN FORWARD OF WINDSCREE	N ON THE LEFT SIDE. THERE IS A HOLE APPROXIMATELY 1/2 INCH IN DIAMETER. AT THIS POINT, THERE IS ALSO "BUBBLING" OF THE P	AINT ON THE RIGHT SIDE. THE PATTERN FOLLOWS THE TOP OF THE STEEL FIREWALL.AT THIS TIME THE TOTAL EXTENT OF THE DAMAGE OR	 IT'S CAUSE IS NOT KNOWN.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002080700015	20020807	00015	SO  	2002	8	7	CA020619012      	2	20020611	G	8520	653631	GEAR            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	CRANKSHAFT	BROKEN          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AT THE MOMENT OF ACCIDENT, THE MOTOR DID A "KICK BACK". TWO TEETH OF THE CRANKSHAFT GEAR THAT WERE IN CONTACT WITH	 THE STARTER CLUTCH SHAFT GEAR BECAME BROKEN AND FELL INTO THE OIL PAN. THIS MODEL OF THE STARTER CLUTCH CAN STICK IF IT	 IS TURNED COUNTER-CLOCKWISE OF THE HELIX THAT PUTS HEAVY PRESSURE ON THE TEETH OF THE CRANKSHAFT GEAR.				1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2002071800018	20020718	00018	EA  	2002	7	18	CA020621004      	2	20020612	G	8530		VALVE SEAT      								LYC   	O320  	O320*       	41508	EA  					CYLINDER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INTAKE VALVE LEAKING 20/80 COMPRESSION. PROBLEM FOUND ON THE BENCH. THE CYLINDER HAD TO BE REMOVED, THE VALVE RE-S	EATED AND THE CYLINDER RE-INSTALLED ON THE ENGINE.										3	O			E274				 
2002070800048	20020708	00048	CE  	2002	7	8	CA020621007      	1	20020605	G	3232	MS166251068	RETAINER        			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2AF34C	D2AF34C310  	GL  	MLG DOOR	FAILED          	W				B				EMER. DESCENT           				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) PILOT INBOUND FOR LANDING & SELECTED GEAR DOWN. REPORTED THAT GEAR DID NOT EXTEND & GEAR MOTOR CONTINUED RUNNING. 	 BEGAN EMERGENCY EXTENSION OF GEAR WITH HAND PUMP BUT NO PRESSURE BUILDING ON HAND PUMP.  SEVERAL PROCEEDURES WERE CARRI	ED OUT BY PILOT & GROUND CREW, WITH NO SUCCESS. ON FLY BY IT WAS NOTED NOSE GEAR EXTENDED & SEEMED LOCKED, BUT MAIN GEAR	 HALFWAY EXTENDED. PILOT FINALLY EXECUTED GEAR UP LDG.  ON INSPECTION OF MLG, IT WAS FOUND THAT REAR LT MLG DOOR ACTUATO	R CYLINDER SEPARATED FROM PISTON ROD. PILOT REPORTED THAT HYDRAULIC FLUID AT NORMAL LEVEL.		1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2002071800034	20020718	00034	CE  	2002	7	18	CA020624003      	1	20020617	G	5321	50440012655	FLOORBOARD      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					CABIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15696								(CAN) THE ENTRANCE FLOOR PANEL WAS FOUND CRACKED AT STATION 278.5. PANEL REPLACED AND NO FURTHER DAMAGE REPORTED						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002091800009	20020918	00009	NE  	2002	9	18	CA020624005      	2	20020508	G	7200		BLADE           			BEECH 	MU300 	400BEECH    	       	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT & RT ENGINES	BIRD STRIKE     	W				C				ABORTED TAKEOFF         				C	T	Y	F.O.D.                    	ENGINE CASE PENETRATION   	ENGINE STOPPAGE           	TO	TAKEOFF        	1			CA		400GJ					RJ23				(CAN) THE FLIGHT WAS CLEARED FOR DEPARTURE BY AIR TRAFFIC CONTROL. THE FLIGHT CREW DID NOT OBSERVE ANY BIRDS ON OR AROUN	D THE RUNWAY, AND POWER WAS APPLIED FOR TAKEOFF. AS THE AIRSPEED INCREASED, THE CO-PILOT CALLED 'V1,' AND IMMEDIATELY AL	ERTED THE PILOT TO THE PRESENCE OF BIRDS. THE BIRDS IMPACTED THE AIRPLANE AND THE PILOT ABORTED THE TAKEOFF. THE AIRPLAN	E CAME TO A STOP ABOUT 100 FEET PRIOR TO THE DEPARTURE END OF THE RUNWAY. EXAMINATION OF THE AIRPLANE BY A FAA INSPECTOR	 REVEALED SUBSTANTIAL DAMAGE TO BOTH THE LT AND RT ENGINES. FURTHER EXAMINATION OF THE RT ENGINE REVEALED THAT A FAN BLA	DE SEPARATED AND PENETRATED THE ENGINE COWLING.  A 2-INCH GAP WAS ALSO OBSERVED BETWEEN THE ENGINE AND THE FUSELAGE.	2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2002071800061	20020718	00061	GL  	2002	7	18	CA020626003      	3	20020625	G	6110	B4426	SNAP RING       			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	PROPELLER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER RECEIVED FROM CUSTOMER AFTER LOSS OF SNAP RING. PROPELLER WAS DISMANTLED, BLADES DRESSED, PAINTED AND AS	SEMBLED.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2002071800063	20020718	00063	GL  	2002	7	18	CA020626004      	3	20020625	G	6114	C93C4904	HUB             													MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE HUB WAS FOUND CRACKED ON NR 3 BLADE SOCKET. ONE BLADE NUT WAS FOUND CRACKED.																5	C	P22EA	 
2002071800069	20020718	00069	EU  	2002	7	18	CA020626006      	1	20020619	G	2731	Z14244130000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ELEVATOR TRIM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AS A RESULT OF THE DISCOVERY OF AN ALMOST COMPLETELY FAILED ELEVATOR TRIM CONTROL CABLE ON ANOTHER AIRCRAFT AND BR	OKEN WIRES IN A SECOND AIRCRAFT'S CABLE, THIS AIRCRAFT'S ELEVATOR TRIM CONTROL SYSTEM WAS INSPECTED TO DETEMINE THE COND	ITION OF THE CABLES. IT WAS FOUND THAT THE FORWARD ELEATOR TRIM CABLE ASSEMBLY HAD THE ENDS OF 3 BROKEN WIRES PROTRUDING	 FROM THE OUTER WIRE BUNDLE.  THE FORWARD CABLE ASSEMBLY WAS REPLACED WITH NEW.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002071800092	20020718	00092	EA  	2002	7	18	CA020626007      	2	20020618	G	7414		BOOSTER         			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					LT MAGNETO	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING A PRE-FLIGHT RUN-UP THE AIRCRAFT ENGINE LT MAGNETO DROP WAS 600 RPM. TROUBLESHOOTING SHOWED THAT THE CAUSE 	WAS A FAULT WITH THE SLICK-START MAGNETO BOOSTER. THE BOOSTER WAS REPLACED AND THE ENGINE GROUND RUN. THE MAGNETO DROPS 	WERE WITHIN LIMITS.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002080700017	20020807	00017	EA  	2002	8	7	CA020626008      	2	20020619	G	7414		BOOSTER         			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING A PRE-FLIGHT RUN-UP THE AIRCRAFT ENGINE LT MAGNETO DROP WAS 600 RPM. TROUBLESHOOTING SHOWED THAT THE CAUSE 	WAS A FAULT WITH THE SLICK-START MEGNETO BOOSTER. THE BOOSTER WAS REPLACED AND THE ENGINE GROUND RUN. THE MAGENTO DROPS 	WERE WITHIN LIMITS.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002071800095	20020718	00095	NM  	2002	7	18	CA020626012      	1	20020624	G	6123	311195401	WIRE HARNESS    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	CORRODED        	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			99999								(CAN) ON TAKE-OFF ROLL AUTO FEATHER FAILED TO ARM , TAKE-OFF REJECTED AND AIRCRAFT RETURNED TO RAMP.  MAIN ENGINE ELECTR	ICAL HARNESS CONNECTER PINS FOUND CORRODED , WIRING HARNESS REPLACED , AIRCRAFT RETURNED TO SERVICE .					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002071800102	20020718	00102	EA  	2002	7	18	CA020626017      	2	20020614	G	8530	74541	EXHAUST VALVE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360F1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	VALE FACE	BURNED          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ENGINE POWER LOSER DURING TAKEOFF.  RT ENGINE COMPRESSION TEST REVEALED CYLINDER NR 3 EXHAUST VALVE FACE BURNT CAU	SING AIR LEAKAGE.					1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920	 
2002070800143	20020708	00143	NM  	2002	7	8	CA020627004      	1	20020626	G	7921		OIL COOLER      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2 ENGINE	LEAKING         	W				O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		DE	DESCENT        	1			CA			28311								(CAN) NR 2 ENGINE OIL PRESSURE FELL TO 45 PSI ON DESCENT.  NR 2 OIL COOLER FOUND LEAKING AND REPLACED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002080700021	20020807	00021	CE  	2002	8	7	CA020628002      	1	20020627	G	3233	4377113	CAP             	BEECH       	993880001   	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					NLG ACTUATOR	CRACKED         	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		AP	APPROACH       	1			CA						102					(CAN) PILOT SELECTED GEAR DOWN.  GEAR CAME DOWN AND 3 GREEN WERE INDICATED.  MOTOR KEEP RUNNING UNTIL C/B POPPED.  AIRCR	AFT LANDED WITHOUT INCIDENT.  NOSE GEAR ACTUATOR REPLACED, GEAR SWINGS CARRIED OUT AND AIRCRAFT RELEASED TO SERVICE. END	 CAP FRACTURED.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002071800121	20020718	00121	SO  	2002	7	18	CA020702002      	2	20020620	G	8530	SA648044	PISTON          			CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	R	J	SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) AFTER A SOUTH BOUND DEPARTURE FROM CYPY RUNWAY 03 AN ABNORMAL DROP IN MANIFOLD PRESSURE WAS NOTICED. THE P/C SWITC	HED FUEL TANKS TO ENSURE THE CAUSE WAS NOT FUEL CONTAMINATION. THERE WAS NO IMPROVEMENT. ENGINE INDICATIONS WERE LOW OIL	 PRESSURE, HIGH OIL TEMP, HIGH CYLINDER TEMP, AND SMOKE COULD BE SEEN FROM THE COCKPIT. THE A/C WAS TURNED BACK TO CYPY 	RUNWAY 03. AFTER ENSURING SUFFICIENT ALTITUDE TO MAKE THE FIELD, ENGINE WAS SHUTDOWN TO ENSURE NO FURTHER DAMAGE. AIRCRA	FT WAS LANDED WITHOUT INCIDENT AND ROLLED OFF THE RUNWAY, ON & OFF THE TAXIWAY AND ONTO THE APRON WHERE IT WAS PARKED. M	AINTENANCE INSPECTION REVEALED NR 6 PISTON DAMAGED BEYOND ECONOMICAL REPAIR. PISTON REMOVED.	1	H	7	1 	3O	3	O	 	A16CE   	E8CE				 
2002080700024	20020807	00024	NE  	2002	8	7	CA020702007      	2	20020627	G	7310		TUBE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL MANIFOLD	CONTAMINATED    	W				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING A REMOVAL / INSTALLATION OF THE FUEL NOZZLES,A SMALL PIECE OF METAL DEBRIS WAS FOUND WITHIN THE I	NTERNAL PASSAGE OF ONE OF THE FUEL MANIFOLD TRANSFER TUBES.  THE DEBRIS WAS LODGED WITHIN THE TUBE AND HAD TO BE EXTRACT	ED BY PUSHING IT THROUGH WITH A PUNCH.  THE NOZZLES DID NOT SHOW ANY ABNORMAL CONDITION.  A NEW TRANSFER TUBE WAS INSTAL	LED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002080700025	20020807	00025	EU  	2002	8	7	CA020702008      	1	20020623	G	3110		WARNING SYSTEM  			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	FAILED          	W				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			CA											(CAN) PILOT REPORTED NO MASTER WARNING OR CAUTION LIGHTS WORKING ON A/C.THE SYSTEM SENDS POWER TO LIGHTS FROM CENTRAL AD	VISORY & WARNING CONTROL UNIT & PLACES GROUND TO TURN LIGHTS ON.  14.62 VOLTS MEASURED FROM UNIT.  AFTER CONSULTING WITH	 TECHNICAL REPRESENTATIVE FOR MANUFACTURER A  NEW CONTROL UNIT ORDERED.  AFTER IT INST LIGHTS FAILED TO WORK. WIRES FROM	 TB115-02 WERE REMOVED VOLTAGE WAS TESTED AGAIN & WHEN WIRES WERE INSTALLED THE SYS WORKED NORMAL.  THE A/C DEPARTED ON 	FLT TO ANOTHER BASE SYS FAILED AGAIN AT BASE.  BASE ENGINEER WAS INSTRUCTED TO REMOVE WIRES GOING OUT OF TB115-02 TO SEE	 IF PROBLEM WITH ONE OF 4 LIGHTS HOOKED UP TO IT.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002071800127	20020718	00127	EU  	2002	7	18	CA020703001      	2	20020625	G	8520		PLUG            			HOACAU	HK36R 	HK36R       	4170002	EU  	ROTAX 	912   	ROTAX912    	55555	EU  					CRANKSHAFT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRANKSHAFT HAS PRESSED IN WELSH PLUG IN FORWARD SECTION. THIS PLUG WAS FOUND INSIDE CRANKCASE.THE FOD WAS LIMITED 	TO CYLINDERS AND UNDERSIDE OF PISTONS.					1	K	7	1 	3O	3	I	RC	G51EU   	EXPE3I				 
2002080700031	20020807	00031	EU  	2002	8	7	CA020704005      	1	20020624	G	2434		SLIP RING       		524321215   	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 GENERATOR	GROOVED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						100389					(CAN) INSPECTED GEN NR 2 BRUSHES FOR WEAR DURING SCHEDULED 100 HR INSP.  FOUND APPROX 50 PERCENT LIFE REMAINING ON MOD "	C" BRUSHES, HOWEVER THE BRUSH SLIP RING CONTACT AREA WAS GROOVED. IAW AIRCRAFT MM IF THERE IS PITTING, GROOVES OR SCORIN	G FOUND ON THE SLIP RING SURFACE THEN REPLACE THE GENERATOR. GENERATOR 2 REPLACED WITH NEW UNIT.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002073000131	20020730	00131	WP  	2002	7	30	CA020705004      	1	20020618	G	3397	1103070110	DECODER         			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					CABIN	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING READING LIGHT TEST, BURNING ODOR COMING FROM AREA AROUND SEAT ROWS 26 ABC TO 30 ABC NOTICED. ALL 	READING LIGHTS WERE WORKING AT TIME & SMELL VERY WEAK. AFTER MOMENT LIGHTS FROM ROW 27 ABC TO END WENT OUT. IN THAT AREA	 TECHNICIAN HEARD STATIC / CRACKLING SOUND JUST BEFORE LIGHTS WENT OUT & SMELL GOT STRONGER. OVERHEAD PANELS ABOVE ROWS 	26,27,28&29 WERE DROPPED & ODOR EXTREMELY STRONG. NO EVIDENCE OF ANY MALFUNCTION,  ARCHING OR BURN MARKS. SYS RESET & WH	EN THAT DONE DECODER AT ROW 29 ABC (POS 28) STARTED TO SMOKE. POWER CUT IMMEDIATELY & APPEARED TO BE NO OUTSIDE DAMAGE T	O SURROUNDING AREA. NO DAMAGE TO ANY OF CANNON PLUGS , WIRING OR CONNECTORS.	2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002073000132	20020730	00132	WP  	2002	7	30	CA020705006      	1	20020622	G	3232	269002119	ACTUATOR        			LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					MLG DOOR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FOUND LT MLG DOOR ACTUATOR CRACKED .250 INCHES AND LEAKING (CONFIRMED BY NDT), IN DOOR CLOSED POSITION. MAINTENANC	E REPLACED THE ACTUATOR IAW AMM 32-33-01.					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002080700039	20020807	00039	WP  	2002	8	7	CA020708003      	1	20020625	G	3240	60028812	MODULE          			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					BRAKE ASSY	CRACKED         	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT(IN MANCHESTER) RETURNED TO RAMP DUE TO B HYD SYSTEM LEAK FROM LT BRAKE MODULE. MAINTENANCE DISCOVERED THA	T THE UNIT WAS CRACKED 2.5 INCHES JUST OVER SYSTEM B BRAKE RETURN PORT LT AND REPLACED THE UNIT IAW AMM 32-44-01.					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002080700185	20020807	00185	EU  	2002	8	7	CA020708009      	1	20020613	G	2540	24E507009G01	WATER HEATER    			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					LAVATORY	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING THE C-08 CHECK, IT WAS DISCOVERED DURING THE OPERATIONAL TEST, THAT THE POTABLE WATER HEATERS, IN LAVATORY 	F,  WERE MAKING THE C/B TRIP. THE 3 UNITS WERE REMOVED AND SENT TO THE AVIONICS SHOP. WHEN REMOVING THE TOP COVER OF ONE	 UNIT, WE FOUND A SOPPY SUBSTANCE AND THE 2 OTHER UNITS SHOULD NOTHING (NO DEPOSITS). WHEN THE BOTTOM COVERS WERE REMOVE	D, WE FOUND ALL 3 THERMOSTAT ASSEMBLIES (P/N 24D50703G03) AND IRCUIT BOARD (24D507078G03) ASSEMBLIES BURNED. P/N OF THE 	POTABLE WATER HEATER ASSEMBLIES: P/N 24E507009G01. S/N'S OF THE POTABLE WATER HEATER ASSEMBLIES; S/N GOS 02204, G6W 0381	3, GOS 03427	2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2002080700198	20020807	00198	CE  	2002	8	7	CA020711001      	1	20020704	G	2497	21039	RHEOSTAT        	OHMITE      	21039       	LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					COCKPIT	DAMAGED         	W				H	D			DEACTIVATE SYST/CIRCUITS	RETURN TO BLOCK         			B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) WITH THE AIRCRAFT POWERED UP AND AC INVERTER ON, FLIGHT CREW NOTICE SMOKE RISING FROM LT SIDEWALL PANEL. UPON FUTH	ER INSPECTION WITH SIDEWALL REMOVED.  THREE WIRE BUNDLES THAT GO TO THREE DIFFERENT REHOSTAT WERE FOUND WITH SPIRAL WRAP	 AROUND THEN AND MELTED TO TWO OF THREE REHOSTATS. DUE TO THE CHANGE OF RESISTANCE IN THE REHOSTAT IN DIFFERENT POSITION	S AND ALSO BECAUSE IT IS SUCH A TIGHT AREA WERE THE WIRE COULD CHAFE THE PROBLEM WOULD NEVER HAPPENED. THE REOSTAT WERE 	REPLACED AND AIRCRAFT RETURN TO SERVICE.		2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2002080700199	20020807	00199	CE  	2002	8	7	CA020711002      	1	20020711	G	5310	55112402	DOOR FRAME      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUSELAGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OUTBOARD DOOR SKIN HAS WORN THE DOOR FRAME LINTEL AT THE RADIUS INTO THE DOOR OPENING AS MUCH AS 50 PERCENT MATERI	AL THICKNESS.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002080700204	20020807	00204		2002	8	7	CA020711004      	4	20020708	G	3160		DISPLAY         			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					PFD	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DURING FIRST DEPARTURE OF THE DAY THE NR 1 PFD DISPLAY UNIT (DU) WOULD NOT DISPLAY (BLANK). THE DU WAS REPLACED. T	HE A/C FLEW WITH NIL PROBLEMS.ON CLIMB OUT ON THE NEXT FLIGHT THE CREW REPORTED SMOKE IN THE FLIGHT DECK. THE AIRCRAFT R	ETURNED. THE NR 2 PFD WAS BLANK ON ARRIVAL AND CB WAS OUT. BURNING SMELL WAS CONFIRMED TO BE FROM THE NR 2 PFD. THE PFD 	WAS REPLACED. TECH RECORDS SHOW THE NR 2 PFD WAS PREVIOUSLY REPLACED ON MAY 7/02 DUE TO BLUE LINE ON SCREEN.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002080700208	20020807	00208	EA  	2002	8	7	CA020712003      	2	20020708	G	7320		FADEC           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					FUEL CONTROL	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			CA											(CAN) A POWER PLANT MESSAGE WAS RECEIVED DURING INITIAL ELECTRICAL POWER UP OF THE A/C. THE CODES WERE CLEARED AND THE E	NGINE GROUND RUN. NO PROBLEM WAS EVIDENT AT THAT TIME. TAKE OFF WAS BEGUN, AND ABORTED AS THE INDICATED TORQUE WENT TO 1	12 PERCENT FOR 2 SECONDS.  MAINTENENCE ACTIONS:  FADEC TRIM COMPENSATOR RESISTANCE VALUES WERE CHECKED, AND FOUND OK. TH	E FADEC WAS THEN REPLACED. NO FURTHER PROBLEM WAS EXPERIENCED. THE AIRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002080700211	20020807	00211	EU  	2002	8	7	CA020712005      	1	20020711	G	3230	C23199104	CONTROL VALVE   			AIRBUS	310   	A310300     	3930305	EU  										NLG DOOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING AN A-CHECK A HYDRAULIC OIL PUDDLE WAS FOUND IN FRONT OF NOSE GEAR. AFTER INVESTIGATION A PIN HOLE WAS FOUND	 ON THE RIGHT NLG DOOR ACTUATOR CONTOL VALVE. THE ACTUATOR, CONTOL VALVE ASSEMBLY WAS REPLACED AND A LEAK CHECK WAS CARR	IED OUT WITH NO FUTHER LEAKS NOTICED.				2	L	7	2 	4F			RT	A35EU   					 
2002080700214	20020807	00214	EA  	2002	8	7	CA020712006      	2	20020708	G	7314	AN4101	PUMP            			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	FUEL	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB FROM THE WHITEHORSE AIRPORT, THE PILOT NOTED THAT THE FUEL PRESSURE ON THE NUMBER 2 ENGINE WAS FLUCTU	ATING. THE ELECTRIC BOOST PUMP WAS ACTIVATED TO STABILIZE THE FUEL PRESSURE. THE PILOT EJECTED THE RETARDANT LOAD AND RE	TURNED TO THE AIRPORT. MAINTENANCE REPLACED THE ENGINE DRIVEN FUEL PUMP WITH A SERVICEABLE UNIT. THE ENGINE WAS GROUND R	UN AND LEAK CHECKED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4R	4	R	 	A25WE   	E259	6	C	P8879	 
2002080700220	20020807	00220	EA  	2002	8	7	CA020715003      	1	20020712	G	5740		ATTACH ANGLE    			CNDAIR	CL215 	CL2151A10   	1900320	EA  										WING TO BODY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND AT ATTACH FASTENER HOLE AT LOWER SPAR LOCATION DURING NDT REQUIRED BY AD 1997-07R2 WHOSE REQUIREMENTS 	ARE EVERY 415 FLIGHT HOURS OR 1500 WATER DROPS, WHICHEVER COMES FIRST. THIS AIRCRAFT HAD 1250 WATER DROPS SINCE THE LAST	 COMPLIANCE OF THIS AD.				2	H	7	2 	4R			RT	A14EA   					 
2002080700231	20020807	00231	EA  	2002	8	7	CA020715004      	1	20020708	G	2800		CONTROL PANEL   			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     	 	NE  					REFUEL/DEFUEL	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) WHILE REFUELING USING THE COCKPIT REFUEL / DEFUEL PANEL, THE PANEL FAILED AND WAS FOLLOWED BY A STRONG ELECTRICAL 	SMELL. AIRPLANE DEPOWERED.COCKPIT REFUEL/DEFUEL PANEL REPLACED. AIRCRAFT RETURNED IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2002080700232	20020807	00232	EA  	2002	8	7	CA020715005      	1	20020710	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			22903	17464							(CAN) CO-PILOT SIDE WINDOW CRACKED DURING FLIGHT AT 5000 FEET. DIVERTED FLIGHT TO KOLN, GERMANY.SIDE WINDOW REPLACED. AI	RCRAFT RETURNED IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002080700235	20020807	00235	EU  	2002	8	7	CA020715007      	1	20020715	G	2797		WIRE HARNESS    			ISRAEL	1124  	1124        	4500102	EU  										CONTROL COLUMN	CHAFED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, AN ELECTRICAL SHORT WAS NOTICED AT THE BASE OF THE PILOTS CONTROL COLUMN. WIRING BUNDLE RUNNING	 UP THE CONTROL COLUMN WAS CHAFING ON THE STRINGER TO WHICH THE CONTROL COLUMN IS MOUNTED. THE CO-PILOTS COLUMN WAS INSP	ECTED AND SIMILAR CHAFING WAS NOTICED. WIRING WAS REPAIRED AND RE-LOCATED TO INSURE CLEARANCE DURING MOVEMENT OF THE COL	UMN. CARE MUST BE TAKEN WHEN SECURING THE WIRE BUNDLES TO INSURE CLEARANCE DURING MOVEMENT OF THE CONTROL COLUMNS.			2	M	7	2 	4F			 	A2SW    					 
2002080700241	20020807	00241	NM  	2002	8	7	CA020715010      	1	20020328	G	3246	314354	WHEEL           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) NR 4 MAIN WHEEL FAILED DURING TAXI OUT IN BATHHURST (ZBF)FOR TAKE OFF.WHEEL WAS JUST INSTALLED AND HAD ZERO TIME O	N WHEEL SINCE INSTALLATION. THE OUTER FLANGE SEPERATED FROM THE WHEEL.WHEEL HALF SENT TO GOODRICH FOR ANALYSE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002080700253	20020807	00253	EA  	2002	8	7	CA020717001      	1	20020715	G	5520	KS4	BEARING         			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ELEVATOR	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION FOUND THAT THE CENTER BEARING ON THE RT ELEVATOR WAS MISSING.						1	H	7	1 	3T	4	T	 	A806    	E4EA				 
2002081900005	20020819	00005	EU  	2002	8	19	CA020717002      	1	20020716	G	2131		CONTROLLER      			AIRBUS	320   	A320212     	3930322	EU  	CFMINT	CFM56 	CFM565A3    	 	NE  					CABIN PRESSURE	MALFUNCTIONED   	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN LEVEL FLIGHT, FL350, FELT PRESSURE CHANGE.  ECAM INDICATION, CABIN CLIMB RATE OF 700 FPM. PRESSURE PAGE ACCESS 	TO ASSESS RATE RAPIDLY INCREASED TO 1100 FPM.  EMERGENCY DESCENT INITIATED, CABIN RATE INCREASE TO 1500 FPM.  EXCESS CAB	IN ALT ECAM ACTIVATED AND ACTIONED.  DITCH BUTTON SELECTED ON THEN OFF AS OUTFLOW VALVE APPEARED IN NORMAL POSITION.  PR	ESSURE SELECTED TO MANUAL AND VALVE CLOSED WHEN SELECTED.  CABIN PRESSURE CONTROL REGAINED AT APPROX FL240. CABIN RATE W	ENT TO -2800 IN DESCENT.  AIRCRAFT LEVELED AT 16 000, ALL SYSTEMS AND PRESSURE APPEARED NORMAL.  FLIGHT CONTINUED ENROUT	E TO YWG	2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002073000133	20020730	00133	SW  	2002	7	30	CA020718008      	1	20020623	G	3213		SUPPORT         	BELL        	205050403   	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					SKID TUBE	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) AFTER LANDING THE AIRCRAFT, THE PILOT HEARD A LOUD BANG. THE AIRCRAFT DID NOT MOVE AND THERE WAS NO INDICATON OF A	NY MALFUNCTION ON THE INSTRUMENTS. THE PILOT OPENED THE CREW DOOR AND SAW THE RT SKID TUBE SLIPPED OUT TO THE RIGHT. INS	PECTION REEALED THAT THE FORWARD CROSSTUBE HAD SNAPPED IN HALF AT THE RT SUPPORT POSITION. THE BROKEN CROSSTUBE WAS REMO	VED AND A NEW CROSSTUBE WAS INSTALLED.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002080700264	20020807	00264	CE  	2002	8	7	CA020718009      	1	20020624	G	5530	04311481	FITTING         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	VERTICAL STAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				10919							(CAN) ON PRE-FLIGHT INSPECTION THE PILOT NOTICED A CRACK ON THE LEFT VERTICAL FIN ATTACH BRACKET. WHEN MAINTENANCE REMOV	ED THE BRACKET IT WAS FOUND BROKEN THROUGH. THE BRACKET WAS REPLACED WITH NEW AND NEW HARDWARE USED. THE RIGHT BRACKET W	AS REMOVED CLEANED AND INSPECTED NO FAULT FOUND REINSTALLED USING NEW HARDWARE. THE REMAINING AIRCRAFT IN THE FLEET WERE	 INSPECTED WITH NO FAULTS FOUND.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002080700265	20020807	00265	EA  	2002	8	7	CA020718010      	1	20020628	G	5711		SPAR            			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	O540A1C5    	41532	EA  					CENTER WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WING SPAR CENTRE SECTION LOWER FORWARD CAP ANGLE VERTICAL FLANGE LEG WHERE RIVETED TO SPAR WEB HAS 25 PERCENT LOSS	 OF THICKNESS IN SEVERAL AREAS PROBABLY DUE TO INTERGRANULAR STRESS CORROSION. NO STRUCTURES REPAIR MANUAL EXISTS FOR TH	ICKNESS LIMITS. ANOTHER WING WAS CHECKED AND IT HAS MORE SEVERE CORROSION THICKNESS LOSS. CONSIDER THIS A SAFETY CONCERN	 ON THIS AGING AIRCRAFT.			1	H	7	1 	3O	3	O	 	A7EA    	E295				 
2002080700270	20020807	00270	NE  	2002	8	7	CA020719004      	3	20020712	G	6110	53216	BEARING RACE    			AYRES 	S2    	S2RNORMAL   	7630202	SO  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D*        	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER WAS REPORTED TO BE STICKING, AND UPON TEARDOWN OF THE PROPELLER IT WAS NOTED THAT THE CAP RACE WAS CRACK	ED. AS A RESULT THE CWT SHAFT WAS WORN BEYOND USE. OTHER FINDINGS WERE TWO BROKEN CWT. PINS IN THE CWT BRACKET, ONE WORN	 CHAFING RING, AND WORN BARREL SUPPORT BLOCKS. ALL THE ABOVE PARTS WERE REPLACED, PROP WAS ASSEMBLED LOCKED, AND BALANCE	D.			1	L	7	1 	3R	3	R	NC	A3SW    	5E2	5	C	P257	 
2002080700271	20020807	00271	CE  	2002	8	7	CA020719005      	1	20020627	G	5753	95160000604	SKIN            			BEECH 	55    	95A55       	1152704	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLETING A 100 HR INSPECTION THE LEADING EDGE SKIN OF FLAP WAS FOUND CRACKED AT ACTUATOR ATTACH POINT.CRAC	KS EXTENDED INBOARD & OUTBOARD APPROXIMATELY 1INCH FROM THE FORWARD ATTACHMENT HOLE FOR FLAP ACTUATOR. - CRACKS WERE DET	ECTED AFTER CLEANING FLAPS.- CRACKS WERE ONLY VISIBLE WHILE FLAPS EXTENDED.- CRACKS WERE VISIBLE BEST FROM BELOW LOOKING	 AFT.			1	L	7	2 	3O	3	O	 	3A16    	3E1	5	C	P911	 
2002080700272	20020807	00272	CE  	2002	8	7	CA020719006      	1	20020710	G	5541	9763000023	SPAR            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PHASE 2 INSPECTION IT WAS NOTED THAT THE RUDDER SPAR WAS CRACKED APPROXIMATELY 1.3 INCH, WHERE THE CENTRE	 HINGE BRACKET ATTACHES. THE CRACK WAS RUNNING VERTICALLY ALONG THE LT NUT PLATE FOR ATTACHING THE HINGE BRACKET. UPON R	EMOVAL OF THE SPAR IT WAS FOUND THAT THE HINGE DOUBLER P/N 96-630000-307 WAS ALSO CRACKED IN THE SAME PLACE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002080700273	20020807	00273	EA  	2002	8	7	CA020719007      	2	20020704	G	8520	11F20022D3	CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CRANKSHAFT CRACKED - PIECE FROM COUNTERWEIGHT BROKEN - MISALIGNMENT CAUSED CAMSHAFT TO SHEAR 2 VALVE FACES DAMAGED	.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002080700275	20020807	00275	CE  	2002	8	7	CA020719009      	1	20020612	G	7120	J951358	MOUNT           			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	DEFORMED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE MOUNTS FOUND DEFORMED AND SOFT ALLOWING FOR EXCESSIVE MOVEMENT OF ENGINE ON MOUNTS.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2002080700276	20020807	00276	SO  	2002	8	7	CA020722001      	1	20020718	G	3250	4025700402377	SCISSORS        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN DOING A WALK AROUND THE PILOT NOTICED THE NUT, PART OF THE BOLT AND THE FORWARD LUG OF THE SCISSOR LINK WAS M	ISSING. CORROSION ON THE FACE OF BREAK INDICATES PRIOR CRACKS AT BREAK LOCATION.INITIATED INSPECTION OF SCISSOR LINKS AN	D HARDWARE ON SAME AIRCRAFT TYPE IN FLEET.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002081200013	20020812	00013	GL  	2002	8	12	CA020722005      	3	20020719	G	6110	A2807	PIN             	HARTZL      	HCE3YR2ATF  	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						DJ11753A					(CAN) CUSTOMER COMPLAINED THAT PROPELLER DURING FLT WOULD NOT GO ALL THE WAY OUT OF FEATHER, INTO LOW PITCH. WHILE ON GR	OUND TRIED TO MOVE PROP TO LATCH WITH PADDLE, BUT ONLY ABLE TO MOVE IT PART WAY. UPON OUR REMOVAL OF LOW PITCH STOP IT N	OTED THAT A3205 L.P. SCREW TURNED OUT & JAMMED BETWEEN LP STOP&PITCH CHANGE ROD. CYLINDER THEN REMVD&BROKEN A2807 LATCH 	PIN FOUND LAYING IN PISTON. PINS WERE REPL, CYLINDER INST, & ANGLES WERE SET. UPON SETTING FEATHER ANGLES THEY WERE FOUN	D TO BE SHORT ON TRAVEL, HUB NUTS WERE LOOSENED BLADE TRAEL ADJUSTED,&NUTS TIGHTENED. ASSY OF PROP COMPLETED,&PROP RETUR	NED TO CUSTOMER.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002073000134	20020730	00134	NM  	2002	7	30	CA020722007      	1	20020708	G	3260		PROXIMITY SWITCH			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	OUT OF ADJUST   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) DEPARTING YZF THE NLG INTRANSIT LIGHT WOULD NOT EXTINGUISH AFTER GEAR UP SELECTED. MTCE OBSERVED A CONTAMINATED PR	OXIMITY SWITCH SENSOR, DEFECT REMAINED AFTER CLEANING. THE UPLOCK POXIMITY SWITH WAS REPLACED AND STRIKE PLATE ADJUSTED.	 AIRCRAFT WAS GROUND FUNCTION TESTED SERVICEABLE AND TEST FLOWN BEFORE RETURN TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002081900007	20020819	00007	SO  	2002	8	19	CA020722012      	1	20020711	G	6121	582855	HOUSING         			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	PROP VALVE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) ENROUTE YUX FROM YUW NR 4 ENGINE WOULD NOT SYNC. PRECAUTIONARY ENGINE SHUTDOWN CARRIED OUT. MAINTENANCE REPLACED T	HE PROP VALVE HOSUING. THE AIRCRAFT WAS GROUND CHECKED SERVICEABLE BEFORE RETURN TO SERVICE.					2	H	7	4 	4T	4	T	 	A1SO    	E282	6	C	P906	 
2002081200018	20020812	00018	SW  	2002	8	12	CA020722013      	1	20020630	G	5711		SPAR            			BBAVIA	7     	7EC         	2110120	SW  	CONT  	C90   	C9012F      	17009	SO  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ALL 4 SPARS REPLACED DUE TO SMALL CRACKS AT NAIL HOLES, EDGE OF PLYWOOD REINFORCING AS A PRECAUTIONARY MEASURE. NO	 LARGE CRACKS FOUND.4 NEW METAL SPARS INSTALLED.					1	H	7	1 	3O	3	O	 	A759    	E252				 
2002081200020	20020812	00020	CE  	2002	8	12	CA020722015      	1	20020626	G	5330	AK172168	SKIN            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11000								(CAN) WHEN STEPPING ONTO FUSELAGE STEP, THE STEP HAD MORE 'GIVE' THAN NORMAL. WHEN STEP WAS UNBOLTED, CRACKS WERE SEEN I	N THE FUSELAGE SKIN. ALL COMPANY 172S & 172RGS WERE CHECKED AND ALL HAD CRACKS DEVELOPING TO SOME DEGREE. IT SEEMS THAT 	THE INSTALLATION ISN'T STRONG ENOUGH AND AN EXTRA DOUBLER OUGHT TO BE INSTALLED UNDER THE MOUNTING NUTS.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002082300084	20020823	00084	CE  	2002	8	23	CA020724002      	1	20020702	G	2824	36600	CHECK VALVE     			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE331625   	 	WP  					FUEL SYSTEM	OPEN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING A FLIGHT WHILE UTILIZING THE AUXILIARY RESOURCES, A CHECK VALVE STAYED PARTIALLY OPEN. THE MAIN RESERVOI	R TRANSFERRED TO THE AUXILIARY AND THE FUEL (TOO FULL) EXITED BY THE VENT AND LEAKED TO THE GROUND. THE PILOT ACTIVATED 	THE BOOST PUMP WITH AUXILIARY TRANSFER AND THE PROBLEM WAS RESOLVED.				1	L	7	2 	4T	4	T	 	A14CE   	E2WE				 
2002082300087	20020823	00087	SW  	2002	8	23	CA020724005      	1	20020625	G	2820		LINE            			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL DIST	CORRODED        	W				K				NONE                    				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		IN	INSP/MAINT     	1			CA											(CAN) - DURING ANNUAL INSPECTION, FOUND FUEL ODOR IN CABIN AND FUEL STAIN ON LOWER FUSELAGE AREA.  CABIN SIDE PANEL REMO	VED FOR INSPECTION AND FOUND BOTH RIGID FUEL LINE FROM WING FUEL TANK TO AIRCRAFT FUEL STRAINER CORRODED AND LEAKING FUE	L. NEW RIGID FUEL LINE INSTALLED.				1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2002081200036	20020812	00036	CE  	2002	8	12	CA020724010      	1	20020723	G	3222	04425037	FORK            	CESSNA      	044250413   	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  WITH THE PAINT CLEANED AWAY FROM THE UPPER OUTSIDE RADIUS OF THE FORK, THE TECHNICIAN WAS ABLE TO DETECT THE CRAC	K WITH A GOOD LIGHT AND 10 X MAGNIFIER. THE CRACK RUNS HORIZONTALLY AND IS ABOUT 1-2 INCHES LONG. THE DEFECTIVE PART HAS	 BEEN REMOVED FROM SERVICE AND REPLACED WITH A FACTORY NEW PART.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002073000135	20020730	00135	NM  	2002	7	30	CA020724012      	1	20020722	G	2910	NAS16126	O-RING          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	CUT             	W				D				RETURN TO BLOCK         				J	K		WARNING INDICATION        	FLUID LOSS                		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI AIRCRAFT LOST NR 1 HYDRAULIC PRESSURE, AND QUANITY WENT TO ZERO. O-RING REPLACED AT UNION AT RUDDER PR	ESSURE REGULATOR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002073000136	20020730	00136	EA  	2002	7	30	CA020725002      	1	20020529	G	2910		LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYDRAULIC SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) LOSS OF SYS 1 HYDRAULIC FLUID DURING FLIGHT. PIN HOLE FOUND ON PUMP RETURN LINE. RETURN LINE REPLACED						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002081200046	20020812	00046	NE  	2002	8	12	CA020725003      	2	20020725	G	8500	K60516	PIN             			DHAV  	DHC3  	DHC3        	2800202	EA  	WSK   	ASZ62 	ASZ62IRM18  	 	NE  					NR 9 CYLINDER	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE PIN FRACTURED IN THE AREA OF THE PIN THE RUNS INSIDE THE LINK ROD BUSHING. THE FRACTURE APPEARS TO HAVE ORIGIN	ATED INSIDE THE CASTING AS A RESULT OF A FLAW IN THE CASTING OR FROM AN INCLUSION OR SOME OTHER INHERENT DISCREPANCY IN 	THE CASTING.THE EDGES OF THE FRACTURED PIN SHAVED THE BRASS LINK ROD BUSHING ALMOST TO THE LINK ROD PARENT MATERIAL AND 	CONTAMINATED THE ENTIRE ENGINE WITH BRASS.THE PIN IS BEING FORWARDED TO THE MANUFACTURER FOR FURTHER INVESTIGATION.			1	H	7	1 	3R	3	R	 	A815    	E10NE				 
2002083000233	20020830	00233	NM  	2002	8	30	CA020725004      	1	20020604	G	3040		WINDSHIELD      			BOEING	737   	7372T7      	1384482	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					COCKPIT	ARCED           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA						91121H1125					(CAN) FIRST OFFICER NR 1 WINDSHIELD ARCING,  UPPER MID SECTION DISCOLOURED BY WIRING LEADS REPLACED WINDSHIELD						2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2002081900037	20020819	00037	EA  	2002	8	19	CA020725005      	1	20020719	G	2420	764510	PLUNGER         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ADG ARM	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE VALIDATION OF AMM TASK 24-23-01-720-803 IAW BOMBARDIER ENGINEERING TDS 601R-0566, WE DAMAGE THE ADG BAC	K PLATE AND BLADE LOCK PLUNGER OCCURRED. THE DAMAGE OF THE ADG WAS CAUSED BY AN IMPROPERLY CRIMPED LOCK TABFROM THE FACT	ORYLOCATED BETWEEN THE SELF LOCKING NUT AND THE BLADE LOCK PLUNGER OF THE ADG.  DURING THE TESTING THE SELF LOCKING NUT 	SLACKENED OFF ALLOWING THE ENGAGEMENT LENGTH OF THE PIN TO INCREASE.  THE PROTRUDING PIN IMPACTED THE ADG WHILE THE ADG 	WAS ROTATING.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002081200047	20020812	00047	SO  	2002	8	12	CA020725006      	1	20020707	G	8011	641368	BEARING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	MCAULY	3AF34C	3AF34C503   	GL  	STARTER SHAFT	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ON A TRAINING FLIGHT IN CRUISE PILOTS OBSERVED LOW OIL PRESSURE LIGHT ILLUMINATION ON THE LT ENGINE AND NO OIL PRE	SSURE ON THE GAUGE. THE PROPELLER FEATHERED ON ITS OWN DUE TO NO OIL PRESSURE. ENGINE WAS SHUT DOWN ACCORDING TO THE EME	RGENCY PROCEDURES AND THE AIRCRAFT RETURNED AND LANDED AT THE AIRPORT OF DEPARTURE WITHOUT INCIDENT. UPON INSPECTION IT 	WASFOUND THAT A NEEDLE BEARING FROM THE STARTER CLUTCH ASSEMBLY HAD MADE ITS WAY TO THE OIL PUMP GEARS AND SUBSEQUENTLY 	JAMMING THE GEARS SHEARING THE PUMP DRIVE MAKING THE PUMP INOPERATIVE.		1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2002073000137	20020730	00137	EA  	2002	7	30	CA020725007      	1	20020604	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CAPTAIN,S WINDSHIELD CRACKED ON DESCENT. WINDSHIELD REPLACED						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002081200054	20020812	00054	CE  	2002	8	12	CA020725013      	1	20020717	G	5311	5042006653	FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TWO CRACKS STARED FROM THE RADIUS OF THE LOWER FLANGE. THE FORWARD CRACKED ENDED AT LIGHTNING HOLE WHILE THE OTHER	 CRACK ENDED BEHIND THE AFT LIGHTNING HOLE. IPL 53-10-10-37					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002081200063	20020812	00063		2002	8	12	CA020725014      	4	20020613	G	3417	HG480B13	ADC             			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AUTO FLIGHT	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AUTOPILOT ENGAGED IN CRUISE,UNABLE TO UNFREEZE MANUALLY,LEFT WING LEVEL TO A SLIGHT RIGHT BANK. AILERON CONTOL LOS	T-FROZEN TILL AUTO PILOT RELEASED.CENTRAL AIR DATA COMPUTER REPLACED P/N HG480B13 S/N P-529					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002081900059	20020819	00059	CE  	2002	8	19	CA020726005      	1	20020724	G	2610	302158	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) CREW REPORTED A RIGHT ENGINE FIRE LIGHT IN FLIGHT.THE WARNING LIGHT ILLUMINATED, WENT OUT FOR A BRIEF PERIOD AND T	HEN CAME ON AGAIN. THERE WAS NO PHYSICAL EVIDENCE OF A FIRE AND ALL ENGINE PARAMETERS WERE NORMAL. THE ENGINE WAS SHUT D	OWN AND THE FIRE BOTTLE DISCHARGED. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTION DETERMINED THAT THE AFT	 LOWER FIRE DETECTOR WAS DEFECTIVE. TIME ON PART UNKNOWN.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2002082300089	20020823	00089	CE  	2002	8	23	CA020726008      	1	20020618	G	7603	5038901229	THROTTLE CABLE  			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA											(CAN) APPROXIMATELY 6 INCHES FROM ENGINE END THROTTLE CABLE BROKE. REPLACED THROTTLE CABLE.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002081200077	20020812	00077	NE  	2002	8	12	CA020726011      	2	20020716	G	8530	K60516	PIN             			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	ENGINE	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) - ENGINE MAKING CLICKING SOUND SIMILAR TO EXCESSIVE VALVE CLEARANCES.  OIL SCREEN INSPECTED AND BRASS PARTICLES FO	UND.  VALVE CLEARANCES ADJUSTED AND OIL SYSTEM FLUSHED.  ENGINE GROUND RUN AND ENGINE NOISE STILL EXISTED.  SPARK PLUGS 	PULLED AND EXAMINED AND NR 9 CYLINDER WAS DETERMINED TO BE BURNING OIL. CYLINDERS REMOVED AND BROKEN WRIST PIN FOUND.				1	H	7	1 	3R	3	R	 	A815    	5E2	6	C	P719	 
2002081900063	20020819	00063	SW  	2002	8	19	CA020726017      	1	20020701	G	6210		BLADE           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					MAIN ROTOR	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LT WING TIP OF A CL-415 WATER BOMBER CONTACTED THE FORWARD ROTOR BLADE OF THE 205. THE 205 WAS PARKED AND TIED	 DOWN. THE CL-415 WAS DESCRIBED AS TRAVELLING AT A "SLOW TAXI SPEED". ONE BLADE SUSTAINED MINOR DAMAGE (REPAIRABLE) AT T	IP. NO OTHER DAMAGE WAS FOUND WITH A VISUAL INSPECTION. BELL HELICOPTER PRODUCT SUPPORT ISSUED A LETTER STATING A VISUAL	 INSPECTION WAS ALL THAT WAS REQUIRED. THE DAMAGED BLADE WAS REPLACED. DURING THE TRACK AND BALANCE PROCEDURE LATERAL BA	LANCE COULD NOT BE REDUCED BELOW 0.80 IPS. AS A PRECAUTION THE M/R HEAD, M/R MA5, TRANSMISSION AND ALL TXSM MOUNTS WERE 	REPLACED. AIRCRAFT WAS EASILY BALANCED. SUSPECTED BENT MAST.	1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002081900064	20020819	00064	EA  	2002	8	19	CA020726019      	2	20020703	G	7322	04500704	BUTTERFLY VALVE 	CESSNA      	04500522    	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235C2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	CARBURETOR	SEPARATED       	W				A				UNSCHED LANDING         				R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA											(CAN) THE SEAL FOR THE BUTTERFLY VALVE IN THE CARBURETOR AIR BOX (FOR CARBURETOR HEAT) SEPARATED AND WAS SUCKED UP INTO 	THE CARBURETOR. THIS CAUSED THE ENGINE TO LOSE PERFORMANCE WHICH MADE THE PILOT RETURN FOR A LANDING. TOWER REPORTED SMO	KE (LIKELY FROM A RICH MIXTURE) TAILING THE AIRCRAFT. UNEVENTFUL LANDING. AIRCRAFT REMOVED FROM SERVICE. NOW REPAIRED AN	D BACK ON LINE.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002081900065	20020819	00065	CE  	2002	8	19	CA020726020      	1	20020711	G	2731	03103625	SCREW           	CESSNA      	12601481    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ACTUATOR	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE TRIM TAB ON THE HORIZONTAL STABILIZER STARTED TO FLUTTER CAUSING VIBRATION IN THE CONTROL	 COLUMN. TRIM MECHANISM JAMMED IN THE FULL NOSE UP SETTING. PILOT WAS FORCED TO OVERRIDE TRIM SETTING WITH CONTROL INPUT	S AND LAND ON A NEARBY LAKE.SUBSEQUENT INSPECTION REVEALED THE SCREW ASSEMBLY BROKEN IN HALF AT THE START OF THE THREADE	D SECTION. AMO DIRECTOR OF MAINTENANCE STATES VERY UNUSUAL FAILURE. BROKEN PART IS BEING HELD FOR INSPECTION IF REQUIRED	.		1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002080700127	20020807	00127	WP  	2002	8	7	CA020729001      	1	20020719	G	5510	369D2363312	TIP CAP         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					HORIZONTAL STAB	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) WHILE IN A STEEP DESCENT THE PILOT OBSERVED THE RIGHT HAND TIP CAP (WINGLET) GO PAST HIM AND HIT THE GROUND IN THE	 LANDING / WORKSITE. THE AIRCRAFT WAS LESS THAN 300 FEET AGL. THE AIRCRAFT CONTINUED DESCENT AND MADE A NORMAL POWER ON 	LANDING. RECOVERY AND INSPECTION OF THE FAILED PART INDICATE VERY RECENT CRACKING AT THE FORWARD EDGE AIRFLOW OF THE ATT	ACHED WINGLET CAUSED TEARING OF THE REMAINDER OF THE STRUCTURE. THERE IS NO INDICATION OF A BIRD OR OTHER ITEM CONTACTIN	G THE WINGLET.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002081900066	20020819	00066	SW  	2002	8	19	CA020729002      	1	20020711	G	6240		INDICATOR       			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					MAIN ROTOR	FAILED          	W				B				EMER. DESCENT           				O			OTHER                     			HO	HOVERING       	1			CA											(CAN) FROM REPORTS: THE AIRCRAFT WAS HOVERING WITH A WATER BUCKET OVER A FIRE. ROTOR SPEED DECAYED AND PILOT MADE A FORC	ED LANDING IN A CLEARING. THE AIRCRAFT LANDED VERY HARD AND ROLLED ON TO ITS RIGHT SIDE. PILOT CRAWLED OUT AND SUSTAINED	 MINOR INJURIES. THE AIRCRAFT WILL MOST LIKELY BE DECLARED A "WRITE OFF". CAUSE IS UNKNOWN AND THE T.S.B. IS CURRENTLY I	NVESTIGATING THE INCIDENT. OTTAWA T.C.C. (PMI) WAS INFORMED VERBALLY FRIDAY, JULY 12, 2002.			1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002081200107	20020812	00107	GL  	2002	8	12	CA020729003      	3	20020717	G	6111		BLADE           			CESSNA	140   	140         	2071602	CE  	CONT  	C85   	C8512       	17008	SO  	MCAULY	1B90	1B90*       	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  EXTRA WORK REQUIRED TO REMOVE CORROSION CARRIED OUT: AN OVERHAUL. AS	 PER MCCAULEY MANUAL 730720					1	H	7	1 	3O	3	O	NC	A768    	E233	5	N	P842	 
2002082300090	20020823	00090	GL  	2002	8	23	CA020729004      	1	20020716	G	5540	2055450300	HINGE BRACKET   			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					VERTICAL STAB	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON BOTTOM LEFT WELD OF SUPPORT BRACKET.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2002082300092	20020823	00092	SO  	2002	8	23	CA020729005      	1	20020703	G	5280	42059007	HINGE           			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED 100 HOUR EVENT NR 2 LANDING GEAR INSPECTION, CRACK FOUND ON LEFT HAND FORWARD MAIN LANDING GEAR O	UTBOARD DOOR HINGE. CAUSE DETERMINED TO BE FATIGUE.					1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2002081900070	20020819	00070	CE  	2002	8	19	CA020729006      	1	20020711	G	3212	65D1	COVER           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					FLOAT	DEPARTED        	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) UPON LIFTING OFF THE WATER THE RT FLOAT HATCH - DEPARTED THE FLOAT - CREASING RT FUSELAGE SKIN AHEAD OF BULKHEAD A	T STATION 108.0 AND HIT RT LEADING EDGE OF HORIZONTAL STABILIZER.					1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2002081200109	20020812	00109	EA  	2002	8	12	CA020729008      	2	20020716	G	7322	RSA5AD1	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL CONTROL	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) PILOT REPORTED THAT THE ENGINE QUIT WHEN LANDING AND THROTTLE PULLED TO FULL IDLE.  GROUND RUN CONFIRMED PROBLEM. 	MIXTURE CONTROL ADJUSTED TO GET PROPER RISE AT IDLE CUT-OFF - RUN UP AND FULL IDLE OPERATION NOW NORMAL.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002082300093	20020823	00093	CE  	2002	8	23	CA020729009      	1	20020627	G	3230	4013004	BRUSHES         			BEECH 	100   	B100        	1152919	CE  										MLG MOTOR	FAILED          	W				L				ABORTED APPROACH        				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA											(CAN) WHILE LANDING GEAR WAS BEING EXTENDED DURING AN APPROACH, LANDING GEAR DID NOT COME OUT AFTER A FEW TRIES (GEAR UP	, GEAR DOWN), IT DID FINALLY EXTEND. THE AIRCRAFT WAS CHECKED AND IT SEEMED THAT THE ENGINE WAS FORCING DURING RETRACTIO	N. THE BRUSHES WERE CHECKED AND 2 OUT OF 4 WERE FOUND FAILED. THESE WERE REPLACED. A FEW MORE RETRACTIONS WERE TRIED AND	 EVERYTHING RETURNED TO NORMAL.			1	L	7	2 	4T			 	A14CE   					 
2002081900087	20020819	00087	CE  	2002	8	19	CA020729011      	1	20020716	G	3246	C30057	WHEEL           			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSEPCTION IT WAS DISCOVERED THAT THE HUB WAS CRACKED IN THE AREA OF THE GREASE SEAL RETAINING RING. THE CRAC	K IS ONLY ABOUT 3/8 INCH LONG AND TRAVELS PARALLEL TO THE RETAINING RING GROOVE JUST BELOW IT. HUB WAS REPLACED.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002082200032	20020822	00032	EU  	2002	8	22	CA020729014      	1	20020614	G	5610	9598110112	WINDOW          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REMOVAL OF THE MAIN RT WINDSCREEN, IT WAS NOTICED THAT ONE OF LOWER SECTION SCREW ATTACHMENT LUGS ON THE RT	 SIDE WINDOW WAS CRACKED. THE SIDE WINDOW REQUIRED REPLACMENT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002082200037	20020822	00037	SW  	2002	8	22	CA020730005      	1	20020716	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A658        	17003	SO  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WING SPARS, RIGHT FRONT WING WITH SMALL CRACKS FROM NAIL HOLES VARIOUS LOCATIONS. RIGHT REAR SPAR WITH CRACK FROM 	TIP DAMAGE PREVIOUS.BOTH SPARS REPLACED.					1	H	7	1 	3O	3	O	 	A759    	E205				 
2002082200038	20020822	00038	CE  	2002	8	22	CA020730006      	1	20020729	G	2434	ES4145	ROTOR           	FORD        	DOFF10300J  	CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  	MCAULY	2D34C	B2D34C211   	GL  	SLIP RINGS	OUT OF TOLERANCE	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA						A154280					(CAN) NEW ROTOR WAS INSTALLED AT OVERHAUL. AFTER 374 HRS, UNIT FAILED TO PRODUCE OUTPUT. ON DISASSEMBLY AND INSPECTION, 	ONE BRUSH WAS FOUND COMPLETELY WORN OUT, AND THE BRUSH SHUNT BRAIDED LEAD WAS CHAFED IN TWO.  FOUND THAT THE SLIP RINGS 	ON THE ROTOR WERE OUT OF CONCENTRICITY BY 0.005  OF AN INCH TIR. THIS CONDITION WOULD CAUSE RAPID BRUSH WEAR.  WHEN THE 	NEW ROTOR WAS INSTALLED, THE WORK ORDER DID NOT INDICATE THAT THE SLIP RINGS WERE INSPECTED FOR RUNOUT (TIR). THEY WERE 	EITHER OUT AT THAT TIME BUT IT WAS NOT DETECTED, OR THE SLIP RING ASSEMBLY HAS MOVED ON THE ROTOR SHAFT WHILE IN SERVICE	.	1	H	7	1 	3O	3	O	 	A13CE   	E286	5	C	P7EA	 
2002081200110	20020812	00110	SO  	2002	8	12	CA020731002      	2	20020723	G	7414		LEAD            	CONT        	O470L       	CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					MAGNETO	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						671877L					(CAN) DURING RUN-UP AFTER ANNUAL INSPECTION LT MAGNETO GROUNDED OUT.  INSPECTION FOUND "P" LEAD INTERMITTENT.  ON FLEXIN	G RT "P" LEAD IT WAS ALSO FOUND TO BE INTERMITTENT.  FURTHER EXAMINATION DISCLOSED DETERIORATED INSULATION CLOSE TO ENTR	Y TO MAGNETOS ALLOWING GROUNDING ON BRAIDED SHIELDING.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002082200041	20020822	00041	EU  	2002	8	22	CA020731003      	1	20020723	G	7820		MUFFLER         			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ENGINE EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A FIRST 100 HOUR INSPECTION ON A NEW AIRCRAFT, THE NR 3 CYLINDER EXHAUST PIPE WAS FOUND TO BE CRACKED WHERE	 IT IS WELDED TO THE MUFFLER. THE CRACK WAS APPROXIMATELY 1.5 INCHES LONG AROUND THE CIRCUMFERENCE OF THE PIPE. THIS PIP	E HAS A STRUT ATTACHED TO IT BRACING THE PIPE TO ONE OF THE INJECTOR SERVO MOUNTING STUDS. IT IS SUSPECTED THAT IF THE S	TRUT IS IMPROPERLY ADJUSTED THERE IS STRESS PUT ON THIS PIPE, AND WITH THE HEATING AND COOLING OF THE EXHAUST SYSTEM IT 	MAY PRODUCE CRACKING.		1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002081600158	20020816	00158	NM  	2002	8	16	CA020731013      	1	20020709	G	2750	BACP30K15	CONTROL CABLE   			BOEING	737   	7372T7      	1384482	NM  	PWA   	JT8   	JT8D17      	52049	NE  					TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 5 FLAP ACTUATOR ROLLER TRACK DISENGAGED AND WENT THROUGH THE INBOARD SIDE OF NR 5 FLAP FAIRING.  NR 5 FLAP TRAC	K FITTING FOUND DAMAGED (SNAPPED) DUE BOOM CABLE BROKEN.  CABLE, TRACK FITTING,  PULLEYS,  BOOM ASSY, AND CAM FOLLOWER G	UARD ADJUSTED AS PER AMM. SYSTEM CERTIFIED AND CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2002082200087	20020822	00087	CE  	2002	8	22	CA020731014      	1	20020624	G	2720	NAS428H37	STOP            			CESSNA	150   	150J        	2071820	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C172	1C172TM     	GL  	RUDDER	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UPON COMPLETING INSPECTION OF RUDDER STOPS PER AD CF-2000-20, IT WAS FOUND THAT THE RUDDER STOPS WERE BOTH MISSING	. THERE WERE NO HOLES IN THE TAILCONE SKIN WHERE THE STOPS SHOULD HAVE BEEN, BUT THE ANCHOR NUTS WERE RIVETS TO THE BULK	HEAD. THIS SKIN WAS REPLACED (ACCORDING TO A WORK REPORT FOUND IN THE LOGBOOK) IN 1978 WHILE THE AIRCRAFT WAS IN MAJOR R	EPAIRED.OBVIOUSLY, THIS AIRCRAFT WAS FLOWN WITHOUT RUDDER STOPS FOR SOME 24 YEARS AND 1365 HOURS.			1	H	7	1 	3O	3	O	 	3A19    	E274	5	N	P910	 
2002082200091	20020822	00091	CE  	2002	8	22	CA020731017      	1	20020731	G	3220	280X4	TUBE            			CESSNA	305   	305         	2074001	CE  	CONT  	O470  	O47011      	17026	SO  					TAIL WHEEL ASSY	SPLIT           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING SERVICING OF TAILWHEEL,  A NEW TUBE WAS BEING INSTALLED.  THE TUBE WAS INFLATED TO CHECK FOR LEAKS (STANDAR	D PROCEDURE) AND IT WAS NOTICED THAT THE SIDE OF THE TUBE STARTED TO SPLIT.  8 TUBES WERE PURCHASED AT THE SAME TIME.  A	LL OF THEM HAVE THE SAME DEFECT.  THE TUBES ARE BEING RETURNED TO THE SUPPLIER FOR CREDIT. THE TUBES WERE PURCHASED IN J	ULY 2002.			1	H	7	1 	3O	3	O	 	EXPA1H71	E269				 
2002100400082	20021004	00082	NM  	2002	10	4	CA020801001      	1	20020714	G	2761	684D1007	ACTUATOR        			BOEING	767   	767383      	1385214	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					SPEED BRAKE SYS	BINDING         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) SPOILER LEVER FEELS TO HAVE MORE TENSION (BINDING) WHEN DEPLOYING AND RETRACTING. REPLACED SPEEDBRAKE MECHANISM AN	D TESTED PER AMM 27-62-04-002-114					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2002100400083	20021004	00083	EU  	2002	10	4	CA020801002      	1	20020715	G	2730	31075217	SERVO           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					ELEVATOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) WHILE DOING OPEN PROCEDURES CALLED FOR MEL 27-93-01 A RB ELEVATOR SERVO FAILED.  AIRCRAFT REMOVED FROM SERVICE FOR	 SERVO CHANGE.  REPLACED RT BLUE ELEVATOR SERVO CONTROL AS PER AMM 27-34-51-400. OPERATION CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002100400087	20021004	00087	NM  	2002	10	4	CA020801003      	1	20020717	G	2710	550030017	ACTUATOR        			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					AILERON LOCKOUT	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) RT AILERON LOCKED OUT DURING FLIGHT AFTER LEAVING YVR. RT LOCK OUT ACTUATOR REPLACED PER AMM 27-11-44 PG 1-12 OPER	ATION CHECKED SERVICEABLE					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2002081600163	20020816	00163	CE  	2002	8	16	CA020801011      	1	20020725	G	7820		MUFFLER         			CESSNA	206   	U206D       	2073342	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	RT EXHAUST PIPE	SEPARATED       	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN)  THE MUFFLER INSTALLED MAY 27, 2002 SEPARATED AT THE BELL FLANGE (UPPER ATTACH POINT). THE TAILPIPE CLAMP REMAINED	 CONNECTED.  THE MUFFLER WAS REMOVED AND REPLACED ON JULY 4, 2002 WITH A NEW OVERHAULED MUFFLER AND NEW ATTACHING HARDWA	RE. THE AIRCRAFT WAS RETURNED TO SERVICE.  SEC 7 SUB SEC A AND B: PILOT ALERTED TOWER THAT THERE WAS SMOKE IN THE COCKPI	T AND THAT HE WAS ABORTING HIS TRAFFIC PATTERN TO LAND.			1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2002082200100	20020822	00100	CE  	2002	8	22	CA020801015      	1	20020731	G	2435		ARMATURE        			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  	MCAULY	2D34C	B2D34C219   	GL  	STARTER MOTOR	SEPARATED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REPORTED START ATTEMPT FAILED DUE TO EXCESSIVE ELECTRICAL DRAW AND STARTER MOTOR DID NOT TURN.  STARTER REMO	VED TO INSPECT AND FOUND COMMUTATOR COMPLETELY DISINTEGRATED ALONG WITH THE BRUSH BLOCKS AND HOLDER ASSY.  THE CONNECTIN	G WIRES TO THE ARMATURE WERE FOUND SEVERELY STRESSED AND BROKEN WITH THE APPEARANCE THAT THE STARTER HAD EXPERIENCED EXC	ESSIVE ROTATIONAL SPEED.  ADVISED THAT PREVIOUS PILOT HAD INDICATED A PROBLEM WITH THE BENDIX DRIVE FAILING TO DISENGAGE	 PROPERLY ON THE PREVIOUS START.		1	H	7	1 	3O	3	O	 	3A13    	E295	5	C	P7EA	 
2002082200107	20020822	00107	EA  	2002	8	22	CA020806003      	2	20020722	G	7414	10357584	GEAR            		101630052   	ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						C059701ER					(CAN) - AXLE SHAFT AND WASHER FOUND LOOSE IN DISTRIBUTOR GEAR.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2002082200109	20020822	00109	CE  	2002	8	22	CA020806004      	1	20020803	G	2910	8A12000007	TUBE            			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	HYD SYSTEM	DEFORMED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) OPERATOR PURCHASED A/C FROM COMMERCIAL OPERATOR & INHERITED PERSISTENT & ELUSIVE HYD LEAK.  AFTER TROUBLESHOOTING,	 SOURCE ISOLATED TO TWO B-NUTS NOT TIGHT.  FITTINGS WERE NOT ACCESSIBLE.   5 CYCLES LATER NR 13 HYDRAULIC LINE FAILED ON	 GEAR RETRACTION EMPTYING HYDRAULIC SYS.  A/C RETURNED FOR LANDING ON INFIELD GRASS WITH GEAR PARTIALLY RETRACTED. NO DA	MAGE TO GEAR OR FLOATS WERE ENCOUNTERED.  FAILED LINE SHOWED SIGNS OF SLEEVE COUPLING WORKING AGAINST FLAIR. IT APPEARS 	THAT WHEN B-NUT WAS CORRECTLY TORQUED IT WEAKENED FLAIR ENOUGH TO ALLOW THE AN819-5D COUPLING SLEEVE AND AN818-5D NUT TO	 SLIDE OVER THE END OF THE TUBE.	1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002082200121	20020822	00121	EA  	2002	8	22	CA020806013      	2	20020801	G	8550	71664	IDLER GEAR      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN)  DURING CLIMB OUT, THROUGH ABOUT 11,000 FT,  LT ENGINE LOST POWER. CREW NOTED LOW FUEL PRESSURE ON LT ENGINE, SELE	CTED BOOST PUMP, AND REGAINED NORMAL ENGINE OPERATION.  DIVERTED FOR A LANDING.  LT FUEL PUMP WAS REMOVED AND FOUND TO B	E FUNCTIONAL, THE PUMP DRIVE IN THE ENGINE WAS NOT ROTATING. THE REAR CASE WAS REMOVED AND THE IDLER GEAR WAS FOUND TO H	AVE LOST 5 TEETH THUS DIS-ENGAGING THE FUEL PUMP DRIVE GEARSHAFT. GEAR WAS REPLACED WITH A SERVICEABLE GEAR, ALL OTHER G	EARS AND PARTS INSPECTED AND FOUND SERVICEABLE AND THE ENGINE WAS RE-ASSEMBLED AND TESTED OK.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002082300003	20020823	00003	NE  	2002	8	23	CA020808003      	2	20020723	G	8510	39487	CASE            			GRUMAV	G21   	G21A        	3951204	SO  	PWA   	R985  	R985*       	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE A 3 INCH CRACK WAS FOUND IN THE FORWARD NOSE CASE STARTING JUST ABOVE THE OIL SUMP AND 	PROGRESSING UPWARD. THE ENGINE WAS REPLACED.					1	H	7	2 	3R	3	R	 	TC654   	5E1				 
2002082300004	20020823	00004	SO  	2002	8	23	CA020808005      	1	20020801	G	7700	URHB32E	LIGHT           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					COCKPIT	BURNED OUT      	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) DURING A RUN UP, EXPERIENCED A LOSS OF RPM OF 200 CYCLES ON THE RT MOTOR. AFTER VERIFICATION, AN INDICATOR LIGHT W	AS FOUND TO BE DEAD. 2 MONTHS AGO THE SAME PROBLEM HAPPENED WITH ANOTHER ENGINE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002082300005	20020823	00005	EA  	2002	8	23	CA020808006      	2	20020801	G	8530	AEL19001	EXHAUST VALVE   			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2G     	41508	EA  					ENGINE CYCLINDER	BROKEN          	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) AT CRUISING ALTITUDE, THE ENGINE LOST POWER. RPMS DROPPED TO 2000. INSPECTION OF NR 3 CYLINDER,  FOUND NO COMPRESS	ION.  THE EXHAUST VALVE WAS FOUND TO BE BROKEN, REPLACED THE CYLINDER.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002082300011	20020823	00011	CE  	2002	8	23	CA020812005      	1	20020811	G	2731		PIN             	CESSNA      		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	SPUR GEAR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TWO PERMANENT PINS THAT HOLD THE SPUR GEAR TO THE ROTATING SHAFT OF THE TRIM TAB ACTUATOR HAD FALLEN OUT AND WENT 	MISSING.  TRIM CONTROL WAS IMPOSSIBLE DUE TO SLIPPAGE OF THE SPUR GEAR IN THE SHAFT.  ACTUATOR REPLACED WITH NEWLY OVERH	AULED UNIT.				1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2002082300016	20020823	00016	NM  	2002	8	23	CA020813005      	1	20020721	G	2910	82970010143	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			36132	36132							(CAN) DURING WALK-AROUND FOUND HYDRAULIC LEAK NEAR NR 1 GEAR , INSPECTION FOUND NR 1 SPU PRESSURE LINE LEAKING . LINE RE	PLACED WITH TEMP FLEX LINE . AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002082300023	20020823	00023	NM  	2002	8	23	CA020813014      	1	20020806	G	5320	65453132	STRINGER CLIP   			BOEING	727   	72725C      	138400H	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C3-CHECK FOUND STRINGER CLIP CRACKED AT BS 1030 AT STRINGER 4 RT. REMOVED AND REPLACED STRINGER CLIP WITH A	 NEW CLIP IAW 51-30-2.					2	L	7	3 	4F			 	A3WE    					 
2002082300027	20020823	00027	SO  	2002	8	23	CA020814005      	1	20020809	G	8011		DRIVE GEAR      	PRESTOLITE  	MZ4204      	PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					STARTER MOTOR	DISINTEGRATED   	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA						8L000474					(CAN) ON TAKEOFF,  PILOT REPORTED NOISE AND ABORTED.  INSPECTION REVEALED DISINTEGRATION OF STARTER MOTOR BENDIX DRIVE G	EAR AND FRONT STARTER BUSHING IN CONTACT WITH SPINNER BACKING PLATE.  THE BENDIX APPARENTLY DID NOT DISENGAGE AFTER STAR	TUP AND THE ENGINE DROVE THE STARTER MOTOR TO FAILURE.  APPEARS THE ARMATURE SEIZED ON ITS BEARINGS, THEN THE BENDIX TRY	ING TO STILL TURN THE MOTOR PUSHED THE ARMATURE FORWARD ALONG WITH THE NOSE BUSHING INTO THE PERIPHERY OF THE SPINNER BA	CKING PLATE AT WHICH POINT THE BENDIX GEAR DISINTEGRATED.		1	L	7	1 	3O	3	O	 	A18SO   	E223				 
2002082300044	20020823	00044	NM  	2002	8	23	CA020816004      	1	20020808	G	2701	AE66111	BEARING         			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					RUDDER	SEIZED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) CREW REPORTING RUDDER PEDAL HARD TO MOVE ON GROUND.  AFTER INVESTIGATION,  MAINT FOUND A ROLLER BEARING SEIZED IN 	THE CAM ROLLER ARM ASSY. OF THE RUDDER FEEL CENTERING MECHANISM MAINTENANCE REPLACED THE ROLLER AND TESTED THE RUDDER PE	DAL FORCES IAW AMM 27-21-00 P. 570.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2002082300045	20020823	00045	NM  	2002	8	23	CA020819009      	1	20020814	G	2540	14352004	DUMP VALVE      	BOEING      		BOEING	737   	7372Q9      	138448M	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FWD LAVATORY	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) FORWARD LAVATORY FLUID BYPASSED DUMP VALVE ASSEMBLY INTO DRAIN MAINIFOLD AND LEAKED INTO THE SERVICE PANEL AREA. A	IRCRAFT WAS AT 32,000 FT AT A TEMP OF -17C, OAT, WHEN THE ICE SHED FROM THE FWD LAV SERVICING PANEL AND CONTACTED THE RT	 INBOARD WING AND HORIZONTAL STAB AREA.  SPECIAL INSPECTION CARRIED OUT IAW MM 55-10-201.  FORWARD TOILET TANK DUMP VALV	E FOUND AT FAULT. VALVE REPLACED AS PER MM 38-32-31.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002082300194	20020823	00194	SO  	2002	8	23	CA020820004      	1	20020805	G	7160		INTAKE DUCT     			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE AIR INTAKE DUCTS / INERTIA SEPERATORS WERE FOUND TO BE CRACKED PRETTY MUCH ALL OVER.  PLEASE NOTE THAT THE 	PAIR OF AIR INTAKE DUCTS IS CRACKED.  THEY ARE MADE OF FIBERGLASS.  NEW INTAKES WERE ORDERED AND THE ENGINE AND ENGINE M	OUNT HAVE BEEN REMOVED TO ALLOW REPLACEMENT.				1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2002083000234	20020830	00234	CE  	2002	8	30	CA020820007      	1	20020817	G	2121	FN100	COOLING FAN     			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	AIR DISTRIBUTION	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AIRCRAFT RETURNED TO BASE DUE TO SMOKE AND ELECTRICAL SMELL IN COCKPIT.  ALL AVIONICS EQUIPMENT,  WIRING,  LIGHTIN	G,  RHEOSTATS,  INSPECTED SATISFACTORY.  FAULT FOUND IN GPS COOLING FAN.  THE FAN WAS REPLACED AND THE AIRCRAFT RETURNED	 TO SERVICE.NO FURTHER EVIDENCE OF SMOKE OR SMELLS IN COCKPIT OCCURRED.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002090300014	20020903	00014	SW  	2002	9	3	CA020820011      	1	20020819	G	2910	27810322511	TUBE            			FRCHLD	SA227 	SA227CC     	3377522	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	HYD SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			15636								(CAN) SHORTLY AFTER DEPARTURE THE CREW NOTED ILLUMINATION OF THE RT HYDRAULIC LIGHT. A FEW SECONDS LATER THE LEFT HYDRAU	LIC LIGHT ILLUMINATED FOLLOWED BY A LOSS OF PRESSURE ON THE HYDRAULIC PRESSURE GAUGE.  THE AIRCRAFT RETURNED TO BASE AND	 LANDED UNEVENTFULLY. MAINTENANCE INSPECTION OF THE AIRCRAFT DETERMINED A LEAK IN THE HYDRAULIC PRESSURE LINE BETWEEN TH	E FIREWALL AND THE RIGHT SHUTOFF VALVE. THE LINE HAD DEVELOPED A CRACK ADJACENT TO THE SLEEVE AT THE FLARED END OF THE R	IGID LINE AT THE FIREWALL. THERE WAS NO EVIDENCE OF PREVIOUS CHAFING OR DAMAGE TO THE AFFECTED LINE. THE LINE WAS REPLAC	ED	2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	P61GL	 
2002090300066	20020903	00066	CE  	2002	9	3	CA020821002      	1	20020821	G	7120	9090771S	ISOLATION MOUNT 			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION OF THE RT ENGINE. THE UPPER INBOARD VIBRATION ISOLATOR ENGINE MOUNT WAS FOUND TO BE DE	BONDED, THE BACK HALF OF THE RUBBER WAS DEBONDED FROM THE METAL FACE PLATE. THE MOUNT WAS REPLACED AND THE AIRCRAFT RETU	RNED TO SERVICE.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2002090300071	20020903	00071	SO  	2002	9	3	CA020821006      	1	20020805	G	7170		BREATHER        			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE BREATHER ACCESSORIES DRAIN MANIFOLD FOUND CHAFED THROUGH ABOUT 50 PERCENT OF THE TUBE WALL THICKNESS.  BREA	THER IS CHAFING ON CIRCUMFERENCE OF THE HOLE IT GOES THROUGH IN THE COWLING.  THERE IS NO GROMMET, IT IS JUST A HOLE IN 	THE ALUMINUM SKIN WITH A TUBE GOING THROUGH IT WITH LITTLE CLEARANCE. THE TUBE  IS NOT SUPPORTED AND VIBRATES.				1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2002090300081	20020903	00081	NM  	2002	9	3	CA020823003      	1	20020814	G	2761	65449617	HOUSING         			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					SPOILER ACTUATOR	SPLIT           	W				L				ABORTED APPROACH        				K	F	J	FLUID LOSS                	FLT CONT AFFECTED         	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN) ON APPROACH CREW REPORTED COMPLETE LOSS OF HYD FLUID FROM 'A' SYS  UPON SELECTION OF FLAPS & MLG.  CREW CONDUCTED 	MISSED APPROACH & PROCEEDED TO COMPLETE 'LOSS OF SYS HYDRAULICS NON NORMAL CHECKLIST. CREW PERFORMED VISUAL APPROACH & L	ANDED A/C WITHOUT INCIDENT.  MAINT INSPECTION REVEALED NR 1 OUTBOARD GROUND SPOILER ACTUATOR CASE HAD SPLIT RESULTING IN	 COMPLETE LOSS OF HYDRAULICS. MAINT ENGINEERS CHANGED ACTUATOR, AND  ENGINE DRIVEN HYDRAULIC PUMPS & CHANGED / CHECKED A	LL RELATED FILTERS FOR CONTAMINATION.  SYS GROUND CHECKED SERVICEABLE & A/C RETURNED TO SERVICE WITH NO FURTHER INCIDENT	S TO  REPORT.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002090300138	20020903	00138	NM  	2002	9	3	CA020826004      	1	20020819	G	2721	2828001009	CONTROL UNIT    			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					RUDDER TRIM	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AIRCRAFT REQUIRES LARGE AMOUNTS OF RIGHT RUDDER TRIM IN ORDER TO FLY STRAIGHT 250 KTS RANGE REQUIRES 2.5 UNITS OF 	RT RUDDER TRIM. 300 - 325 KTS REQUIRES 3.5 UNITS.BOTH LT INBD AILERON PCUS REPLACED AND RIGGED AS PER AMM 27-11-48					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2002090400003	20020904	00003	EA  	2002	9	4	CA020826010      	1	20020822	G	3270	C2UT473	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					WATER RUDDER	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WATER RUDDER (TAIL WHEEL) TORQUE TUBE FOUND TO HAVE A SPIRAL CRACK ENCIRCLING THE VERTICAL PORTION OF THE TUBE. EX	TERNALLY THE TUBE ASSEMBLY SHOWED NO MAJOR DEFECTS. INTERNALLY THE TUBE WAS SEVERLY CORRODED AT THE INTERFACE OF THE TUB	E JOINT AND THE WELDED SPLINE SHAFT. THE SUBMITTER SUGGESTS THAT A INTERNAL CORROSION PREVENTATIVE COMPOUND BE APPLIED B	EFORE THE UNIT IS PUT INTO SERVICE.			1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002102100038	20021021	00038	EU  	2002	10	21	CA020827002      	1	20020825	G	7920	5007T08P01	TUBE            			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					AFT FAN AREA	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   FOUND AN OIL PRESSURE LINE CRACKED AT THE AFT FAN AREA BY METHOD OF NDT. A COMPANY DECISION IN CONDUCTING AN INS	PECTION OF THE OIL PRESSURE LINES AT THE AFT FAN AREA BY METHOD OF NDT WAS INSTRUCTED TO OUR CONTRACTED APPROVED MAINTEN	ANCE ORGANIZATIONS TO COMPLY WITH, ON ALL OUR FALCON 20 S ASAP.    ENGINE WAS DISASSEMBLED FOR COMPLIANCE OF A 3000 HOUR	 HOT SECTION INSPECTION AND A 600 HOUR INSPECTION. THE INSPECTION OF THE OIL PRESSURE LINES ARE PRESSURE TESTED AT THE E	NGINE OVERHAUL TIME PERIOD, IN THIS CASE AT EACH 5000 HOUR INTERVAL. PART WAS REPLACED WITH SERVICEABLE NDT'D PART.		2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2002102100039	20021021	00039	CE  	2002	10	21	CA020827004      	1	20020716	G	3251	508201892	LINKAGE         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			14027	14027							(CAN) THE STEERING LINK WAS FOUND BROKEN 3/4 OF AN INCH FROM WERE IT ENTERS THE DUST BOOT. THE STEERING LINK WAS REPLACE	D AND THERE HAS BEEN NO FURTHER OCCURANCES					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002090600158	20020906	00158	SW  	2002	9	6	CA020827008      	1	20020731	G	6320	206040662101	SUN GEAR        			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CUSTOMER REPORTED TRANSMISSION TO BE MAKING METAL AT 185.1 SINCE OVERHAUL. TRANSMISSION RETURNED TO OUR FACILITY F	OR TEARDOWN AND INSPECTION. ON TEARDOWN IT WAS FOUND THAT THE SUN GEAR HAD FAILED. THE SUN GEAR WAS INSTALLED NEW AT THE	 TIME OF OVERHAUL.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002090400009	20020904	00009	CE  	2002	9	4	CA020829002      	1	20020828	G	2720	626023248	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PHASE "A" INSPECTION.  MAINTENANCE PERSONNEL WHEN THROUGH THE TAIL CONE AREA TO COMPLETE A VISUAL INSPECTIO	N.  ON THE LT SIDE OF THE TAIL CONE TECHNICIAN DISCOVERED THE RUDDER LT OUTBOARD CABLE WAS FRAYED BETWEEN THE PULLEY AND	 THE SAFETY PIN. CABLE REPLACED & RIGGED RUDDER SYSTEM IAW C650 AMM 27-20-00.				2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2002090400010	20020904	00010	CE  	2002	9	4	CA020829005      	1	20020804	G	5510	07321011	BRACKET         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C*     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT LANDED IN ROUGH WATER, CAUSING THE BATTERY TO CRACK AT THE BATTERY POSTS.  A COMPLETE INSPECTION OF THE A	IRCRAFT WAS CARRIED OUT, AND THE CRACK IN THE REINFORCEMENT BRACKET WAS DISCOVERED. NO OTHER DEFECTS WERE FOUND.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2002091000018	20020910	00018	WP  	2002	9	10	CA020829006      	1	20020808	G	5710		STRUCTURE       			LKHEED	188   	188A        	5262602	WP  	ALLSN 	501D  	501D13      	03004	GL  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			54373								(CAN) CRACK ALONG EXISTING PATH FOUND. AIRCRAFT RETURNED TO MAINTENANCE BASE. CRACK IS OUTBOARD OF BL-165 19 INCHES						2	L	7	4 	4T	4	T	RT	4A22    	E282				 
2002091000020	20020910	00020	NE  	2002	9	10	CA020829008      	2	20020819	G	7314		COUPLING        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					RT ENG FUEL PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE INPUT DRIVE SPLINES OF THE ENGINE HIGH PRESSURE FUEL PUMP WERE FOUND TO BE VERY WORN,  AND SLIPPAGE OCCURRED C	AUSING FUEL STARVATION.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002091000022	20020910	00022	EA  	2002	9	10	CA020829010      	2	20020814	G	7314	RG9080J4A	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE FUEL	FAILED          	W				D				RETURN TO BLOCK         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING FOR TAKEOFF, THE RT ENGINE QUIT AFTER TURNING ON EMERGENCY PUMP.  FUEL FLOW GAUGE SPIKED UP ON SECON	D TRY AND DID THE SAME.  FOUND ENGINE DRIVEN PUMP BYPASSING FUEL THRU AIR SIDE OF FUEL INJECTOR. E/D PUMP REPLACED AND O	PERATION NORMAL.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002091000025	20020910	00025	EU  	2002	9	10	CA020829014      	1	20020826	G	2823		SHUTOFF VALVE   			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					NR 1 ENGINE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) IN YQB, HAD TO SHUT NR 1 ENGINE DOWN WITH FIRE HANDLE SINCE MOVING THE HP FUEL LEVER NR 1 TO THE OFF POSITION.  CL	OSE THE HP FUEL VALVE.  MAINTENANCE IN YQB, CHECKED THE FUEL SYSTEM FOR PROPER FUNCTION,  IN ACCORDANCE WITH THE AMM 71-	00-00, P.534 AND CHECKED SERVICEABLE. THE AIRCRAFT DEPARTED FOR YYZ. MAINTENANCE IN YYZ ALSO REPLACED FOR PRECAUTIONARY 	REASONS, THE NR 1 HP FUEL SOV SWITCH  I.A.W 76-12-11, THE NR 1 ENG. FUEL SHUT OFF RELAY 27 KC  I.A.W. THE ELECTRICAL STD	. PRACTICE MANUAL 20-46-50 AND THE MAIN ENG. CONTROL  I.A.W. THE AMM 73-21-01 P.401		2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2002091000026	20020910	00026	WP  	2002	9	10	CA020829016      	1	20020826	G	7830	LJ37013	BLOCKER DOOR    			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					THRUST REVERSER	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND NR 1 ENGINE THRUST REVERSER BLOCKER DOOR AT THE 8 O`CLOCK POSITION,  DAMAGED AND THE TRANSLATING SLEEVE NOT 	CLOSED PROPERLY (GAP TO LARGE).  MAINTENANCE REPLACED THE BLOCKER DOOR I.A.W.  AMM 78-31-16 AND THE TRANSLATING COWL RIG	GED I.A.W. 78-30-00 P. 516, PARA E.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002090600160	20020906	00160	WP  	2002	9	6	CA020829017      	1	20020818	G	2161	7638801	CONTROLLER      			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					CABIN TEMP	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE AIRCRAFT WAS FLYING AND DIVERTED DUE TO NR 2 PACK UNABLE TO CONTROL IN MANUAL MODE WHILE THE AUTO MODE WAS UND	ER MEL 21-21-01 CATC.  MAINTENANCE REPLACED THE PACK CONTROLLER IAW AMM 21-62-01					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002091800012	20020918	00012	GL  	2002	9	18	CA020830001      	2	20020815	G	7323	104100A13A8	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT NOTICED GOVERNOR OVERSPEEDING BEYOND SET LIMITS AND SHUT DOWN ENGINE.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002091800015	20020918	00015	NE  	2002	9	18	CA020830004      	2	20020729	G	8530	CH91ER	CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) THE AIRCRAFT WAS ON FLOATS MOVING A CAMP FROM ONE LOCATION TO ANOTHER WHEN THE ENGINE STARTED TO RUN VERY ROUGH. T	HE PILOT SWITCHED FUEL TANKS THINKING THAT IT MIGHT BE WATER AND ADDED CARB HEAT JUST IN CASE IT WAS CARB ICE. WHEN THAT	 DID NOT HELP HE LANDED ON A LAKE AND CALLED BACK TO BASE.  MAINTENANCE STAFF WENT OUT AND FOUND NR 3 CYLINDER WAS CRACK	ED.  CYLINDER WAS CHANGED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	H	7	1 	3R	3	R	 	A815    	5E2				 
2002090400012	20020904	00012	CE  	2002	9	4	CA020830006      	1	20020802	G	2436	0560	SENSOR          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	OVER VOLTAGE	FAILED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA						A121706					(CAN)   HIGH VOLTAGE LIGHT CAME ON DURING FLIGHT.   FLIGHT TERMINATED.  OVER VOLTAGE SENSOR FAILED.  RESULTED IN DAMAGE 	TO VOLTAGE REGULATOR AND BATTERY CONTACTOR.  ELECTRICAL COMPONENTS REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002091000030	20020910	00030	EU  	2002	9	10	CA020830010      	2	20020719	G	8530	20330160	CYLINDER        			DHAV  	DHC2  	DHC2MK2     	2800106	EA  	WSK   	PZL   	PZL3S       	67204	EU  	WSK	US132	US132000A   	NE  	VALVE SEAT	CRACKED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) ON A 100 HOUR INSPECTION,  NR 2 & 7 CYLINDER HAD VERY LOW COMPRESSION. AFTER REMOVAL OF BOTH CYLINDERS IT WAS NOTI	CED THAT THE EXHAUST VALVE SEATS WERE CRACKED. THE CYLINDERS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.					1	H	7	1 	3R	3	R	 	A806    	E18EU	5	C	P4NE	 
2002091000032	20020910	00032	CE  	2002	9	10	CA020830012      	1	20020806	G	3230	M710501	MOTOR           			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					HYD POWERPACK	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN)  ON FINAL APPROACH,  MLG WOULD NOT RESPOND TO SELECTOR LEVER MOVEMENT. MLG SUBSEQUENTLY LOWERED USING EMERGENCY HA	ND PUMP.  UNEVENTFUL LANDING CARRIED OUT.  MAINTENANCE DETERMINED MLG MOTOR 60 AMP CIRCUIT BREAKER HAD OPENED.  BREAKER 	IS LOCATED IN LT WING CENTRE SECTION LEADING EDGE.   A/C PLACED ON JACKS,  BREAKER RESET & GEAR RETRACTION TEST PERFORME	D. GEAR RETRACTED NORMALLY & CYCLE COMPLETED WITHIN MAINT MANUAL TIME LIMITS, HOWEVER MOTOR REPLACED ON SUSPICION IT HAD	 CAUSED BREAKER TO OPEN.  REPLACED MOTOR (0 TSO) CYCLED GEAR NOTICEABLY QUICKER & QUIETER THAN  ORIGINAL MOTOR.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2002091000033	20020910	00033	CE  	2002	9	10	CA020830013      	1	20020820	G	7810	17540071	RISER           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND CRACK JUST BELOW THE EXHAUST FLANGE WELD. CRACK HAD PROGRESSED HALF WAY AROUND THE BACK OF THE RISER ASSEMBL	Y. CRACK WAS FOUND DURING A REGULARLY SCHEDULED INSPECTION. CRACK HAD NOT BEEN VISIBLE AT THE PREVIOUS INSPECTION, SO CR	ACK DID PROGRESS QUITE QUICKLY. RISER ASSEMBLY WAS REPLACED WITH A SERVICEABLE UNIT, WHILE ORIGINAL WAS SENT IN FOR CORE	.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002091800016	20020918	00016	EU  	2002	9	18	CA020830014      	1	20020520	G	7921	9696	MOTOR           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					OIL COOLER FAN	WORN            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON SHUTDOWN PILOT HEARD FAN MAKING A DIFFERENT SOUND. ON INSPECTION OF FAN, IT WAS FOUND TO BE LOOSE. INDICATING W	ORN ARMATURE BEARING JOURNALS. AT THIS TIME A NEW DC MOTOR WAS INSTALLED. ON TEAR DOWN OF MOTOR IT WAS FOUND THAT IT NEE	DED 2 NEW BEARING 4 NEW BUSHING 1 ARMATURE - WORN JOURNALS				1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2002091800017	20020918	00017	CE  	2002	9	18	CA020830016      	1	20020809	G	7120	075100123	MOUNT           			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			59044								(CAN) ENGINE MOUNT HAD BROKEN TUBE JUST ABOVE FISHMOUTH WELD 11 INCHES BELOW UPPER RT FUSELAGE ATTACH.						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2002091000103	20020910	00103	CE  	2002	9	10	CA020903005      	1	20020726	G	3230	50301008	SWITCH          			BEECH 	100   	B100        	1152919	CE  										MLG MOTOR	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WHILE THE LANDING GEAR WAS BEING STRETCHED, THE LANDING GEAR STAYED DOWN AND THE AIRCRAFT RETURNED TO ITS BASE. SW	ITCH WAS FOUND BROKEN IN THE CONTROL RELAY IN THE GEAR MOTOR. THE SWITCH WAS REPLACED AND LANDING GEAR RETRACTIONS WERE 	PERFORMED.				1	L	7	2 	4T			 	A14CE   					 
2002091000105	20020910	00105	CE  	2002	9	10	CA020903007      	1	20020830	G	3242	AN37A	BOLT            	CLEVELANDXXX	30144       	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					BRAKE ASSY	UNDERTORQUED    	W				O				OTHER                   				W	K		INADEQUATE Q C            	FLUID LOSS                		LD	LANDING        	1			CA											(CAN) AFTER LANDING,  DISCOVERED BRAKE FLUID LEAKING FROM AFT CALIPER AFT PISTON BORE GUIDE BOLT,  CAUSED BY BOLT BEING 	UNDER TORQUED. PISTON BORE GUIDE BOLT TIGHTENED TO 30 INCH POUNDS PER CLEVELAND MM.  BRAKE RESEVOIR TOPPED OFF,  BRAKES 	CHECKED SERVICEABLE. ALL GUIDE BOLTS THIS AIRCRAFT 8 TOTAL TORQUE CHECKED AND 5 OTHERS FOUND BELOW SPECIFIED TORQUE.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002091800025	20020918	00025	CE  	2002	9	18	CA020904001      	1	20020515	G	5342	043200115	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	STABILIZER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   UPON REMOVAL OF BRACKET TO GAIN ACCESS TO NUT PLATES DISCOVERED THE REINFORCEMENT AND RT SPAR CRACKED ALONG BEND	 RADIUS UNDER THE BRACKET. CRACKS COULD NOT BE SEEN UNTIL BRACKET WAS REMOVED.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002091800027	20020918	00027	EU  	2002	9	18	CA020904004      	1	20020826	G	3246	AH43208	WHEEL           			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33110    	01514	WP  	ROTOL	R333	R333482F12  	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE POST FLIGHT INSPECTION, A 6 INCH CRACK WAS NOTED, ALONG WHEEL FLANGE AT TIRE BEAD ATTACHMENT. ON DI	SASSEMBLE INSPECTION THE CRACK EXTENDING TO 7.51INCH ON THE INSIDE OF WHEEL FLANGE. NO VISIBLE DAMAGE NOTED ON INNER WHE	EL HALF MATE. BUT WAS REMOVED AND SENT FOR NDI INSPECITON.				2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	P61GL	 
2002091800028	20020918	00028	EU  	2002	9	18	CA020904005      	1	20020827	G	2435	9408308803	BEARING         		5243212142  	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STARTER GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILATUS GIVES A 3000 HOUR LIFE TO NR 2 GEN DRIVE OUTER BEARING, BUT NOT TO INNER BEARING. DURING REPLACEMENT OF OU	TER BEARING DUE TO T/X, FOUND INNER BEARING UNSERVICEABLE. IT IS NOW OUR POLICY TO REPLACE INNER BEARING AS WELL DURING 	OUTER BEARING REPLACEMENT.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002091200018	20020912	00018	NM  	2002	9	12	CA020904007      	1	20020904	G	7500		ISOLATION VALVE 			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					BLEED SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) BOTH ENGINE SURGING AT CRUISE, BLEED SURGING FROM 20PSI TO 52 PSI. NR 2 ENGINE SURGING CONSIDERABLY MORE ON DESCEN	T.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002091800030	20020918	00030	NM  	2002	9	18	CA020904009      	1	20020823	G	2751	1812993	INDICATOR       			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN)  DURING APPROACH, PILOT OBSERVED A SPLIT FLAP INDICATION.  AIRCRAFT LANDED WITHOUT INCIDENT.  FLAP POSITIONING IND	ICATOR REPLACED AND CHECKED SERVICEABLE IAW MM 27-50-00. 4. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002091800031	20020918	00031	SO  	2002	9	18	CA020904010      	1	20020820	G	5730	6206102	SKIN            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WINGS REMOVED FOR INSPECTION AFTER HARD LANDING WITH RT WING REMOVED FORWARD AND AFT WING WALKS UNDER UPPER WING S	KINS INSPECTED AND CRACKS FOUND AT END RADIUS OF STAMPED STIFFENER SECTIONS.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002091800032	20020918	00032	EA  	2002	9	18	CA020904011      	2	20020820	G	7414	M3100	RIVET           	SLICK       	4372        	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					IMPULSE COUPLING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						00031603					(CAN) AFTER TWO COMPLETE IMPULSE COUPLING FAILURES WHICH RESULTED IN THE ENGINES BEING REMOVED FOR REPAIR,  IT WAS DECID	ED THAT AT EVERY 100 HOUR INSPECTION THE LT MAGNETO WOULD BE REMOVED AND THE IMPULSE COUPLING INSPECTED. ON THIS IMPULSE	 COUPLING ONE PAWL RIVET WAS LOOSE AND COULD BE EASILY ROTATED. THE PAWL GAP WAS NOT BEYOND LIMITS IN ACCORDANCE WITH UN	ISON 4300/6300 SERIES MAINTENANCE AND OVERHAUL MANUAL L-1363 CHAPTER 3 SECTION 3.3.4B. THE IMPULSE COUPLING WAS REPLACED	 WITH A NEW ONE. THE 100 HOUR INSPECTION INTERVAL ON THE IMPULSE COUPLINGS WILL BE CONTINUED AS COMMON PRACTICE.		1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002091900008	20020919	00008	EU  	2002	9	19	CA020904012      	3	20020828	G	6114	A915B	BEARING         	MUHBR       		ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	PROP HUB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									94277		(CAN) T57006 PROPELLER REMOVED AT SCHEDULED 100 HOUR INSPECTION. DURING ROTATION OF PROP BY HAND AN OBJECT COULD BE HEAR	D TUMBLING AROUND INSIDE HUB. NOTE THAT JUST PRIOR TO REMOVAL OF THE PROP A REPORT WAS RECEIVED STATING THAT THE PROPELL	ER WOULD NOT RETAIN ITS SETTING AND WOULD KEEP UP BY 200 - 300 RPM . HUB BLADE BORES WORE ENOUGH FOR GREASE TO LEAK OUT 	OF PROP. BALL BEARING SEPARATORS WORE AND CAME OUT OF BEARINGS. BALLS WOULD THEN CONTACT EACH OTHER GIVING SOUND OF RATT	LING.		1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2002091800060	20020918	00060	CE  	2002	9	18	CA020905008      	1	20020904	G	3244		TIRE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MAIN WHEEL	DAMAGED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER TOWING AIRCRAFT OUT FOR DEPARTURE A BULGE WAS FOUND IN THE TIRE.  THE WHEEL ASSEMBLEY WAS REPLACED WITH A OV	ERHAULED UNIT.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002091800066	20020918	00066	NE  	2002	9	18	CA020906005      	2	20020829	G	7414	45540613	SWITCH          			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	S3H1        	52016	NE  					MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						NONE					(CAN) PILOT DISCOVERED FORWARD COCKPIT MAGNETO CONTROL SPINNING FREELY WITH NO APPARENT CONNECTION TO SWITCH.  MAINTENAN	CE PERSONNEL DISCOVERED THAT INDICATED LEVER MECHANISM FOUND TO BE BROKEN AT WELD.   LEVER NO LONGER ABLE TO TURN MAGNET	O SWITCH.  LEVER REPAIRED BY WELDING, AND RE-INSTALLED.				1	L	7	1 	3R	3	R	 	EXPA1L71	E143				 
2002100900006	20021009	00006	EA  	2002	10	9	CA020909001      	1	20020905	G	5630	85240076001	WINDOW          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	SERVICE DOOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) FLIGHT ATTENDANT COULD HEAR AIR LEAK FROM REAR AFT SERVICE DOOR DURING FLT. FOUND WINDOW CRACKED AROUND CIRCUMFERE	NCE OF WINDOW.  BOLTS ALSO FOUND BADLY CORRODED.  NEW WINDOW AND HARDWARE INSTALLED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002100900013	20021009	00013	EU  	2002	10	9	CA020910007      	1	20020909	G	3251	Z4242390000	CONTROL CABLE   			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN)   ON TAXI THE AIRCRAFT WOULD ONLY TURN IN ONE DIRECTION.  IT WAS FOUND THAT THE RT STEERING CABLE HAD BROKEN AT TH	E FWD END AT THE LOOP AROUND THE BOLT.  THE CABLE WAS REPLACED AND THE STEERING SPRING GAP WAS SET.  ALL OTHER CABLES ON	 THE FLEET OF Z242L AIRCRAFT WERE INSPECTED WITH NO DEFECTS FOUND.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002100200002	20021002	00002	NM  	2002	10	2	CA020912010      	1	20020830	G	5330		SKIN            	BOEING      		BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			66295								(CAN) CRACK AT AFT CARGO DOOR CUTOUT SKIN,  AFT LOWER CORNER AT FASTNER HOLES.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2002100900039	20021009	00039	GL  	2002	10	9	CA020913006      	3	20020912	G	6111	57A2202	BEARING         													HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER TAKING THE PROPELLER APART,  IT WAS NOTED THAT NR 2 BLADE THRUST BEARING WAS BROKEN INTO SEVERAL SMALL PIECE	S.  AS A RESULT OF THIS BROKEN BEARING, THERE WAS SOME MINOR DAMAGE TO THE BLADE SHOULDERS.  ONE BEARING WAS ALSO FOUND 	CORRODED ON THE OUTER SURFACE.  BOTH OF THESE BEARING RACES WERE REPLACED,  AND THE BLADE SHOULDER WAS REPAIRED,  CHECKE	D ON THE OPTICAL COMPARATOR, MEASURED FOR DIMENSIONS, AND COLD ROLLED.  THERE WAS ALSO ONE SET OF BEARINGS THAT CONTAINE	D A LARGE AMOUNT OF RESIDUE MAGNETISM, THIS WAS DEMAGNETIZED, AND REINSTALLED.												5	C	STC	 
2002100900046	20021009	00046	SW  	2002	10	9	CA020913009      	1	20020827	G	5711	71493	SPAR            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					WING	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN THE FUEL CELL STIFFENER SPAR ON THE WING.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002100900053	20021009	00053	EA  	2002	10	9	CA020913012      	1	20020905	G	5413	C6W1512S141	LONGERON        			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A20      	52043	EA  					NR 2 NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 2 ENGINE NACELLE LONGERON CRACKED ON INBOARD SIDE.						1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2002102100044	20021021	00044	NE  	2002	10	21	CA020916002      	2	20020822	G	7322	A3025U3	CARBURETOR      			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		CR	CRUISE         	1			CA											(CAN) A/C TOOK OFF WITH A LOAD OF ABOUT 4,500 LBS.  POWER ON T/O NORM. CLIMB POWER SELECTED AND A/C CLIMBED TO CRUISE AL	TITUDE. A/C CLIMB SLUGGISH. ENG INSTRUMENTS NORM.  AT CRUISE A/C SLUGGISH, ENG INSTRUMENTS NORM.  AFTER 12 MIN,  ENG QUI	T W/O WARNING. LANDED ON SMALL LAKE. EMER PROCEDURES C/O & LANDED W/O INCIDENT.  ON INVESTIGATION,  FUEL SYS INSPECTED F	OR CONTAMINATION.  NO WATER OR CONTAMINATES FOUND,  & SUFFICIENT FUEL TO CARB TO RUN ENGINE.  CARB REMOVED & SERVICEABLE	 INSTALLED, ENG TEST RUN, & NO DEFECTS NOTED.  CARB WAS INSTALLED ON THIS A/C HAD ALSO BEEN REPAIRED WITH TTSO/H 297.3 H	RS.   BEFORE CARB WAS REPAIRED IT WAS REMOVED FROM SERVICE DUE TO A VERY RICH MIXTURE & COULD NOT BE ADJUSTED.	1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002100900062	20021009	00062	CE  	2002	10	9	CA020916005      	1	20020802	G	3246	33924925	WIRE ROPE       			CESSNA	172   	172D        	2072410	CE  	LYC   	O360  	O360A1A     	41514	EA  					TIE RODS	BROKEN          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF RUN,  AT APPROXIMATELY 2 FT OFF THE WATER, A/C SETTLED BACK DOWN DUE TO UNSTABLE AIR.   A NOISE WAS HEA	RD AND THE A/C BECAME VERY UNSTABLE.  ABORTED TAKEOFF.  AS THE A/C SLOWED DOWN & THE LIFT DISSIPATED, THE LT WING SUDDEN	LY DIPPED DOWN AND CAME IN CONTACT WITH THE WATER CAUSING THE A/C TO VEIR LT ABRUPTLY, DISPLACING A CONSIDERABLE AMOUNT 	OF WATER, BUT MANAGE TO KEEP THE A/C FROM INVERTING. CAUSED ALL THE FITTING ON THE END OF THE FLOAT STRUTS TO FAIL. THE 	FINAL RESTING POSITION OF THE A/C WAS ENGINE POINTING UP, TAIL AND LT WING TIP PARTIALLY SUBMERGE. THE A/C WAS TOWED AND	  BEACHED. UPON INSPECTION,  IT WAS FOUND THAT BOTH CROSS WIRES WERE BROKEN  ALLOWING THE WING TO GO DOWN.	1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2002100900099	20021009	00099	EU  	2002	10	9	CA020917005      	1	20020911	G	2710	TB1017012000	ROD END         			SOCATA	TB9   	TB9         	8680694	EU  	LYC   	O320  	O320D2A     	41508	EA  					RT AILERON	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A SCHEDULED MAINTENANCE INSPECTION THE RT AILERON SWIVEL ROD END WAS FOUND STIFF. ON FURTHER INSPECTION THE BEA	RING RACE WAS FOUND BROKEN AND SOME OF THE BALL BEARINGS WERE MISSING.					1	L	7	1 	3O	3	O	NT	AS1EU   	E274				 
2002100900105	20021009	00105	EU  	2002	10	9	CA020918003      	1	20020915	G	3251	3790037108	METERING VALVE  			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NLG STEERING	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						00733					(CAN) AFTER LANDING AND JUST TURNING OFF RUNWAY,  UNABLE TO STEER AIRCRAFT USING RUDDER PEDDLES OR TILLER.  HYDRAULIC PR	ESSURE NORMAL.  SELECTING RESERVE BRAKE AND STEERING ALSO NO HELP.  AIRCRAFT TOWED TO GATE. REPLACED NLG STEERING METERI	NG VALVE AS PER AMM 32-51-04				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002100200005	20021002	00005	EU  	2002	10	2	CA020918005      	1	20020916	G	2910	SC47003	ACTUATOR        	SAMM        		AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					HYD SYSTEM	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						1434					(CAN) YELLOW HYDRAULIC SYSTEM LOST FLUID AND CABIN FILLED WITH SMOKE. YELLOW SYSTEM YAW DAMPER ACTUATOR FOUND LEAKING.  	YAW DAMPER CHANGED AS PER AMM.  YAW DAMPER OPERATION CHECK CARRIED OUT AS PER AMM.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002100900140	20021009	00140	NE  	2002	10	9	CA020918011      	2	20020909	G	8530	358686	CYLINDER HEAD   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	NR 9	CRACKED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN) NR 9 CYLINDER HEAD SEPARATED BETWEEN SPARK PLUG HOLES 20 MINUTES AFTER TAKEOFF WHILE IN CRUISE FLIGHT.  SERVICEABL	E UNIT INSTALLED AND RESUMED FLIGHT.					1	H	7	1 	3R	3	R	 	A815    	5E2	6	C	P719	 
2002100900142	20021009	00142	SO  	2002	10	9	CA020919001      	1	20020901	G	2120	554901	CLAMP           	PIPER       	8124402     	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					AIR DISTRIBUTION	LOOSE           	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, THE AIRCRAFT DEPRESSURISED. UPON INSPECTION, THE FORWARD CLAMP ON THE FRESH AIR TUBE WAS FOUND LOO	SE AND THE TUBE WAS DISCONNECTED. THE FIBERGLASS ON THE EVAPORATOR BOX WAS THEN REINFORCED AND THE CLAMP REINSTALLED.					1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2002100900148	20021009	00148	EA  	2002	10	9	CA020923001      	1	20020801	G	2997		WIRE            			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					HYD POWER	SHORTED         	W				O				OTHER                   				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			CA											(CAN) DURING PREFLIGHT CHECKS, THE HYDRAULIC PUMPS WERE SELECTED ON AND THE COCKPIT LIGHTING DIMMED.A HEAVY CURRENT LOAD	 COULD BE HEARD COMING FROM THE GROUND POWER CART.HYD PUMP 3B C/B TRIPPED.TWO ATTEMPTS WERE MADE TO RESET THE C/B, EACH 	HAVING THE SAME EFFECT AS PREVIOUSLY NOTED BUT WOULD NOT RESET.SMOKE WAS NOTICED COMING FROM THE AVIONICS BAY AND POWER 	WAS REMOVED FROM THE A/C.INVESTIGATION REVEALED THE MAIN POWER FEED WIRE TO THE 3B HYD PUMP IN THE AVIONIC BAY AROUND ST	ATION 281 HAD SHORTED TO A CLAMP THAT SECURED THAT WIRE BUNDLE		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002102100047	20021021	00047	EA  	2002	10	21	CA020927004      	2	20020924	G	7510	9091010017	TUBE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					INTAKE ANTI ICE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ENGINE ANTI-ICE INTAKE TUBES REPLACED AS PER BEECH SB 71-3142, WERE FOUND CRACKED (NOT SEPARATED) ATFIRST INSPECTI	ON AFTER SB COMPLIANCE.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002100200007	20021002	00007	CE  	2002	10	2	CA020930001      	1	20020927	G	2130	3001241	SEAL            			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					BLEED AIR DUCT	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			17135								(CAN) LT BLEED AIR WARNING CAME ON AT FLIGHT LEVEL 41000.  BLEED AIR SHUT-OFF & SWITCH SELECTED IN THE OFF POSITION LIGH	T EXTINGUISHED.  FOUND LEFT HAND PYLON BLEED AIR DUCT SEALS DRYED AND CRACKED.					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2002102900017	20021029	00017	EU  	2002	10	29	CA020930006      	1	20020929	G	2170	BAS16346416	DUCT            		258VF1331   	BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					WATER SEPARATOR	LEAKING         	W				A				UNSCHED LANDING         				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DUCT FROM WATER SEPERATOR SOCK IN AFT EQUIPMENT BAY DISCONNECTED FROM SEPERATOR. CABIN DEPRESSURIZEDAND AIRCRAFT D	ECENDED AND RETURNED TO BASE.  DUCTS AND CLAMPS WERE INSPECTED AND AFTER RE-INSTALLATION AIRCRAFT WAS RUN TO MAX DIFF ON	 RAMP USING APU. NO LEAKS NOTED AND AIRCRAFT WAS RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002102900020	20021029	00020	CE  	2002	10	29	CA021001003      	1	20020930	G	5753	652511585	RIB             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAPS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RIB EXTENSIONS ON FLAP ASSY'S ON BOTH LT & RT FLAPS WERE WORN BY THE RIVETS HOLDING THE FLAP TRACKS ON THE WING. T	HE WEAR WAS AS MUCH AS 50 PERCENT MATERIAL THICKNESS.THESE 4 RIB EXTENSIONS WERE REPLACED. SIMILAR WEAR ON THE INBOARD &	 OUTBOARD RIB EXTENSIONS WERE WITHIN BLENDABLE LIMITS.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002102100048	20021021	00048	CE  	2002	10	21	CA021001006      	1	20020925	G	3040	10138402517	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT	OVERHEATED      	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) SHORTED AND OVERHEAT CONDITION ON LT WINDSHIELD GROUND TERMINAL CAUSING A HEAVY SMELL OF BURNED PLEXIGLASS TYPE OF	 ODOUR.  PILOTS SWITCHED OFF LT WINDSHIELD ANTI-ICE AND SMOLDERING SUBSIDED.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2002102100049	20021021	00049	CE  	2002	10	21	CA021001007      	1	20020930	G	3211	664130667	BUSHING         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	CORRODED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING PHASE 5 INSPECTION CORROSION WAS NOTICED AROUND THE TRUNNION INNER PINS.AFTER MUCH DIFFICULTY THE PINS WERE	 REMOVED AND CORROSION WAS FOUND ON THE INSIDE OF THE BUSHINGS,SEIZING THE PINS. THE PINS ARE STACKED TO THE TRUNNION AN	D BUSHING WITH ROLL PINS. THE GEAR IS REQUIRED TO BE REMOVED AT 25800 LANDINGS, BUT, THERE IS NO REQUIREMENT TO REMOVE A	ND INSPECT THE PINS.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002102100051	20021021	00051	CE  	2002	10	21	CA021001009      	1	20020930	G	2497		TERMINAL        			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  					CIRCUIT BREAKER	LOOSE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) ON DESCENT INTO FORT SMITH FROM FORT CHIPEWYAN, THE CREW NOTICED AN ELECTRICAL SMELL, FOLLOWED SHORTLY BY SMOKE.AL	L ELECTRICAL POWER WAS TURNED OFF.ALL NON ESSENTIAL FUNCTIONS WERE TURNED OFF THEN POWER WAS TURNED BACK ON.  THE SMELL 	REAPPEARED.POWER WAS RESTORED LONG ENOUGH TO LOWER GEAR AND MAKE RADIO CALLS THEN TURNED OFF FOR LANDING.  ON INSPECTION	, THE WIRE ATTACHED TO THE POWER SIDE OF THE WING DEICE LIGHT CIRCUIT BREAKER WAS LOOSE.THE BAD CONNECTION WAS CAUSING T	HE WIRE TO HEAT UP NEAR THE TERMINAL.		1	L	7	2 	3T	3	T	 	A14CE   	E4EA				 
2002102100052	20021021	00052	SW  	2002	10	21	CA021001012      	1	20020925	G	2497	J340	CONNECTOR       			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					GCU PANEL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE GCU PANEL CONNECTOR WIRES IN THE LT NACELLE WERE FOUND CHAFED APPROXIMATELY 1 INCH FROM THE CONNECTOR. SEVERAL	 WIRES HAD BEEN CHAFED BY A TOOL USED TO LOOSEN THE HYDRAULIC FILLER CAP WHICH IS LOCATED JUST FORWARD OF THE CONNECTOR.	 THE WIRES ARE PROTECTED IN THAT AREA WITH NYLON SPIRAL WRAP BUT BECAUSE OF THE SHALLOW ANGLE TO THE CONNECTOR THE TOOL 	COULD PENETRATE THE WRAP WHICH COULD THEN SPRING BACK AND COVER THE DAMAGE MAKING IT DIFFICULT TO NOTICE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2002102100054	20021021	00054	WP  	2002	10	21	CA021001013      	1	20020926	G	3510	40193733	HOSE            			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					OXYGEN SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE 'MEDIUM PRESSURE OXYGEN HOSE ASSY AT THE OXYGEN  CYLINDER HOOKUP PANEL, WAS FOUND TO DAMAGED. THIS FLEXIBLE BR	AID LINE WAS FRAYED AT THE PANEL CONNECTION AND THE FLEXIBLE LINE INSIDE  WAS CRACKED.9 OF THOSE LINES WERE ORDERED AOG.	 ALSO, FOR PRECAUTIONARY REASONS, THE 'LOW PRESSURE OXYGEN HOSES ASSY THAT CONNECTS TO THE CREW OXY. AND MICROPHONE SERV	ICE PANEL' WERE ALSO ORDERED AOG (9 LINES). A SPECIAL INSPECTION 1-35-003 REV 00, WAS RAISED FOR A FLEET CAMPAIGN INSPEC	TION.		2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002102100056	20021021	00056	CE  	2002	10	21	CA021002001      	1	20020930	G	5312	641201534	BULKHEAD        	CESSNA      		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUSELAGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHERE THE ELEVATOR TRIM CABLES PASS THROUGH THE CANTED BULKHEAD, THE RT CABLE WAS FOUND WEARING INTO THE LOWER COR	NER OF THE HOLE & THE LT CABLE WAS JUST CLEAR BY ABOUT .020 INCH.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002102900024	20021029	00024	WP  	2002	10	29	CA021002008      	1	20020825	G	7910	369A8322	SEAL            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ENGINE OIL WAS DETECTED COMING THROUGH THE UPPER AFT RT INTERIOR PANEL AND GRAVITY LEAKAGE DOWN TO THE AIRCRAFT FL	OOR. CONDITION ONLY EXISTED UNDER STEEP RT TURNS OF THE HELICOPTER. A/C RETURNED TO BASE AND UPON INVESTIGATION OF THIS 	SITUATION IT WAS DETERMINED THAT THE RUBBER OIL SEAL FROM THE ENGINE OIL FILLER SUPPORT TO ENGINE OIL TANK DEVELOPED A H	OLE UNDER THE CLAMP AT THE TANK LOCATION. OIL TANK IS LOCATED AT THE UPPER RT (AFT FACING FORWARD) OF THE HELICOPTER. TH	AT EXPLAINED THE AREA OF LEAKAGE IN QUESTION. NEW SEAL WAS INSTALLED ANDTHE AIRCRAFT WAS GROUND RUN AND FLOWN WITH NO FU	RTHER LEAKAGE. DEFECT ENTRY WAS COMPLETED AS PER COMPANY MCM AND UNDER CARS 605.06 AND RECTIFIED PRIOR TO NEXT FLIGHT.	1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002102100129	20021021	00129	SO  	2002	10	21	CA021002011      	1	20020826	G	5280		STRUCTURE       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14253								(CAN) LT OUTBOARD GEAR DOOR HAD A SMALL CRACK FRONT AND BACK OVER THE HINGE TO THE GEAR LEG. RT OUTBOARD GEAR DOOR HAD A	 SMALL CRACK FRONT OVER THE HINGE TO THE GEAR LEG.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002102100130	20021021	00130	SO  	2002	10	21	CA021002012      	1	20020826	G	5280	4040522	RIB             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14253								(CAN) ON INSPECTION IT WAS NOTICED THAT WHERE THE OUTBOARD DOOR HINGE ATTACH TO THE OUTBOARD RIB, THE RIB WAS CRACKED. T	HE RIB WAS REPAIRED AND DOOR REINSTALLED. IF LEFT LONGER THE DOOR COULD HAVE JAM IN THE WHEEL WELL.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002102100131	20021021	00131	SO  	2002	10	21	CA021002013      	1	20020826	G	5730	4472303	SKIN            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14253								(CAN) ON INSPECTION IT WAS NOTICED THAT WHERE THE RT MAIN GEAR PUSHES TO THE UP POSITION, THE RIB HOLDING THE WHEEL STOP	 WAS CRACKED AND THE WING SKIN HOLDING THE RIB WAS ALSO CRACKED FROM THE MANY CYCLES.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002102100132	20021021	00132	SO  	2002	10	21	CA021002014      	1	20020422	G	3232	756265	SPRING          	OZONE       	O14529243   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					DOOR ACTUATOR	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) INBOARD GEAR DOOR OPENED IN FLIGHT AND AFTER LANDING WHEN MASTER WAS CLOSE OFF. THE DOOR CAME OPEN. THE SPRING IN 	THE DOOR ACTUATOR THAT PUSHES THE BALL LOCK WAS FOUND BROKEN.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002102100133	20021021	00133	CE  	2002	10	21	CA021002015      	1	20020829	G	3260	A4503M95	SWITCH          			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) THE HANDLE WOULD NOT WORK IN THE DOWN POSITION UNLESS THE HANDLE WAS TAPPED. A NEWLY OVERHAULED LANDING GEAR CONTR	OL WAS INSTALLED.  IT WORKED FOR 229.5 HOURS AND 216 CYCLES BEFORE FAILING THE SAME WAY. AFTER REMOVING THE HANDLE THE D	OWN SWITCH WAS NOT WORKING. THIS IS THE THIRD CONTROL WITH THE SAME PROBLEM IN 10 MONTHS 450 HOUR OF FLYING.				1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2002102100134	20021021	00134	EU  	2002	10	21	CA021003002      	1	20020913	G	3242		LINER           	CLEVELAND   	03024400    	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE ASSY	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1122					(CAN) DURING INSPECTION FOUND 10 PERCENT OF BRAKE LININGS WORN BEYOND LIMITS STATED IN CLEVELAND BRAKE MANUAL. EVEN THOU	GH LININGS ARE WORN OUT WEAR INDICATORS SHOW BRAKE ASSEMBLY AT HALF LIFE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002102100135	20021021	00135	EU  	2002	10	21	CA021003003      	1	20020913	G	3244	0213500	TIRE            		0213500     	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1287W00244					(CAN) TIRE RUN FOR 46.0 HOURS TIRE WOULD LEAK 25 PERCENT PER DAY. TIRE LEAKS THROUGH SIDE WALL VENTS. THIS IS SECOND TIR	E THIS WEEK TO DO THIS. SECOND TIRE HAD 413 HOURS.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002102100136	20021021	00136	EU  	2002	10	21	CA021003004      	1	20020923	G	2740	9742001212	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HORIZONTAL STAB	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				I			FLT. ATTITUDE INST.       			AP	APPROACH       	1			CA											(CAN) FLIGHT CREW EXPERIENCED UNCOMMANDED UP TRIM ON HORIZONTAL STAB TRIM. SYSTEM WAS DEACTIVATED USING TRIM INTERRUPT S	WITCH, AND AIRCRAFT LANDED USING ACT. STAB TRIM. ON INVESTIGATION FAULTY RELAY FOUND (K22) RELAY REPLACED AND SYSTEM TES	TED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002102100137	20021021	00137	EA  	2002	10	21	CA021004006      	2	20020924	G	7510	9091009913	TUBE            	BEECH       	9091009913  	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					INTAKE ANTI ICE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ENGINE ANTI-ICE (INTAKE) TUBES REPLACED AS PER SB 71-3142 (BEECH) - NEW TUBES FOUND CRACKED (NOT SEPARATED) AT FIR	ST INSPECTION AFTER SB COMPLIANCE.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002102100138	20021021	00138	CE  	2002	10	21	CA021004007      	1	20020915	G	3260	S20881	DOWNLOCK SWITCH 			CESSNA	337   	337F        	2075725	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C301  	GL  	MLG	BROKEN          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ONE WIRE THAT ATTACHES TO THE LT MLG DOWNLOCK SWITCH FRACTURED CAUSING NO 'GREEN' DOWN GEAR LIGHT TO ILLUMINATE AF	TER GEAR WAS SELECTED DOWN. THE WIRES THAT ATTACH TO THE SWITCH ARE PERMANENTLY MOULDED AND APPROXIMATELY 18 GAUGE WHICH	 ARE QUITE THIN FOR THE APPLICATION.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2002102100139	20021021	00139	CE  	2002	10	21	CA021004008      	1	20021003	G	2842	774000068	TRANSMITTER     			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FUEL QTY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT 1/4 FUEL LEVEL TRANSMITTER READS 7/8.  NOTE: PROBLEM ONLY EXISTS WHEN TRANSMITTER IS IN FUEL. BENCH CHECK IN DR	Y CONDITION INDICATES CESSNA  RESISTANCE SPEC'S AS NORMAL.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2002102900126	20021029	00126	EA  	2002	10	29	CA021004009      	2	20020916	G	8500	TIO540J2BD	ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  						FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AFTER TAKEOFF PILOT REDUCED POWER TO CLIMB, NOTED UNUSUALLY LOW OIL PRESSURE,  AFTER FURTHER REDUCINGPOWER TO CRUI	SE SETTING OIL PRESSURE STABILIZED AT BOTTOM OF GREEN ARC. PILOT COMPLETED FLIGHT (10M MINS) TO BASE. OIL TEMPS & CYLIND	ER HEAD TEMPS NORMAL.  ENGINEER INSPECTED OIL PRESSURE RELIEF VALVE FOR FOD.   FOUND SMALL METAL FOD UNDER SEAT.  REMOVE	D & INSPECTED OIL FILTER, REVEALED METAL TRACES ABOVE NORMAL CONCENTRATIONS.  ENGINE  REMOVED FROM AIRFRAMES TO BE INSPE	CTED BY O/H FACILITY.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002102100140	20021021	00140	SO  	2002	10	21	CA021007003      	1	20020930	G	5512	4015514	SKIN            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LEFT HORIZONTAL STABILIZER LEADING EDGE SKIN CRACKED APPROXIMATELY 13 INCHES.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002102100142	20021021	00142	GL  	2002	10	21	CA021007004      	2	20020920	G	7310	68756320	LINE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)   AIRCRAFT LANDED NORMAL SHUTDOWN.   FUEL WAS NOTICED DRIPPING FROM ENGINE PAN DRAIN.  BOOST PUMPS TURNED ON TO CH	ECK FOR STATIC LEAKS.   FOUND SUBJECT LINE DRIPPING FUEL AROUND 'B' NUT. NUT WAS CHECKED AND WAS TIGHT.   LINE WAS REMOV	ED AND INSPECTED AND A CRACK WAS FOUND. CRACK RUNS ABOUT 1/3 OF THE CIRCUMFERENCE OF THE STEEL TUBE AT THE BASE OF THE F	LARE.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002102100143	20021021	00143	SW  	2002	10	21	CA021007005      	1	20020909	G	2810	714931L	FUEL TANK       			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					CENTER	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CRACK IN LT INBOARD FUEL TANK UPPER SURFACE AT OUTBOARD END OF CENTER PREFORMED STIFFENER. - IN ALUMINUM SPAR WING	S.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002102100147	20021021	00147	SO  	2002	10	21	CA021007014      	1	20020913	G	5410	7847502	RIB             			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					NACELLE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN)    PILOT ON A RETURN FLIGHT HOME EXPERIENCED A SLOWER THAN NORMAL LANDING GEAR RETRACTION. A VISUAL INSPECTION WAS	 CARRIED OUT. INSPECTION OF THE LEFT MAIN GEAR AREA REVEALED TWO RIB ASSEMBLIES DAMAGED. THEY WERE LOCATED ADJACENT TO E	ACH SIDE OF THE GEAR LEG, AT STATION 49.25 AND 69.24. THE AIRCRAFT WAS REMOVED FROM SERVICE. DURING THE GEAR REMOVAL, TH	E SUPPORT FITTING (AFT) WAS FOUND CRACKED AT THE LOWER OUTBOARD BOLT HOLE. PART NUMBER FOR THE RIB ASSEMBLIES WERE 78475	-04 AND 78500-02. SUPPORT FITTING NUMBER WAS 67042-012. AIRCRAFT AIRFRAME HOURS WERE 7138.6. THE AIRCRAFT WAS TWO HOURS 	AWAY FROM A SCHEDULED 50 HOUR INSPECTION. THE RIB ASSEMBLIES AND SUPPORT FITTING REPLACEMENT WAS CARRIED OUT, AND LANDIN	1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2002102100161	20021021	00161	NM  	2002	10	21	CA021008004      	1	20020930	G	2752	1502371	PIN             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					LT FLAP ACTUATOR	OUT OF POSITION 	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THE FLAP DRIVE CAUTION LIGHT ILLUMINATED DURING PUSHBACK. FLAPS DRIVE OK FROM 5 DEGREES, TO 35, EXTENDING.FLAP DRI	VE LIGHT ILLUMINATED AGAIN, WHEN FLAPS WE RERAISED FROM 35 TO 5 DEGREES. FCU WAS RESET AND THE A/C FERRIED TO HOME BASE.	 MECHANICS FOUND ACCESS PANEL WAS FOUND DAMAGED, THE LT INBOARD FLAP TRAILING EDGE IS DAMAGED, DELAMINATED.  THE MECHANI	CS ALSO FOUND PIN OUT OF POSITION, FROM THE OUTBOARD ACTUATOR.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002102100163	20021021	00163	NM  	2002	10	21	CA021009022      	1	20020620	G	3260	464505	DOWNLOCK SENSOR 			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					RT MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) LANDING GEAR FAILURE-LIGHT IN GEAR HANDLE CAME ON 4-5 TIMES INTERMITTENTLY DURING FLIGHT. THE PROBLEM WAS RECORDED	 5 TIMES IN THE LAST 6 DAYS. WE EXTENDED THE GEARS IN GOOD TIME AND GOT NORMAL DOWN AND LOCKED INDICATION.1 MIN LATER WE	 GOT LIGHT IN GEAR HANDLE,RED, GREEN AND YELLOW ALTERNATING.ALTERNATE GEAR EXTENSION PROCEDURE USED. INVESTIGATION/ACTIO	N FAULT CODES FROM PSEU - CODE RGDLKL FAULT PROX SENS OPEN FOUND . RH GEAR DOWNLOCK NR 1 SENSOR AND HARNESS ASSY REPLACE	D. AT FURTHER INVESTIGATION OF THE SENSOR AND HARNESS ASSY THE WIRES JUST BEHIND THESENSOR WAS FOUND OPEN WHEN MANIPULAT	ING.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002102900142	20021029	00142	EA  	2002	10	29	CA021009023      	2	20021006	G	7322	105009N	TUBE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CARBURETOR	SEPARATED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) INJECTION TUBE IN CARB BROKE LOOSE IN FLIGHT AND JAMED THROTTLE IN 2400 RPM RANGE. AIRCRAFT LANDED AT HIGH RATE OF	 SPEED AND MAIN TIRES WHERE BLOWN ON ROLL OUT.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002102900143	20021029	00143	CE  	2002	10	29	CA021009026      	1	20021002	G	7931	83278	PRESSURE SWITCH 			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE OIL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT NOTICED LOW OIL PRESSURE LIGHT AND HOBBS METER HAD STOPPED. INVESTIGATION REVEALED THAT SWITCHP/N 83278 HAD 	FAILED INTERNALLY ALLOWING OIL TO COME UP THROUGH THE SWITCH AND CONNECTOR.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002102900144	20021029	00144	SO  	2002	10	29	CA021009027      	2	20021009	G	8550	HD4C2	DRAIN LINE      			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	FAILED          	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) OIL DRAIN PLUG FROM ENGINE O-RING WEARS OUT.  METAL RUBBED AGAINST METAL UNTIL COLLAR WEARS OFF. THEN CENTER PIECE	 FELL OUT LEAVING A 1/2 INCH HOLE FOR THE OIL TO DRAIN. (IN FLIGHT). THIS DRAIN VARIES FROM ENGINE TO ENGINE TYPE.					1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2002102200007	20021022	00007	CE  	2002	10	22	CA021010003      	1	20020927	G	7120	05510171	MOUNT           			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10834								(CAN) ENGINE MOUNT ASSEMBLY CRACKED AT LOWER CROSS MEMBER RT SIDE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002103000005	20021030	00005	EA  	2002	10	30	CA021010004      	2	20020926	G	7414	M3163	IMPULSE COUPLING	SLICK       	4371        	CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					MAGNETO	CRACKED         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA						00041882					(CAN) OUR MAINTENANCE SCHEDULE APPROVAL FOR 172R CALLS FOR MAG OVERHAUL AT 700 HOURS +/- 10 HOURS. AT 657.9 HR MAGS WERE	 CHANGED FOR ROUGH ENGINE (2-3 SEC) SNAG. AT OVERHAUL MAG IMPULSE COUPLINGS FOUND CRACKED AT HUB.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002102200008	20021022	00008	CE  	2002	10	22	CA021010007      	1	20020928	G	2110	7468331	SWITCH          	HAMSTD      	73844315    	CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ACM	SHORTED         	W				B	H			EMER. DESCENT           	DEACTIVATE SYST/CIRCUITS			B	M	J	SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 	WARNING INDICATION        	CR	CRUISE         	1			CA						50797					(CAN) THERMAL SWITCH FAILED ON ACM COMPRESSOR DISCHARGE CAUSING AN AUTOMATIC SHUTOFF OF BOTH BLEED AIR TO AIR CYCLE MACH	INE. EMERGENCY PRESSURIZATION AUTOMATICALLY TURN ON WITH ANNUNCIATOR LIGHT ON PANEL.HOT AIR FROM BLEED AIR AND SMOKE FRO	M DUST IN DUCT CAME INTO THE CABIN, THE PILOT DID AN EMERGENCY DESCENT AND SHUT THE EMERGENCY BLEED AIR AT SAFE ALTITUDE	. THE  SMOKE CLEARED AT ABOUT 5000'. SAFE LANDING WITH ANNUNCIATOR FOR EMERGENCY BLEED LIGHT STILL ON. ACM AND THERMAL S	WITCH REPLACED.		1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2002103000007	20021030	00007	SO  	2002	10	30	CA021010009      	1	20020926	G	3231	8626305	BRACKET         			PIPER 	PA44  	PA44180     	7104402	SO  										MLG DOOR	BROKEN          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA											(CAN) NOSE GEAR RECYCLE FOUR TIMES BEFORE FULLY EXTENDED. NOSE GEAR INSPECTED AND FOUND RIGHT GEAR DOOR LINK ATTACHMENT 	BRACKET BROKEN. THE BROKEN BRACKET WAS STOPPING THE NOSE FROM GOING DOWN TO LOCK POSITION.					1	L	7	2 	3O			 	A19S0   					 
2002102800078	20021028	00078	EA  	2002	10	28	CA021015009      	1	20021015	G	3232	82970014011	CASE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG DOOR ACT	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			27316								(CAN) ON APPRAOCH, THE PILOT NOTED A NR 2 HYDRAULIC ISO VLV CAUTION LT. AND NR 2 HYDRAULIC QUANTITY REDUCED TO APPROXIMA	TELY 1 QUART.  MAINTENANCE FOUND LT MLG REAR AND CENTER DOOR ACTUATOR HOUSING (CASTING) CRACKED NEAR THE UPPER ATTACHMEN	T FITTING. THE DOOR ACTUATOR WAS REPLACED AND ALL FURTHER CHECKS COMPLETED PRIOR TO RELEASE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002103000014	20021030	00014	CE  	2002	10	30	CA021015010      	1	20021013	G	5740	817841432SPS12	BOLT            			BEECH 	100   	B100        	1152919	CE  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF WING AND BOLTS,  IN CONJUNCTION WITH AD.  DYE PENETRANT INSPECTION FOUND CRACK IN LOWER FORWA	RD LT WINGBOLT.  CRACK FOUND ON BOLT SHAFT/FLANGE AREA.  NO OTHER CRACKS FOUND DURING INSPECTION.  BOLT REPLACED.   ORIG	INAL FAILED BOLT INSTALLED AUG. 1ST, 1996. TIME ON A/C 6776.0, CYCLES 5362.   BOLT WAS INSPECTED ON A YEARLY BASIS. WITH	 NO CRACKS DETECTED PREVIOUS.			1	L	7	2 	4T			 	A14CE   					 
2002103000024	20021030	00024	EU  	2002	10	30	CA021016014      	1	20020623	G	8012	9550147560	VALVE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ENGINE FAILED TO START. MAXIMUM NG ATTAINED - 40 PERCENT.  START ELECTROVALVE REPLACED WITH AIRWORTHY PART, START 	CORRECT.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002103000029	20021030	00029	NE  	2002	10	30	CA021016019      	2	20020716	G	7412	ABG6766000	EXCITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) ENGINE START REVEALED REDUCED IGNITOR SPARKING. ONE HIGH ENERGY GENERATOR FOUND FAULTY, REMOVED UNSERVICEABLE. NEW	 PART INSTALLED.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002103000030	20021030	00030	EU  	2002	10	30	CA021016020      	1	20020605	G	7714	0177555170	TACH GENERATOR  			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) FAILURE OF THE TACH BOX CAUSED THE BLEED VALVE TO CLOSE ON ENGINE START-UP, STALLING THE COMPRESSOR.START WAS ABOR	TED. PART REPLACED WITH AIRWORTHY TACH BOX.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002110600189	20021106	00189	CE  	2002	11	6	CA021016030      	1	20021008	G	3242	AN4H214	BOLT            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	BRAKE CALIPER	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) UPON COMMENCING TAXI, BRAKES WERE TESTED BY PILOT AS PER CHECKLIST, AND CALIPER ASSEMBLY BOLTS FAILED AND ALLOWED 	PISTON TO OVER EXTEND AND CAUSE LOSS OF FLUID. BOLTS APPEAR TO HAVE BEEN FRACTURED FOURSOME TIME, DUE EITHER TO FATIGUE 	OR OVERTORQUING. BOLT MANUFACTURER UNKNOWN, BUT HEAD HAS SYMBOL. C-X-S				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002120500060	20021205	00060	CE  	2002	12	5	CA021022004      	1	20021022	G	2434		FAN             	FORD        	DOFF10300F  	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ALTERNATOR FRONT	BROKEN          	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA						A150894					(CAN) ON VISUAL INSPECTION NOTICED COOLING FAN'S FINS BROKEN AND METAL STIFFENER BROKEN IN HALF, INSIDE THE ALTERNATOR C	ASE.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002120500061	20021205	00061	CE  	2002	12	5	CA021022005      	1	20020903	G	8011		STARTER         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STARTER NOT ENGAGING. STARTER REPLACED WITH SERVICEABLE UNIT.  AFTER SENDING THE UNIT TO LAMAR FOR WARRANTY CONSID	ERATION, AND TO DISCOVER WHAT WAS ACCTUALLY WRONG WITH THE UNIT, WE WERE INFORMED THE THE WARRANTY WILL NOT BE HONOURED.	 LAMAR DESCRIBED THAT THE UNIT WAS UN-ECONOMICAL TO REPAIR.  THE UNIT HAD APPERENTLY BEEN OVERHEATED (AMATURE FAILURE.) 	THE STARTER WAS SUBJECTED TO 'IMPROPER STARTING TECHNIQUE.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002120500062	20021205	00062	CE  	2002	12	5	CA021022007      	1	20020924	G	8011	PM2401	STARTER         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED DURING PRE-TAKE-OFF RUN-UP: 'OVERCHARGING DURING RUN UP, COMPLETE ELECTRICAL MALFUNCTION 30 SEC. TH	EN COMPLETE ELECTRICAL FAILURE BURNING SMELL (PALASTIC RUBBER).  CYCLED MASTER NO EFFECT, SHUTDOWN.' STARTER FOUND BURNE	D UP AND SHORTED, STARTER REPLACED WITH NEW.  ALSO ALTERNATOR WAS FOUND TO BE UN-SERVICEABLE.  IT WAS CONCLUDED THAT THE	 STARTER HAD SHORTED DURING THE STARTING PROCESS, AND THE STARTER CONTACTOR WAS TEMPORARILY FUSED (STUCK CLOSED).  THE A	LTERNATOR ATTEMPTED TO RUN THE ELECTRICAL SYSTEM WITH STARTER SOLOENOID TEMPORARILY ENGAGED AND THE SHORTED STARTER IN T	HE CIRCUIT. THE AMMETER SHOWED A HEAVY DRAW AND THE ALTERNATOR EVENTUALLY QUIT.  THE BATTERY ALSO SUFFERED SOME DAMAGE. 	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002120500063	20021205	00063	CE  	2002	12	5	CA021022008      	1	20021022	G	8011		STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STARTER NOT ENGAGING.  STARTER REPLACED WITH SERVICEABLE UNIT.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002111400079	20021114	00079	NE  	2002	11	14	CA021028008      	2	20021027	G	8500		ENGINE          			GRUMAV	G21   	G21         	3951202	SO  	PWA   	R985  	R985AN14B   	52008	NE  					NACELLE	MAKING METAL    	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA											(CAN) PILOT NOTICED ENGINE RUNNING ROUGH ON LAST FLIGHT. PROCEEDED TO DO PERFORMANCE RUNS ON GROUND AND FOUND ENGINE WOU	LD NOT DEVELOP POWER. MAINTENANCE PULLED OIL SCREENS AND FOUND SEVERE METAL CONTAMINATION IN SUMP. CAUSE UNKNOWN AT THIS	 POINT.				1	H	7	2 	3R	3	R	 	TC654   	5E1				 
2002120200181	20021202	00181	EA  	2002	12	2	CA021029012      	1	20021024	G	5610		WINDSHIELD      	            	60R330339   	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  	 		            		OUTER PANE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			CA		 				99078H2836					(CAN) WHILE IN FLIGHT OUTER PANE OF L/H WINDSHIELD CRACKED. WINDSHIELD REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002120600008	20021206	00008	CE  	2002	12	6	CA021030001      	1	20021010	G	7810	17540071	RISER           			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) EXHAUST PORT MATING FLANGE ON RISER CRACKED THROUGH FLANGE AND ALONG LOWER EDGE OF WELD 5/8 OF CIRCUMFERENCE. REPL	ACED RISER ASSEMBLY.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002120600013	20021206	00013	CE  	2002	12	6	CA021031002      	1	20021017	G	5551	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION OF STABILIZER BRACKET NUTPLATES AS PER AD 80-11-04, IT WAS NOTED THAT STEEL BRACKET ITSE	LF WAS CRACKED. AT REMOVAL, BOTH LEFT AND RIGHT TOP SIDES WERE CRACKED. THE FIN BOLTS TO THIS BRACKET, SO THE CRACKING C	OULD BE A RESULT OF STRESS ON THE FIN TO BRACKET ATTACH POINT DUE TO SPIN TRAINING. THIS IS THE SECOND BRACKET IN OUR FL	EET OF 7 152'S TO BE FOUND CRACKED.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002120600014	20021206	00014	SW  	2002	12	6	CA021031004      	1	20021022	G	2810	714931R	FUEL TANK       			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  					WING	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ALUMINUM SPAR WINGS.- CRACK LOCATION ON WELD OF PREVIOUS REPAIR.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002120600015	20021206	00015	SW  	2002	12	6	CA021031005      	1	20021023	G	2720	12364	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RUDDER CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT & RT RUDDER CABLES FRAYED AT PULLEYS - MINIMAL DEFLECTION AT PULLEY. - UNSURE AS TO WHY THEY ARE FRAYED. - REPL	ACING STAINLESS CABLES WITH GALVINIZED.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002120600016	20021206	00016	SW  	2002	12	6	CA021031006      	1	20021022	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					WING	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE FRAYED AT WING ROOT ALUMINUM PULLEY.- NEW CABLE FABRICATED WITH GALVINIZED. - OLD CABLE WAS STAINLESS STEEL.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002120600017	20021206	00017	SW  	2002	12	6	CA021031007      	1	20021022	G	2720	12364	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RUDDER CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT & RT RUDDER CABLES FRAYED AT PULLEY. MINIMAL DEFLECTION AT PULLEY. THEREFORE UNSURE AS TO WHY THEY ARE FRAYED. 	- REPLACING STAINLESS CABLES WITH GALVINIZED.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002120600019	20021206	00019	SO  	2002	12	6	CA021101002      	1	20021018	G	5712	78500002	RIB             			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  					LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED 1000 HOUR INSPECTION, THE RIB HAS BEEN FOUND CRACKED IN THE FORWARD BOTTOM CORNER.						1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2002120600020	20021206	00020	SO  	2002	12	6	CA021101003      	1	20021013	G	2730	110K15001012	CONTROL CABLE   			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT AFTT: 22782.0 HOURS. CABLE FOUND FRAYED DURING INSPECTION OF ELEVATOR CABLE SYSTEM AS PER AD 82-09-08R2 A	ND SB 110-027-064-R2 AND C2 INSP SHEET, HENCE NECESSITY OF DISCONNECTING CABLES FOR PROPER INSPECTION. PULLEY MS 20220A2	 ALSO REPLACED AS SHOWING 'INDENT' PIN POINTS IN PULLEY'S GROOVE. CABLE AND PULLEY REPLACED.				1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2002120600021	20021206	00021	EU  	2002	12	6	CA021101005      	1	20021019	G	2752	9787320307	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) THE PILOT SELECTED FLAPS IN PREPARATION FOR LANDING.THE AURAL WARNING AND FLAP CAUTION LIGHT ON THE CAWS PANEL WER	E THEN OBSERVED BY THE PILOT.  THE AIRCRAFT LANDED AND THE FLAPS WERE RESET ON THE GROUND.THIS SNAG OCCURRED AN ADDITION	AL TWO (2) TIMES THROUGHOUT THE DAY.WHEN THE AIRCRAFT RETURNED TO BASE, MAINTENANCE FOUND THAT THE OUTBOARD ACTUATORS WE	RE FROZEN AND WOULD NOT MOVE.  A HEAT GUN WAS USED FOR APPROX. 60 SECONDS TO FREE THE ACTUATORS.THE ACTUATORS WE RESERVI	CED WITH NEW GREASE AND THE AIRCRAFT RELEASED FOR FLIGHT.THIS MAINTENANCE ACTION DID NOT RESOLVE THE PROBLEM SO NEW ACTU	ATORS WERE INSTALLED IN THE OUTBOARD POSITIONS.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120600022	20021206	00022	EU  	2002	12	6	CA021101006      	1	20021024	G	3233		SWITCH          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG ACTUATOR IND	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) THE PILOT SELECTED THE GEAR DOWN DURING APPROACH. THE NOSE GEAR AND THE LT MAIN INDICATIONS SHOWED 'DOWN & LOCKED'	. THE RT GEAR INDICATOR WAS SHOWING A 'GEAR UNSAFE' CONDITION.  THE PILOT USED THE EMERGENCY GEAR PUMP TO INSURE THAT TH	E GEAR WAS INDEED DOWN AND LOCKED.THERE WAS NO MOVEMENT FROM THE HYDRAULIC HAND PUMP, SO THE GEAR WAS RETRACTED AND CYCL	ED AN ADDITIONAL FOUR (4) TIMES BEFORE THE GEAR SAFE INDICATION WAS ACHIEVED. WHEN THE AIRCRAFT RETURNED TO BASE, MAINTE	NANCE PERFORMED THE FUNCTION TEST OF THE LANDING GEAR & EMERGENCY EXTENSION SYSTEMS WITH NO DEFECTS OCCURRING.HOWEVER, W	HEN THE RT GEAR 'DOWN INDICATION SWITCH' WAS COOLED TO APPROX. -15(C) THE SNAG COULD BE DUPLICATED.AN OVERHAULED GEAR AC	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120600024	20021206	00024	CE  	2002	12	6	CA021101011      	1	20021031	G	2497	650801127	WIRE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MAIN ELECTRICAL	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12654								(CAN) DURING A PHASE 5 INSPECTION, A 10 GAUGE WIRE WAS FOUND TO HAVE SPLIT OPEN EXPOSING 2 INCHES OF BARE WIRE BEHIND TH	E LT CIRCUIT BREAKER PANEL. THIS WIRE TIES THE LT AND RT CIRCUIT BREAKER PANELS AT CB58 AND CB120 RESPECTIVELY. THE MATE	RIAL SPEC ON THE WIRE IS M81381/8. WHILE REMOVING IT FROM THE AIRCRAFT IT ALSO SPLIT OPEN IN OTHER AREAS WHEN FLEXED.THE	 WIRE WAS REPLACED WITH A DIFFERENT SPEC WIRE PER MAINTENANCE PRACTICES IN CHAPTER 20 OF THE CITATION WIRING DIAGRAM MAN	UAL.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002120600025	20021206	00025	EA  	2002	12	6	CA021104002      	1	20021029	G	5610	601R3303311	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA			14074								(CAN) CAPTAIN'S SIDE WINDOW SHATTERED AT 23,000 FT.  LANDING UNEVENTFUL. FERRIED AIRCRAFT FOR WINDOW REPLACEMENT.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002111300056	20021113	00056	WP  	2002	11	13	CA021104004      	2	20021028	G	7310	8945682	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	FUEL SYSTEM	CHAFED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN)  IN CRUISE RT ENGINE BEGAN TO LOOSE TORQUE WITHIN 5-10 SECONDS.  ENGINE TEMP DROPPED TO 400 DEGREES IN 30 SECONDS.	  PROP FEATHERED AND ENGINE SHUTDOWNN PROCEDURES CARRIED OUT.  AIRCRAFT LANDED AND MAINTENANCE CREW DISPATCHED FROM YVR.	 FUEL LINE CHAFED.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2002120600027	20021206	00027	SO  	2002	12	6	CA021104007      	1	20021027	G	2622		EXTINGUISHER    			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					CABIN	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AT LAST FLIGHT OF THE DAY, PILOT NOTICED PRESSURE VERY LOW ON REAR CABIN HAND FIRE EXTINGUISHER AND REPORTED SNAG.	 UPON REMOVAL, MAINTENANCE PERSONNEL FOUND UNIT VERY LIGHT, AND PRESSURE ZERO. THE Q.A.CHECKED: BOTTLE LOOSELY UNSCREWED	 FROM HEAD. NOTE: SEAL OF HANDLE: NOT BROKEN. PILOT SAID HE CHECKED IT OK ON HIS PREFLIGHT. EVIDENTLY UNIT HAS BEEN TEMP	ERED WITH. RECOMMENDATION: THAT THE NEXT OF THE BOTTLE BE DRILLED FOR SAFETY WIRING TO THE HEAD.			1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2002120600028	20021206	00028	CE  	2002	12	6	CA021104010      	1	20021016	G	3020	10191002211	HINGE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ICE BYPASS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15310								(CAN) UPON INSPECTION IT WAS NOTED THAT THE DOOR ASSY BYPASS ICE VANE WAS RUBBING AGAINST THE COWLING.  AFTER CLOSE INSP	ECTION IT WAS NOTED THAT THE HINGE HAD CRACKED FROM THE INBOARD END OUTBOARD ABOUT 3 INCH ALONG THE HINGE PIN. THE HINGE	 ASSEMBLY WAS REPLACED.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002120600035	20021206	00035	SO  	2002	12	6	CA021105007      	1	20021030	G	2435	200S6L118Q	STARTER GEN     			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER/GENERATOR SHAFT SHEARED WHILE MOTORING THE RT ENGINE FOR START. THE SHAFT BROKE AT 1/8 INCH BELOW THE SPLI	NE. INSTALLED NEW STARTER/GENERATOR ON RT ENGINE. GROUND RUN SERVICEABLE. AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2002120600036	20021206	00036	CE  	2002	12	6	CA021105008      	1	20021101	G	7120	045100336	MOUNT           			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE MOUNT CRACKED AT RT TOP AT THE WELDED JOINT.						1	H	7	1 	3O	3	O	 	3A19    	E223				 
2002120600037	20021206	00037	CE  	2002	12	6	CA021105009      	1	20021101	G	5511	043200146	RIB             			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) L/H INBOARD LEADING EDGE RIB WAS FOUND CRACKED AT THE TOP REAR CORNER OF THE HORIZONTAL STABILIZER.						1	H	7	1 	3O	3	O	 	3A19    	E223				 
2002120600038	20021206	00038	CE  	2002	12	6	CA021105010      	1	20021011	G	7602		SHAFT           	FACET       	1048931     	CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470L       	17026	SO  					THROTTLE	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA						H114611					(CAN) CARBURETOR RUNNING LEAN AT ALTITUDE, THROTTLE SHAFT LOOSE, ENGINE RUNS POORLY WITH THIS CARBURETOR. TIME SINCE FAC	TORY OVERHAUL IS 542.1 HOURS.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002120600039	20021206	00039	EU  	2002	12	6	CA021105011      	1	20021104	G	3242	06308400	PAD             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RT MLG BRAKE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT WAS BEING TOWED FROM TERMINAL TO HANGER WHEN THE RT BRAKE SEIZED AND WHEEL WOULD NOT TURN.FURTHER INSPECT	ION REVEALED THAT THE RIVITS WERE SHEARED ON THE WEAR PADS ON THE OUTSIDE ROWS OF THE BRAKE ASSY.  THE WEAR PIN INDICATO	R WAS SHOWING AROUND 50 PERCENT WEAR.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120600047	20021206	00047	NM  	2002	12	6	CA021108002      	1	20021025	G	2530		HEATER          			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					GALLEY	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE TROUBLE SHOOTING SEVERAL SNAGS REGARDING PROBLEMS FOR 'NO WATER IN FORWARD GALLEY HALF WAY THROUGH FLIGHT' W	ATER LINE RIBBON HEATER FOR WATER LINE ABOVE NOSE WHEEL WELL FOUND BURNED AND BADLY DAMAGED.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2002120600055	20021206	00055	GL  	2002	12	6	CA021108008      	3	20021107	G	6112	3E23604	HARNESS         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) PROPELLER DE-ICE FAILURE INDICATION REPORTED. DEFECT WAS FOUND AS AN INTERMITTENT OPEN CIRCUIT ON ONE OF THE DEICE	 HARNESS LEADS. PART REPLACED WITH NEW. THIS DEFECT OCCURRED 106.2 HRS PREVIOUS,TWO DIFFERENT HARNESS ASSY WERE REPLACED	 AT THAT TIME. THE 4TH HARNESS WAS ALSO REPLACED AS A PREVENTATIVE MEASURE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120600056	20021206	00056	EA  	2002	12	6	CA021108009      	2	20021011	G	7414	67542	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					LEFT MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ENGINE, LT MAGNETO. DAMAGE WAS DISCOVERED DURING ACCOMPLISHMENT OF AN UNRELATED AIRWORTHINESS DIRECTIVE KNOWN A	S, AD2002-20-51.  REMOVAL OF ALL ACCESSORIES ON THE ACCESSORIES HOUSING WAS REQUIRED, FOR THIS AD. WHEN THE MAGNETO WAS 	REMOVED THE MAGNETO GEAR RETAINER  ASSY AND BEARING PULLED OUT OF THE ENGINE TOGETHER WITH THE DRIVE COUPLING YET AGAIN.	UPON FURTHER INSPECTION NO DAMAGE TO THE GEAR RETAINER  ASSY AND BEARING WAS FOUND AND ASSEMBLY WAS REINSTALLED.ALSO THE	 BEARING RECESS WAS INSPECTED AND CHECKED O.K.		1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2002120600058	20021206	00058	EA  	2002	12	6	CA021108010      	2	20021025	G	7414	67542	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					LEFT MAG RECESS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ENGINE,  LT MAGNETO.  DAMAGE WAS DISCOVERED DURING ACCOMPLISHMENT OF AN UNRELATED AD, REMOVAL OF ALL ACCESSORIE	S ON THE ACCESSORIES   HOUSING WAS REQUIRED, FOR THIS AD. WHEN THE MAGNETO WAS REMOVED THE MAGNETO GEAR RETAINER ( ASSY 	AND BEARING PULLED OUT OF THE ENGINE TOGETHER WITH THE DRIVE COUPLING. UPON FURTHER INSPECTION IT WAS DISCOVERED THAT TH	E SHAFT OF THE  'GEAR RETAINER ASSY AND BEARING WERE DAMAGED AND REQUIRED REPLACEMENT. 'GEAR RETAINER ASSY AND BEARING W	AS REPLACED WITH NEW. ALSO THE BEARING RECESS WAS INSPECTED AND CHECKED O.K.  MAGNETO WAS INSPECTED AND IT WAS FOUND THA	T MAGNETO BEARING, SHAFT AND ARMATURE WAS DAMAGED BEYOND REPAIR.   MAGNETO WAS ALSO REPLACED WITH SERVICEABLE MAGNETO.	1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2002120600070	20021206	00070	EA  	2002	12	6	CA021108011      	2	20021028	G	7414	67542	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					LEFT MAG RECESS	DESTROYED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  LT ENGINE, LT MAGNETO.  DURING A 100 HR INSP, OIL FILTER OF LT ENGINE WAS SECTIONED AND INSPECTED. METAL WAS FOUN	D IN FILTER.  SUCTION SCREEN WAS REMOVED AND INSP, PIECES OF A BEARING DISCOVERED.  FURTHER DISASSEMBLY WAS REQUIRED.  L	T OR RT MAGNETO WAS SUSPECTED.  ONCE LT MAGNETO WAS REMOVED, MAGNETO GEAR RETAINER ASSY, AND BEARING DROPPED OUT OF THE 	ENGINE WITH THE DRIVE COUPLING, DRIVE COUPLING NUT AND COTTER-PIN.  GEAR RETAINER BEARING HAD COMPLETELY DESTROYED ITSEL	F. UPON FURTHER INSP, IT WAS DISCOVERED THAT THE SHAFT OF THE GEAR RETAINER ASSY WAS BADLY DAMAGED.  THE BEARING RECESS 	 WAS SERIOUSLY DAMAGED. MAGNETO WAS INSPECTED AND FOUND THE MAG BEARING SHAFT AND ARMATURE WAS DAMAGED BEYOND REPAIR.	1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2002120600073	20021206	00073	NE  	2002	12	6	CA021108012      	3	20021030	G	6110	E3932	HUB             			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON DISASSEMBLY, C792 BEARING WAS FOUND TO BE BROKEN CAUSING DAMAGE TO HUB RENDERING IT UNSERVICEABLE. UPON REMOV	ING PAINT FROM 3 BLADES, CRACKS WERE DISCOVERED IN THE SHANK AREA IN THE COMPOSITE MATERIAL. AS THIS DAMAGE IS NOT ADDRE	SSED IN THE O/H MANUAL,THESE BLADES HAVE BEEN FORWARDED TO THE MANUFACTURER FOR EVALUATION.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002120600075	20021206	00075	CE  	2002	12	6	CA021108013      	1	20021105	G	5610	17360015	WINDSHIELD      			LEAR  	45    	45LEAR      	5170805	CE  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA						617					(CAN) OUTER GLASS FACE PLY 0.12 INCH SHATTERED.						2	L	7	2 	4F			RT	T00008WI					 
2002120600081	20021206	00081	EA  	2002	12	6	CA021108016      	2	20021030	G	8520	LTIO540J2BD	ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RIGHT	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT OF YYC RT POWERPLANT BEGAN TO SURGE 300 TO 400 RPM. PILOT ADVISED TOWER AND RETURNED TO AIRPORT. NOTE	D THAT ONCE POWER WAS REDUCED POWERPLANT, THEN RAN NORMALLY. ONCE ON GROUND, ADDITIONAL ANTI ICE HOLES DRILLED IN BREATH	ER LINE AND 2 LBS PRESSURE ADDED TO PROP DOME. AIRCRAFT GROUND RUN & NO FAULTS FOUND, AIRCRAFT RELEASED FOR FURTHER FLIG	HT.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002120200182	20021202	00182	WP  	2002	12	2	CA021108018      	1	20021016	G	3233	1523042101	ACTUATOR        	            	            	LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  	 		            		LUG	CRACKED         	W			    	K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA		 									(CAN) WHILE PERFORMING A MLG RETRACTION TEST, AFTER REPLACEMENT OF ALL GEARS ON A/C, WE NOTICED AFTER A COUPLE RETRACTIO	NS, THAT THE MLG ACTUATOR PIN (P/N 1523042-101, REF IPC 32-11-03, ITEM 435) OF THE MLGRETRACT ACTUATOR ON THE R/H MLG WA	S CRACKED. RETRACTION SPEED WAS NORMAL. AFTER REPLACEMENT OF THELOWER PIN  (P/N 1523042-101, REF IPC 32-11-03, ITEM 435 	AND REPLACED IAW AMM 32-11-27) AND MLG RETRACTACTUATOR (P/N 1523042-101, IPC 32-11-03, ITEM 405 AND REPLACED I.A.W AMM 3	2-33-01), ON THE NEXT RETRACTION, WE FOUND OUT THAT THEJURY BRACE ASSYWAS MAKING A SNAP SOUND AND THE LAST MOVEMENT OF T	HEACTUATOR WAS TOO FAST (NO SNUBBER ACTION). AFTER REPLACEMENT OF THE  JURY BRACE RETRACT ACTUATOR(P/N 1523107-105, IPC 	2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002120900002	20021209	00002		2002	12	9	CA021112005      	4	20021030	G	8300	996881	CLUTCH          			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  	GEARBOX	SLIPPED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF, ON GO AROUND ENG SEEMED TO SURGE & SLIGHTLY OVERSPEED. STARTED AS AN INTERMITTENT CONDITION AND DU	RING A COUPLE WEEKS DEGRADED. STARTED SURGING SLIGHTLY IN CRUISE. PROP & GOV WERE REPLACED FOR TROUBLESHOOTING. NO CHANG	E. ALL OIL SUPPLY LINES TO GOV CHECKED, OIL PUMP SUCTION CHECKED. NEW OIL COOLER INSTALLED. PROBLEM WENT AWAY FOR 1 WEEK	. GEARBOX REMOVED, OIL TRANSFER SPIGOT CHECKED, OIL PUMP REMOVED AND CHECKED. NO PROBLEMS. ENG GROUND RUN AND RPM OF PRO	P CHECKED WITH TACH. ENG RPM SURGED HIGHER THAN PROP RPM WHEN THROTTLE ADVANCED RAPIDLY. OVERLOAD CLUTCH SLIPPING. CLUTC	H REMOVED FROM GEARBOX. SLIPS AT 210 FT/LB. THRUST WASHER WORN BELOW LIMITS. CLUTCH REPLACED. RUN UP AND NO PROBLEMS.	1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO	 
2002120900004	20021209	00004	CE  	2002	12	9	CA021112007      	1	20021104	G	7920	3035890	LINE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE OIL	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INTERFERENCE OCCURRING BETWEEN OIL TRANSFER TUBE AND ANTI ICE FLEX LINE CAUSED TWO GOUGES IN OIL TRANSFER TUBE .01	5 INCH AND .017 INCH DEEP. WALL THICKNESS OF OIL TRANSFER TUBE IS .025 INCH. THE PROBLEM WAS DETECTED AT SCHEDULED INSPE	CTION. THE PROBABLE CAUSE WAS FAILURE TO ENSURE A DEQUATE SEPARATION BETWEEN THE OIL TUBE AND THE ANTI ICE FLEX LINE DUR	ING INSTALATION OF THE FLEX LINE.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003011500001	20030115	00001	GL  	2003	1	15	CA021112009      	1	20021112	G	6123		SWITCH          			AMTR  	AVRO  	LANCASTER10 	       	GL  	PCKARD	224   	224         	 	SO  	HAMSTD	23E	23EX583     	NE  	PROP FEATHERING	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF, PILOT EXPERIENCED DIFFICULTY CONTROLLING NR 4 PROP RPM.  AFTER INFLIGHT SHUT DOWN, PILOT UNABLE TO	 FEATHER NR 4 PROPELLER.  UPON INSPECTION, NR 4 PROP FEATHERING SWITCH WAS FOUND TO HAVE FAILED INTERNALLY IN SUCH A MAN	NER THAT IT WAS TURNING THE PROP FEATHERING PUMP ON/OFF UNCOMMANDED. THIS SUBSEQUENTLY CAUSED THE RPM CONTROL DIFFICULTY	 WITH THE GOVERNOR.  THE PROP FEATHERING PUMP MOTOR FAILED DUE TO OVER- EXTENDED USE, WHICH CAUSED THE PILOT AN INABILIT	Y TO FEATHER THE ENGINE.  BOTH COMPONENTS WERE REPLACED AND AIRCRAFT EXTENSIVELY TESTED PRIOR TO TEST FLIGHT.		2	H	7	4 	4V	4	V	RC	EXPA2M74	EXP4V	6	C	EXPP6C	 
2003011400078	20030114	00078	NE  	2003	1	14	CA021113003      	2	20021031	G	7250	112000014	NOZZLE          								LYC   	T53   	T5313B      	41549	NE  					2ND GP	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) MILITARY PARTS FOUND INSTALLED ON ENGINE S/N LE-07616.  INSTALLED PART MANUFACTURER CODE NUMBER IS 81996 (US MILIT	ARY).  IT SHOULD BE 91547. (HONEYWELL OEM).  ENGINE S/N LE-07616 OVERHAULED ON 31 MARCH 1993 AT ENGINE TSN:2979.051.  2N	D GP NOZZLE P/N 1-120-000-14  S/N: AC102 2) SEAL HOUSING  P/N 1-140-190-05  S/N: 01359M3) RETAINING RING P/N 1-100-890-0	3								4	U			E17EA				 
2003011400079	20030114	00079	NE  	2003	1	14	CA021113004      	2	20021031	G	7250	119005007	NOZZLE          			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					1ST STAGE PT	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) MILITARY PART FOUND INSTALLED ON ENGINE S/N LE-81004. INSTALLED PART MANUFACTURER CODE NUMBER IS 81996, (US MILITA	RY) IT SHOULD BE 91547. (HONEYWELL OEM) ITEM INSTALLED 7TH MARCH 2001.					1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
2002120900007	20021209	00007	EA  	2002	12	9	CA021113005      	2	20021106	G	7200	3020807	CASE            			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN CASE 6 O`CLOCK POSITION BY FUEL DUMP VALVE.						1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2002120900017	20021209	00017	EA  	2002	12	9	CA021115001      	1	20021107	G	2797		WIRE HARNESS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA			16666								(CAN) AFTER TAKE OFF,  WHEN FLAPS WERE RETRACTED, STALL FAIL CAUTION MESSAGE APPEARED ACCOMPANIED BY HYD CAUTION FOR HYD	 PUMP 1B & 3B.  STALL TAPE ON CAPTAINS & F/O'S PFD APPEAR TO RUN FULL LENGTH OF AIR SPEED INDICATOR.  AIRCRAFT FERRIED F	OR TROUBLESHOOTING. R&R FLAP POSITION TRANSMITTER WIRING HARNESS AND OPS CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002120900019	20021209	00019	EA  	2002	12	9	CA021115002      	2	20021105	G	8550	CH48108	OIL FILTER      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	SEPARATED       	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											CAN-  OIL PRESSURE WAS FLUCTUATING ON START. PRESSURE RELIEF VALVE WAS INSPECTED & FOUND TWO PIECES OF 3/8 TO 1/2 INCH R	UBBER (FROM THE OIL FILTER) WAS FOUND IN THE BAY & SEAT AREA. OIL FILTER REMOVED FOR INSPECTION, WAS SHOWING EVIDENCE OF	 RUBBER PART DETERIORATION. AIRWOLF OIL FILTER SYSTEM STC SH1252ME REMOVED & ORIGINAL OIL SCREEN & HOUSING WAS INSTALLED	 ON THE ENGINE.			1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002120900061	20021209	00061	CE  	2002	12	9	CA021115004      	1	20021005	G	5410	555211060	DOOR            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT ENG NACELLE	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) RT ENGINE ANTI-ICE VALVE REPLACED, INVESTIGATION SHOWS THAT INNER HALF OF LOWER COWLING FASTENERS NOT SECURED. AIR	CRAFT DEPARTED YVR, CREW NOTICED A 'BANG' AND THEN A CONSTANT VIBRATION, GOING THROUGH 8,000 FT, CLIMBING OUT.  CREW CON	TINUED TO CLIMB THROUGH 15,000 FT, BEFORE DECLARING AN EMERGENCY AND RETURNING TO YVR AND COMPLETING A NORMAL LANDING ON	 RUNWAY 12.  INVESTIGATION SHOWED RT LOWER ENGINE COWLING PARTIALLY DETACHED FROM AIRCRAFT AND SKIN KINKED AND BENT, AND	 FORWARD OUTER FASTENER HOLES TORN.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002120900064	20021209	00064	SO  	2002	12	9	CA021115006      	1	20021113	G	5554	4A3441	ATTACH ANGLE    			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19257	19257							(CAN) DURING A SCHEDULED INSPECTION EVENT EXCESSIVE WEAR WAS NOTED AROUND THE BOLT HOLE OF THE UPPER RUDDER ATTACH BRACK	ET. THE RIVETS SECURING THE BUSHING BOSS IN THE BRACKET WERE ALSO WORKING.THE RUDDER ATTACH BRACKET ASSEMBLY PART NUMBER	 4A-3441 WAS REPLACED.				1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2002120900066	20021209	00066	EU  	2002	12	9	CA021115008      	1	20021029	G	3242	23203500	DISK            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION FOUND RT BRAKE ASSEMBLY TO HAVE A BROKEN ROTOR DISK. BRAKE ASSEMBLY REPLACED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120200184	20021202	00184	CE  	2002	12	2	CA021115009      	1	20021105	G	3260	12700341	SQUAT SWITCH    	            	            	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	WIRING	FAILED          	W			    	K	 	 	 	NONE                    				R	 	 	PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA		 									(CAN) PILOT SELECTED GEAR UP AFTER TAKEOFF AND GEAR MOTOR 'APPEARED' TO RUN ON, AND NO GEAR-UP INDICATION WAS NOTED. PIL	OT SELECTED GEAR DOWN AND GOT CORRECT INDICATION AND MOTOR STOPPED AS NORMAL. PILOT CONTINUED BACK TO HOME BASE WITH GEA	R DOWN AND NO FURTHER INCIDENT. MAINTENANCE DISCOVERED BROKEN WIRE INTERMITTENTLY MAKING CONTACT IN NOSE SQUAT SWITCH. R	EPLACED SWITCH WITH NEW P/N 1270034-4 GEAR SWUNG - SYSTEM FOUND SATISFACTORY.			1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2002120900069	20021209	00069	SO  	2002	12	9	CA021115010      	1	20021107	G	2434		BEARING         			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					LT GENERATOR	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) LT GENERATOR TRIPPED,  PILOTS REPORTED AN UNDER VOLTAGE CONDITION.ACTION: LT GENERATOR REMOVED, UPON INSPECTION OF	 COMPONENT, GEARING ASSEMBLY PARTS HAD MIGRATED TO, AND SHORTED OUT A BRUSH HOLDDOWN SPRING TO THE GENERATOR CASE.					2	L	7	2 	4T	4	T	 	1A17    	E297				 
2002120900079	20021209	00079	EU  	2002	12	9	CA021115013      	1	20021112	G	2752	9787320307	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE OF THE AIRCRAFT. THE FLAPS WERE SELECTED DOWN TO THE 40 DEGREE POSITION. DURING MOVEM	ENT OF THE FLAPS A 'GRINDING' NOISE WAS HEARD COMING FROM THE L/H INBOARD FLAP ACTUATOR. THE ACTUATOR BECAME VERY HOT AN	D WOULD CAUSE THE FLAPS TO STALL. THE AIRCRAFT HAD RETURNED FROM A TRIP APPROX. (1)  HOUR PRIOR TO THE DEFECT OCCURRING.	 THE PILOT DIDNOT INCOUNTER ANY FAILURE OF THEFLAP SYSTEM DURING THE FLIGHT. A REPLACEMENT ACTUATOR WAS INSTALLE D AND N	O FURTHER DEFECTS WERE NOTED.RECENT PROBLEMS WITH THIS AIRCRAFTS FLAP SYSTEM, WERE THE RESULT OF ACTUATORS FREEZING AT A	LTITU DE. THIS IS OUR FIRST INCIDENT WHERE SUCH A FAILURE HAS OCCURRED.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120900080	20021209	00080	EU  	2002	12	9	CA021115014      	1	20021103	G	3242	23203500	DISK            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE ASSY	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING LT WHEEL BRAKE LOCKED UP AND SKIDDED TIRE. ON INSPECTION FOUND ROTOR DISK AND BROKEN INTO 2 PIECES AND 	JAMMED BRAKE ASSEMBLY. BRAKE ASSEMBLY AND TIRE REPLACED. ON INSPECTION OF R/H BRAKE ASSEMBLY, FOUND ONE ROTOR DISK ALSO 	BROKEN. BUT THIS ASSEMBLY STILL FUNCTION WITHOUT LOCK UP. REPLACED RT BRAKE ASSY. THIS IS THE 3RD DISK IN 5 DAYS.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002120900090	20021209	00090	SO  	2002	12	9	CA021115023      	1	20021115	G	5751	1710013	RIB             			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					RT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HOURS INSPECTION, FOUND RT AILERON INBOARD TRAILING EDGE RIB CRACKED AROUND BOTTOM MOUNTING NUT. UPON R	EMOVAL OF RIB, THE AILERON SPAR IS ALSO CRACKED AT SAME LOCATION.					1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2003011400080	20030114	00080	CE  	2003	1	14	CA021118003      	1	20021113	G	3230	50450102	TORQUE TUBE     			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470VO     	17026	SO  					MLG	CRACKED         	W				A				UNSCHED LANDING         				E	N		VIBRATION/BUFFET          	FALSE WARNING             		CL	CLIMB          	1			CA											(CAN)   ON T/O,  A CLUNK HEARD NEAR END OF MLG TRAVEL DURING RETRACTION.  NO DIFFERECE IN FLT CONTROL.   PILOTS INFORMED	 RT MLG HANGING.  MLG SELECTED DOWN STEEP BANKS & YAWS PERFORMED TO GET RT MLG LOCKED.  NO DOWN & LOCKED IND EVIDENT, A/	C LANDED UNEVENTFULLY.  RT MLG NOT LOCKED, SIDE BRACE LOCK NOT OVER-CENTER AND DOWNLOCK SPRING BROKEN.  JACKED A/C, RT T	ORQUE TUBE ASSY BROKEN AT OTBD PUSH-PULL TUBE ATTACH POINT.  INVEST REVEALED A CRACK AT ATTACH POINT.  THERE IS NO SPECI	AL INSPECTION ON THIS PART OF MLG, DIFFICULT TO DETECT A CRACK WITHOUT REMOVING TORQUE TUBE FROM A/C.  TORQUE TUBE AND R	ETRACTION SYSTEM TEARDOWN AND INSPECT REQUIRE INITIAL INSPECTIONS AT 10000 HOURS. A/C HAS ONLY 7621.4 HOURS SINCE NEW.	1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2002120900101	20021209	00101	CE  	2002	12	9	CA021118004      	1	20021113	G	3260	50410051	SPRING          			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470VO     	17026	SO  					RT MLG DOWNLOCK	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) SUBSEQUENT TO THE RT MAIN GEAR FAILURE TO LOCK AND FINDING THE TORQUE TUBE CRACKED, THE DOWNLOCK SPRING WAS ALSO B	ROKEN.  HAD THIS SPRING BEEN INTACT THE GEAR WOULD HAVE FREE-FALLEN DOWN AND LOCKED. THERE IS NO RIGGING OR ADJUSTMENT O	N THESE SPRINGS.  BOTH LT & RT SPRINGS WERE REPLACED NEW, THE RT FAILING AFTER 164.4 HOURS AND AGAIN AFTER 25.1 HOURS.  	ALL SPRINGS WERE FOUND TO BE OF THE SAME ORIGIN AND THE INTACT LT SPRING HAS BEEN REMOVED FROM THE AIRCRAFT.ALL SPRINGS 	HAVE BEEN SUPPLIED TO OUR PMI FOR FURTHER INVESTIGATION.		1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2002120900104	20021209	00104	CE  	2002	12	9	CA021118007      	1	20021118	G	2810	051600918	TANK            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					MAIN FUEL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HEADER TANK FOUND LEAKING.  UPON REMOVAL, TANK HAS A 1 INCH CRACK ON TOP OF WELD AROUND BOTTOM AFT SIDE OF TANK.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002120200185	20021202	00185	CE  	2002	12	2	CA021118008      	1	20021107	G	7160	TA8071	BAFFLE          	CONT        	O320E2D     	CESSNA	172   	172         	2072402	CE  	LYC   	O320  	O320E2D     	41508	EA  	 		            		AIRBOX BAFFLE	BROKEN          	W			    	A	D	 	 	UNSCHED LANDING         	RETURN TO BLOCK         			R	 	 	PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA		 									(CAN) A PIECE OF BAFFLE BROKE OFF OF THE AIRBOX BAFFLE CONTROL. THE PIECE LOGGED IN THE CARBURETOR VENTURIRESULTING IN A	 RICH MIXTURE AND PARTIAL POWER LOSS. REPAIRS MADE BY AMO 98.91, OCTOBER 28/02. INCIDENT REPORTED AS POWER LOSS DUE TO C	ARB ICE - SUBSEQUENT RUN-UP REVEALED THE PROBLEM WAS NOT DUECARB ICE BUT RICH MIXTURE AND ROUGH RUNNING UNTIL LEAN - MAI	NTENANCE ARRANGED.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002120200186	20021202	00186	CE  	2002	12	2	CA021118009      	1	20021116	G	2434	C6115050201	ALTERNATOR      	CESSNA      	C6115050201 	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ALTERNATOR	                	W			    	D	 	 	 	RETURN TO BLOCK         				J	L	 	WARNING INDICATION        	NO TEST                   		CR	CRUISE         	1			CA		 				2310					(CAN) PILOT REPORTED STANDBY ALTERNATOR INOP LIGHT CAME ON.  THE SYSTEM WAS SHUT DOWN AND RETURN TO BASE. THE ALTERNATOR	 WAS FOUND TO BE UNSERVICABLE. A SEARCH OF THE AIRCRAFT RECORDS FOUND THAT THIS WAS T HE ORIGINAL ALTERNATOR.  THERE IS 	NO T.B.O. PUT ON THIS UNIT FROM CESSNA.  THE BASE PUT A 3000 HOUR TBO ON THE ALTERNATOR.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002120900179	20021209	00179	CE  	2002	12	9	CA021119008      	1	20021025	G	3246	704AC5225	FLYING WIRE     			CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300C       	17022	SO  					FLOAT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HARD LANDING ON GATINEAU RIVER - BROKE BOTH FLYING WIRES THAT ATTACH UPPER LT HAND AND LOWER RT HAND. THIS ALLOWED	 THE AIRPLANE TO GO DOWN ON RT WING TIP. THIS BROKEN THE ATTACH FITTINGS ON END OF REAR AND DIAGONAL STRUTS.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002120900180	20021209	00180	CE  	2002	12	9	CA021119009      	1	20021108	G	5511	043200146	RIB             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13643								(CAN) THE LT INBOARD LEADING EDGE RIB CRACKED AT TOP REAR CORNER.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002120900181	20021209	00181	CE  	2002	12	9	CA021119010      	1	20021108	G	5511	04320016	RIB             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13643								(CAN) THE RT INBOARD LEADING EDGE RIB CRACKED AT TOP REAR CORNER.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002120900182	20021209	00182	SO  	2002	12	9	CA021119011      	2	20021101	G	8530	654961	CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CONDUCTING A CYLINDER COMPRESSION TEST, THE FOLLOWING RESULTS WERE DISCOVERED:CYLINDER 1-40PSI, 2-45PSI, 3-0	PSI, 4-0PSI,5-40PSI, 6-58PSITHE MEASURE OF THE CYLINDER BARRELS INDICATES THAT THEY SHOULD MEASURE '10 THOU OVERSIZE'. T	HE EXHAUST VALVES ARE ALL WORN, MOREOVER THE INTAKE VALVES ARE ALSO WORN AT THE NEEDLE SHAFT AND TOO THIN ATTHE BASE OF 	THE VALVE.			1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2002120900183	20021209	00183	CE  	2002	12	9	CA021119012      	1	20021116	G	2810	07161249	FLAPPER VALVE   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					LT FUEL CELL	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) VALVE ASSEMBLY CENTER SECTION PIN AND SPRING FAILURE.  THE FAILURE ALLOWED FUEL TO EXIT FUEL VENT SYSTEM.  CORRECT	 BY REPLACING ENTIRE VALVE ASSEMBLY.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003011400091	20030114	00091	SO  	2003	1	14	CA021120001      	2	20021114	G	8550	C1650010202	SCREEN          			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	AIR/OIL SEP	DESTROYED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING OPERATION 1 INSPECT, NON FERROUS METAL FOUND IN LT OIL FILTER AND SCREEN.  INSPECTED FILTER AGAIN IN 20 HOU	RS.  IN LESS THAN 15 HOURS OIL WAS DRIPPING ONTO LT MLG. PAINT REMOVED FROM CRANKCASE FWD OF ALTERNATOR, CRACK WAS CONFI	RMED BY DEVELOPER. ENG REMOVED FOR CRACK REPAIR AND SHOP NOTIFIED TO INSPECT FOR SOURCE OF CONTAM FOUND IN FILTER AFTER 	14.6 HOURS. SHOP COULDN`T FIND SOURCE. RETURN LINE REMOVED FROM AIR/OIL SEPARATOR, METAL FOUND IN HOSE. SEPARATOR, REMOV	ED, & CUT APART. INSIDE SCREEN & HOLDER HAD VIBRATED APART & ALUMINUM GETTING TO CRANKCASE THROUGH RETURN LINE.  PRESS H	OSE TO BOOTS & PRESSURE FILTER HAD A LARGE AMOUNT OF METAL SCREEN PARTS TRAPPED INSIDE.	1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2002121100004	20021211	00004	GL  	2002	12	11	CA021120005      	3	20021112	G	6111	T10282	BLADE           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINEER NOTICED CRACKED TRAILING EDGE OF PROPELLER BLADE, FOUND DURING POST FLIGHT INSPECTION IN THE HANGER.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2002121100005	20021211	00005	CE  	2002	12	11	CA021120006      	1	20021110	G	3340		SWITCH          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LANDING LIGHT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) SMOKE IN THE CABIN WAS DETERMINED TO BE FROM THE LANDING LIGHT SWITCH. SWITCH WAS SHUT-OFF BUT CONTINUED TO SMOKE.	 ONLY WAY TO STOP SMOKING WAS TO TURN OFF THE BATTERY MASTER AS THE CIRCUIT BREAKER IS OF A TYPE THAT CANNOT BE MANUALLY	 PULLED. NEW SWITCH AND CIRCUIT BREAKER WAS INSTALLED AFTER AIRCRAFT WIRING AND LANDING LIGHT CHECKED SERVICABLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002121100008	20021211	00008	CE  	2002	12	11	CA021121003      	1	20021119	G	2701	556575717	SHAFT           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CONTROL PED	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CLAMP SCREW ON THE FLIGHT DIRECTOR MODE SELECTOR CONNECTOR PLUG RUBBED AGAINST THE AILERON TRIM CONTROL SHAFT 	ABOUT 3 INCHES FROM THE AFT END OF THE SHAFT. THE 1/4 INCH SOLID STEEL SHAFT WAS WORN TO .238 INCH DIAMETER AT THIS CONT	ACT POINT. 3/8 INCHES OF EXCESS SCREW WAS CUT OFF TO PREVENT FURTHER WEAR. A FLEET CAMPAIGN INSPECTION HAS BEEN INITIATE	D.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002121100009	20021211	00009	SO  	2002	12	11	CA021121004      	1	20021117	G	3220	6716800	SPRING          			PIPER 	PA44  	PA44180     	7104402	SO  										NLG	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) A STUDENT PILOT SELECTED LANDING GEAR DOWN, WHEN IT WAS NOTICED THAT THE NOSE LANDING GEAR TOOK APPROX. 2 MIN. TO 	EXTEND.  THE AIRCRAFT WAS LANDED SAFELY AND MAINTENANCE WAS NOTIFIED.  IT WAS NOTICE THE NOSE LANDING GEAR DOWN ASSIST S	PRINGS WERE POSITIONED DIFFERENTLY.  FURTHER INVESTIGATION REVEALED THAT THE INNER SPRING WAS BROKEN AND WAS JAMMING THE	 OUTER SPRING, THUS RESULTING IN THE LENGTH OF TIME IT TOOK TO LOWER THE GEAR.  IT IS SPECULATED THAT THE BUILD UP OF HY	DRAULIC PRESSURE FINALLY PUSHED THE GEAR DOWN AND LOCKED. BOTH THE INNER AND OUTER SPRINGS WERE REPLACED NEW.  IT IS BEL	IEVED THAT CYCLES AND FATIGUE CONTRIBUTED TO SPRING BREAKING.	1	L	7	2 	3O			 	A19S0   					 
2002121100010	20021211	00010	CE  	2002	12	11	CA021121005      	1	20021030	G	7160	1099100299	DUCT            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE INLET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOWER FWD ENGINE COWLING FOUND CRACKED.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002121100012	20021211	00012	NE  	2002	12	11	CA021121007      	3	20021121	G	6114	B70192	SETSCREW        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN)   PROPELLER WAS REMOVED FOR A GREASE LEAK, WITH NO INDICATIONS OF LOOSE BLADES.  UPON DISASSEMBLY BLADE PRELOAD SE	T SCREW WAS FOUND CRACKED AND ONCE CLEANED THE TIPS FELL OFF OF NR 2.  BLADES WERE WITHIN THEIR BLADE PLAY LIMITS IN THE	 HUB PRIOR TO DISASSEMBLY. SEVERE WEAR WAS FOUND ON THE PRELOAD PLATES.   PROCEEDED TO CHECK NEW SET SCREWS FROM STOCK, 	AND 21 OUT OF 24 WERE FOUND CRACKED VIA VISUAL INSPECTION USING A 10X MAGNIFYING GLASS.  MANUFACTURER WAS NOTIFIED AND T	HEIR STOCK WAS CHECKED.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002121100014	20021211	00014	CE  	2002	12	11	CA021122002      	1	20020720	G	5551	07321014	BRACKET         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THE REINFORCEMENT BRACKETS WERE CRACKED. NEW PARTS 0732101-4 WERE 	INSTALLED.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2002121100015	20021211	00015	CE  	2002	12	11	CA021122003      	1	20020920	G	5312	07120487	BULKHEAD        			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	TAIL CONE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE ANGLE TAILCONE REINFORCEMENT LT IN THE TAILCONE BULKHEAD 	ASSEMBLY WAS CRACKED.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2002121100016	20021211	00016	CE  	2002	12	11	CA021122004      	1	20021030	G	3211		TUBE            			BEECH 	17    	D17S        	1150538	CE  	PWA   	R985  	R985AN1     	52008	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STRUCTURAL TUBE, 10CM IN LENGTH, FORMING UPPER SUPPORT FOR RT LANDING GEAR SLIDE TUBE FOUND CRACKED DURING PERFORM	ANCE OF UNRELATED MAINTENANCE. CRACK ORIGINATED FROM HOLE IN TUBE USED TO APPLY LINSE ED OIL TO INTERIOR OF TUBE. HOLE H	AD BEEN PLUGGED WITH RIVET. CRACK 1.5CM IN LENGTH WAS EXTENDING AROUND THE CIRCUMFERENCE OF THE TUBE. TUBE WAS CUT FROM 	AIRCRAFT STRUCTURE AND NEW PIECE WELDED IN.			1	Q	7	1 	3R	3	R	 	A649    	5E1				 
2003011400097	20030114	00097	EA  	2003	1	14	CA021122006      	2	20021115	G	8530	LW11633	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CYLINDER BARREL CRACKED,  2 INCHES LONG AT BOTTOM OF CYLINDER HEAD.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002121100017	20021211	00017	CE  	2002	12	11	CA021122008      	1	20021122	G	2711	556575717	SHAFT           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AILERON CONTROL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DAMAGE WAS FOUND ON THE AILERON TRIM CONTROL SHAFT MIDWAY BETWEEN THE TRIM WHEEL AND CHAIN GEAR. THIS DAMAGE WAS F	OUND WHILE CARRYING OUT AN IN HOUSE CAMPAIGN (851-018) TO LOOK FOR THIS TYPE OF DAMAGE TO THE SHAFT. THE DAMAGE WAS CAUS	ED BY THE CLAMPING SCREW ON THE 'SOURCE CONTROLLER' CONNECTOR PLUG. THE SCREW IS TO LONG AND CONTACTS THE TRIM SHAFT. DA	MAGE WAS .004 OR AND INCH DEEP WITH A DRESSED OUT DEPTH OF .006 OF AN INCH AFTER REPAIR.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002121100018	20021211	00018	NM  	2002	12	11	CA021122009      	1	20021007	G	3397	320562	SPLICE          			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CABIN	OVERHEATED      	W				K				NONE                    				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) WHILE AIRCRAFT WAS IN HEAVY MAINTENANCE, TECHNICIANS DISCOVERED HEAT DAMAGE TO SEVERAL WIRING COMPONENTS FOR THE P	ASSENGER SERVICE UNIT READING LIGHTS, ON THE LT SIDE OF THE AIRCRAFT JUST AFT OF THE MAIN CABIN DOOR. WIRING SPLICES EXH	IBITED SIGNS OF OVERHEATING, AND ADJACENT WIRING WAS HEAT DAMAGED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003010600212	20030106	00212	SO  	2003	1	6	CA021124001      	2	20021121	G	7414	103493505	MAGNETO         			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PREFORMING ROUTINE MAINTENANCE, IT WAS FOUND THAT THE LT MAGNETO COULD NOT BE TIMED. IT APPEARS THAT THE MAG	NETO POINTS ARE NOT OPENING. MAGNETO REPLACED WITH OVERHAULED UNIT AND TIMED NORMALLY. GROUND RUN CHECKS ALL OK.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003011400126	20030114	00126	EU  	2003	1	14	CA021125001      	1	20021109	G	7921	RK35782A	OIL COOLER      			BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5342    	 	EU  					ENGINE	LEAKING         	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT TOOKOFF FROM YZG FOR YUZ,  AFTER TAKEOFF IN FLIGHT THE RT ENGINE OIL PRESSURE LIGHT CAME ON, OIL PRESSURE	 ZERO, PILOT SHUTDOWN ENGINE. ON ARRIVING TO YVP, INSPECTION WAS CARRIED OUT, AND RT OIL COOLER HONEYCOMB WAS LEAKING. R	T OIL COOLER WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	3T	4	T	 	A24EU   	A196				 
2003011400127	20030114	00127	SO  	2003	1	14	CA021125003      	2	20021105	G	7310		SHIELD          			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O520  	TSIO520NB   	17040	SO  					FUEL DIST HEAD	MISSING         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA		3055E									(CAN) A/C ENROUTE AT FLIGHT LEVEL 210,  DECLARED AN EMERGENCY.  AIRCRAFT TURNED BACK.  PILOT REPORTED ROUGH RUNNING ENGI	NE & MISFIRING BADLY  A/C LANDED SAFELY.  PILOTS EXPERIENCED POWER LOSS ON NR 3 CYLINDER FIRST & THEN ON BOTH NR 3 & 4 C	YLINDERS. ENGINE IS EQUIPPED WITH CYLINDER HEAD TEMPERATURE PROBES FOR ALL CYLINDERS & COULD SEE 3 & 4 AS COLD CYLINDERS	. BASED ON THE INVESTIGATION PILOTS ARE CONFIDENT PROBLEM WAS ICE CRYSTALS IN THE FUEL.  FUEL IS FEED TO THE CYLINDERS F	ROM A DISTRIBUTION HEAD ON THE TOP OF ENGINE.  A SHIELD THAT IS DESIGNED TO DEFLECT COLD AIR FROM THE DISTRIBUTION HEAD 	AND THE LINES COMING FROM IT, REQUIRED BY AN AD.	1	L	7	1 	3O	3	O	 	2A3     	E8CE				 
2003011400130	20030114	00130	EU  	2003	1	14	CA021125006      	1	20020917	G	2435	P6007052	BELL ASSY       	AUXILEC     		SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					STARTER GEN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2383					(CAN) WHILE COMPETING A DAILY INSPECTION ON THE AIRCRAFT THE ENGINEER NOTICED A CRACK ON THE DRIVE END BELL ON THE START	ER GEN.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003013000026	20030130	00026	EA  	2003	1	30	CA021125009      	3	20021113	G	6111	M76AM	PROPELLER       													SNSNCH	76AM	M76AM       	EA  	LEADING EDGE	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER WITH NO HISTORY SENT IN FOR OVERHAUL. - DURING LIQUID PENETRANT INSPECTION, FOUND SUSPICIOUS WELDING WIT	H EDDY CURRENT CONDUCTIVITY PROBE AS WELDED AREA MATCHED GOOD AREA. KELLERS ETCH SHOWED DISCOLOURATION AND CHROMIC ACID 	ANODIZING CONFIRMED WELDING HAD TAKEN PLACE. AS MOST PROP SHOPS DO NOT HAVE ANODIZE FACILITIES, THIS IS A TOUGH IMPROPER	 REPAIR TO LOCATE.													5	N	1P210	 
2003011400135	20030114	00135	CE  	2003	1	14	CA021125010      	1	20021121	G	2720	151350013	BRACKET         			CESSNA	337   	337A        	2075704	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C59   	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON BOTH INBOARD RUDDER TORQUE TUBE MOUNTING BRACKETS. THE CRACK BEGAN AT THE AFT END OF THE BRACKET, E	XTENDING FORWARD APPROXIMATELY 3-4 INCHES ON THE LT BRACKET AND 1/2 INCH FORWARD ON THE RT BRACKET. THE CRACK OCCURRED A	T THE BEND RADIUS ON THE OUTER PIECE OF THE BRACKET.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2002121100020	20021211	00020	SO  	2002	12	11	CA021125011      	1	20021113	G	3210	AN17651	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					MLG	BROKEN          	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF, VIBRATION WAS NOTICED IN LT MAIN GEAR. INSPECTED MAIN GEAR (LT) LINK BOLT FOUND BROKEN, BOLT REPLACED.	  BEARING UP LOCK REPLACED. RETRACT GEAR CHECKED AND OK. CAUSE: TIGHT TURN ON GROUND WITH BRAKES APPLIED.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002121100021	20021211	00021	CE  	2002	12	11	CA021125012      	1	20021125	G	3020	9091010017	DUCT            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ANTI ICE SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION THE RT ENGINE COWL WAS REMOVED AND THE FLEXIBLE TUBE THAT DELIVERS EXHAUST AIR TO HEAT THE ENGIN	E COWL INTAKE WAS DISCOVERED TO BE CRACKED. THE CRACK EXTENDED APPROXI MATELY 1/3 OF THE CIRCUMFERENCE OF THE TUBE.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003011400146	20030114	00146	EU  	2003	1	14	CA021127002      	1	20021101	G	6123		PLATE           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER	DISLODGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER WAS NOT IN THE FULL FEATHER POSITION. INSPECTION SHOWED THAT THERE WAS A GAP BETWEEN THE FEATHER STOP NU	T AND THE REVERSE ADJUST SLEEVE.  PROPELLER WAS REMOVED AND SENT TO PROPELLER OVERHAUL SHOP FOR REPAIR. ON DISASSEMBLY, 	THE PRELOAD PLATE WAS FOUND TO HAVE MOVED THUS PREVENTING THE PROPELLER TO GO INTO THE FULL FEATHER POSITION. SERVICE BU	LLETIN HC-SB-61-243 REV.1 INCORPORATED. PROPELLER REINSTALLED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003011400151	20030114	00151	EA  	2003	1	14	CA021129004      	1	20021117	G	2841		COMPUTER        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FUEL QTY IND	INACCURATE      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AIRCRAFT OPERATING UNDER MEL 28-24-01-2 (XFLOW /APU FUEL PUMP INOP). ON TAKEOFF CREW NOTICED 600LB FUEL IMBALANCE.	 UNABLE TO TRANSFER FUEL FROM LT TO RT TANK USING GRAVITY FLOW. IMBALANCE INCREASED TO 2000LB IN STRAIGHT AND LEVEL DESP	ITE ALL EFFORTS. FUEL PUMP WAS REPLACED TO CLEAR THE MEL, BUT TROUBLESHOOTING REVEALED THAT FAULT CODES 701 & 702, (FAUL	TS IN BOTH CHANNEL 1 AND CHANNEL 2, WHICH MAY CAUSE ERRONEOUS FUEL SYSTEM INDICATION) WERE INDICATED, WHICH IS BELIEVED 	TO BE THE CAUSE OF THIS INCIDENT		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003011400171	20030114	00171	CE  	2003	1	14	CA021203003      	1	20021202	G	2750	9910554	MOTOR           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAPS	INTERMITTENT    	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN)  FLAPS WILL NOT RETRACT COMPLETELY.  INVESTIGATION REVEALED A SNAPPED COUPLING ON THE RT FLAPACTUATOR SHAFT AT THE	 GEARBOX. FURTHER INVESTIGATION REVEALED THE RT FLAP MOTOR WAS INTERMITENT. SUSPECT THE FLAP MOTOR BRAKE WAS NOT RELEASI	NG DURING FLAP OPERATION.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003011400176	20030114	00176		2003	1	14	CA021203007      	4	20021202	G	6122	180315	BEARING         	WOODWARD    	8210007F    															PROP GOVERNOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						180626F					(CAN) UPON DISASSEMBLY OF THIS GOVERNOR, IT WAS NOTED THAT ONE OF THE FOUR BEARING ASSEMBLIES HAD LOST ITS BALLS. BECAUS	E THERE IS NO SCREEN IN THE BASE OF THIS GASKET, ANY OIL CONTAMINATES COULD CHANNEL BACK INTO THE ENGINE.  THE GOVERNOR 	WAS COMPLETELY OVERHAULED, THE BEARINGS REPLACED, AND THE OWNER OF THE AIRCRAFT WAS ADVISED WHAT THE FINDINGS WERE.																	 
2003010600215	20030106	00215	NM  	2003	1	6	CA021203009      	1	20021130	G	2782	65449617	ACTUATOR        			BOEING	737   	737284      	138448R	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 1 SPOILER	LEAKING         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING, FLIGHT CREW REPORTED THE AIRCRAFT LOST ALL SYSTEM "A" HYDRAULIC PRESSURE AND THE FLUID QUANTITY IND	ICATION READ ZERO.MAINTENANCE INSPECTION REFEALED THE NR 1 GROUND SPOILER OUTBOARD ACTUATOR ASSEMBLY WAS LEAKING - ACTUA	TOR CASING CRACKED. ACTUATOR REPLACED IAW MM 27-62-101				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003011400186	20030114	00186	CE  	2003	1	14	CA021204005      	1	20021204	G	2820		FUEL LINE       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					WING	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WATER CONTAMINATION IN ALUMINIUM FUEL LINE CAUSE DETERIOTION OF THE LINE BY CORROSION AND RUPTURE BY FREEZING.  TH	IS LINE IS LOCATED BETWEEN WING TIP TANK AND ELECTRIC TRANSFER PUMP LOCATED IN WING.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003011400190	20030114	00190	EA  	2003	1	14	CA021204008      	2	20021119	G	7322	105267	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) LOSS OF CONTROL AT/ON TAKEOFF 200KM. CARBUETOR MALFUNCTION.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003011400192	20030114	00192	EA  	2003	1	14	CA021204010      	2	20021120	G	8530	75772	PUSHROD TUBE    			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					NR 3 CYLINDER	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WITH THE ENGINE COWLING REMOVED TO REPLACE UNSERVICEABLE LANDING LIGHT, OIL WAS NOTED AROUND THE NR 3 CYLINDER. IN	VESTIGATION SHOWED SHROUD WAS BROKEN APPROXIMATELY MIDWAY ALONG THE TUBE. AS THE CRACK WAS A RATHER SHARP BREAK THE PROB	LEM WAS NOT FOUND UNTIL THE TUBE WAS MOVED (TWISTED) BY HAND.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003010600217	20030106	00217	NM  	2003	1	6	CA021206002      	1	20021129	G	3230	841005	PSEU            	ELDEC       	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	INTERNAL FAULT	                	W			    	O	A	 	 	OTHER                   	UNSCHED LANDING         			J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA		 				289					(CAN) ON APPROACH CREW SELECTED GEAR DOWN, RECEIVED						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003011400206	20030114	00206	GL  	2003	1	14	CA021206005      	1	20021203	G	5610	2056501100	CANOPY          			DIAMON	DA20  	DA20A1      	2990000	GL  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) A PREVIOUS CRACK THAT ORIGINATED IMMEDIATELY AFT OF THE PORT CANOPY LOCKING HANDLE HAD BEEN STOP-DRILLED.  IN FLIG	HT A CRACK ORIGINATED FROM THE STOP DRILL LOCATION AND PROPAGATED TO THE UPPER PORTION OF THE CANOPY.AN ELLIPTICAL SEGME	NT APPROX. 12 INCHES X 6 INCHES OF THE UPPER SIDE OF THE CANOPY FELL INTO THE AIRCRAFT.  THE NEW CRACK WAS NOT THE RESUL	T OF A BIRD STRIKE OR TURBULENCE ENCOUNTER.			1	L	7	1 	3O			NT	TA4CH   					 
2003010600218	20030106	00218	NM  	2003	1	6	CA021210001      	1	20021203	G	2761	65449617	ACTUATOR        			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					GROUND SPOILER	LEAKING         	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			73030								(CAN) FLIGHT 178,  CREW REPORTED "A" SYSTEM HYDRAULIC PRESSURE AND QTY WENT TO ZERO ON TAXI INTO YYC. LOW PRESSURE WARNI	NG LIGHT ILLUMINATED FOR APPROXIMATELY 90 SECONDS - CREW SELECTED "A"' PUMPS OFF AND SHUTDOWN BOTH ENGINES. AIRCRAFT TOW	ED TO THE GATE. MAINTENANCE INSPECTION REVEALED THE NR 1 GROUND SPOILER ACTUATOR CASING WAS CRACKED AND LEAKING. MAINTEN	ANCE REPLACED THE ACTUATOR, SYSTEM GROUND CHECKED SERVICEABLE - NO LEAKS AND RETURNED TO SERVICE WITH NO FURTHER INCIDEN	TS TO REPORT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003011400230	20030114	00230	CE  	2003	1	14	CA021210008      	1	20021206	G	2434	646655	GEAR            	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ALTERNATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GEAR TEETH FOUND CORRODED ON ALTERNATOR DRIVE HUB. CORRESPONDING DRIVE RING INSIDE ENGINE CHECKED OK.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2003011400232	20030114	00232	EU  	2003	1	14	CA021210009      	1	20021210	G	2842	NB571261	TRANSMITTER     			BNORM 	BN2   	BN2B21      	7080221	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					FUEL QTY FLOAT	WORN            	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FIBRE FUEL LEVEL FLOAT WORE ON RIB INSIDE FUEL TANK SENDING SMALL PARTICLES THROUGH ENTIRE FUEL SYSTEM.						1	H	7	2 	3O	3	O	 	A17EU   	1E4				 
2003010600219	20030106	00219	CE  	2003	1	6	CA021211001      	1	20021201	G	5541	9763000017	SPAR            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16909								(CAN) THE RUDDER WAS REMOVED DUE TO A DAMAGED SKIN. WHEN THE SKIN WAS REMOVED THE UPPER SPAR WAS FOUND CRACKED AT THE HO	LE FOR A NUT PLATE TO ATTACH TO. THIS NUT PLATE IS USED TO HOLD THE UPPER HINGE TO THE RUDDER. SPAR WAS REPLACED					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003010600221	20030106	00221	CE  	2003	1	6	CA021212002      	1	20021202	G	5753	501600183	FLAP TRACK      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16964								(CAN) THE RT OUTBOARD FLAP, INBOARD FLAP TRACK WAS FOUND CRACKED NOTE YOU CANNOT SEE THIS WHEN THE FLAP IS INSTALLED ON 	THE AIRCRAFT					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003021000083	20030210	00083	NM  	2003	2	10	CA021213001      	1	20021205	G	2422	60B400232	STATIC INVERTER 	            	            	BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D17A     	52049	NE  	 		            		STATIC INVERTER	                	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				067C2191					(CAN) DATE OF REMOVAL NOV 25/02 DATE OF ARRIVAL IN SHOP SNAG DESCRIPTIONWHEN CONDUCTING W/C 12010 ITEM 8 B737 DAILY CHEC	K,STNDBY PWR CHECK AC VOLT METER FULL DEFLECTING RIGHT 130 VOLTS. #1 AND 2 AUTO XFMR C/B POPPED AND CADC AC  & 26VAC C/B	S POPPED, UNABLE TO RESET CADC C/BS.COMPONENT INFORMATION U.N.I. 24-22-0107 (P/N60B40023-2)DESCRIPTION INVERTER, STBY 50	0VA FTN R0G0A0 (S/N 067C-2191) TSV LAST REPAIR2001-06-27 FINDINGSSNAG TEST FINDINGSFAULT CONFIRMED REPAIRED BY IMPROVING	 MISCELLANEOUS SOLDERING ON THE CIRCUITS RELATED TO OUTPUT VOLTAGE LEVELS. FAULT CONFIRMED:AT INPUT VOLTAGE OF 24VDC AND	 INPU T CURRENT 1.5A, NO LOAD APPLIED THE FOLLOWING OBSERVATION WAS MADE: OUTPUT VOLTAGE 155 VACWAITED TWO MINUTESVOLTAG	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003011500003	20030115	00003	NM  	2003	1	15	CA021213005      	1	20021129	G	2422	DH1030246	INVERTER        			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF7       	NE  	ELECTRICAL	FAILED          	W				O				OTHER                   				B	G	H	SMOKE/FUMES/ODORS/SPARKS  	MULTIPLE FAILURE          	ELECT. POWER LOSS-50 PC   	CL	CLIMB          	1			CA											(CAN)  JUST AFTER THE A/C BECAME AIRBORNE, CREW NOTED A SMOKE ODOR IN THE COCKPIT.  PRIMARY INVERTER, DC CIRCUIT BREAKER	 OPENED. THE AUX AND SECONDARY INVERTER DC CIRCUIT BREAKERS OPENED ALMOST IMMEDIATELY THEREAFTER.  BOTH 400HZ BUSSES, AN	D 26 VAC BUSSES BECAME UNPOWERED, WITH THE ASSOCIATED LOSS OF SERVICES. THE PRIMARY INVERTOR FAILED, THE AUX INVERTOR WA	S SELECTED TO THE LT BUSS AT THE TIME.  WHEN THE PRIMARY INVERTOR FAILED, THE SHORT CIRCUIT INTERNAL TO THE INVERTOR, DR	AGGED DOWN THE AUX INVERTOR,  AND IT ALSO WENT OFF LINE.  THE REMAINING SECONDARY INVERTOR WAS UNABLE TO HANDLE THE ELEC	TRICAL LOAD AND IT ALSO DROPPED OFF LINE. THE BUSS TIE CIRCUIT BREAKER, (3.5 AMP, CB 14) DID NOT OPEN. INVERTOR REPLACED	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003011500004	20030115	00004	EU  	2003	1	15	CA021213007      	2	20021113	G	8520	888364	CRANKCASE       			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912S3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CRANKCASE APPEARED TO BE LEAKING OIL ABOVE AND BETWEEN NR 1 AND 3 CYLINDERS. CLEANING AREA AND RUNNING SHOWED MORE	 OIL COMING FROM THIS AREA. ENGINE COOLING SHROUD WAS REMOVED AND REVEALED A 3 INCH CRACK IN CASE. CASE WAS REPLACED WIT	H NEW AND ENGINE RETURNED TO SERVICE.				1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO	 
2003011500008	20030115	00008	SO  	2003	1	15	CA021217002      	1	20021214	G	3297	47936002	WIRE            	PIPER       		PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					DOWNLOCK SWITCH	BROKEN          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON FINAL APPROACH, PILOTS SELECTED GEAR DOWN.  THREE GREEN INDICATION LIGHTS WERE CONFIRMED.  THE GEAR HANDLE WOUL	D NOT COME BACK TO NEUTRAL.  THE CREW CONDUCTED A MISSED APPROACHED AND PROCEEDED TO FOLLOW THE APPROPRIATE CHECKLISTS. 	 THE CREW FLEW OVER THE CONTROL TOWER FOR GEAR DOWN CONFIRMATION. THE AIRCRAFT LANDED SAFELY AND WAS TOWED OFF RUNWAY.  	MAINTENANCE CONFIRMED BROKEN WIRE ON LT MAIN GEAR DOWN SWITCH.THE WIRE WAS REPAIRED, GEAR SWING CARRIED OUT, AND SYSTEM 	TESTED OK. THE AIRCRAFT WAS RELEASED FOR SERVICE.		1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2003011500009	20030115	00009	GL  	2003	1	15	CA021217003      	1	20021215	G	5610	2056000902	SPRING          	DIAMON      		DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  					CANOPY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RT SIDE CANOPY SPRING FAILED AT THE LOWER ATTACH POINT. THIS TYPE OF FAILURE HAS BEEN ROUTINELY OCCURING AROUN	D 800-1000 HOURS OPERATION.					1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2003011500016	20030115	00016	EU  	2003	1	15	CA021218001      	1	20021213	G	3242	21577	BRAKE ASSY      			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					NR 3	FIRE            	W				D				RETURN TO BLOCK         				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA											(CAN) NR 3 WHEEL OBSERVED SMOKING AS AIRCRAFT TAXIED TO GATE. THEN FLAMES WERE OBSERVED COMMING FROM BETWEEN WHEEL HUB S	POKES. CREW LOG REPORT STATED MEDIUM BRAKING AND IDLE REVERSE SELECTED FOR LANDING. DUE INOPERATIVE REVERSER NR 2. AFTER	 AIRCRAFT STOPPED AT GATE A SMALL BRAKE FIRE OCCURED.  A FIRE EXTINGUISHER WAS DEPLOYED UNTIL NO FURTHER FLAMES WERE VIS	IBLE. NR 3 BRAKE ASSY AND NR 3 TIRE ASSY REPLACED AND LANDING GEAR WASHED WITH LOW PRESSURE.			1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2003011500023	20030115	00023	CE  	2003	1	15	CA021219005      	1	20021218	G	5520	115610010125	STRUCTURE       	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18850								(CAN) DURING INSPECTION, THE TRAILING EDGE SPLINE ON THE ELEVATORS WERE FOUND CRACKED AT SEVERAL LOCATIONS, THIS IS THE 	5TH SDR REGARDING THESE SPLINES AND A TOTAL OF 7 SPLINES FOUND CRACKED.  THE ELEVATORS WERE REPLACED AND THE AIRCRAFT RE	TURNED TO SERVICE. WE ARE CURRENTLY CONDUCTING A FLEET INSPECTION.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003013100006	20030131	00006	NE  	2003	1	31	CA030102004      	2	20020406	G	8500		ENGINE          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2B   	 	NE  	HARTZL	HCC4Y	HCC4YR2     	GL  	RIGHT	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L505361A			(CAN) EVENT NR 2 INSPECTION, FOUND RT ENGINE METAL PARTICLES IN OIL FILTER, BETWEEN 20-40 PARTICLES.  ENGINE SERVICED WI	TH 15W50 OIL. AIRCRAFT GROUND RUN AND LEAK CHECKED. ONE HOUR TEST FLIGHT, OIL CHECKED AFTER FLIGHT. AT 523.6 HOURS, CUST	OMER DECIDE NOT TO FLY AIRCRAFT. SENT ENGINE FOR OVERHAUL. AFTER ENGINE OVERHAUL,  FOUND THAT THE ENGINE  CAMSHAFT LOBES	 WERE WEARING OUT CAUSING METAL PARTICLES IN THE ENGINE OIL.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P52GL	 
2003013100007	20030131	00007		2003	1	31	CA030102006      	4	20020604	G	6122	H210800	GOVERNOR        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2B   	 	NE  	HARTZL	HCC4Y	HCC4YR2     	GL  	PROPELLER	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SLIGHT RPM HUNTING ON RT ENGINE AT CLIMB OUT POWER. PROP GOVERNORS WERE SWITCHED TO SEE IF PROBLEM WOULD MOVE. END	ED UP SENDING GOVERNOR OUT FOR REPAIR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P52GL	 
2003013100008	20030131	00008	GL  	2003	1	31	CA030103001      	3	20021210	G	6111	A5270	BEARING         													MCAULY	3AF32C	3AF32C505   	GL  	PROP ASSY	DENTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									941261		(CAN) AFTER DISASSEMBLY OF THE PROPELLER IT WAS NOTED THAT ALL THREE BLADE THRUST BEARINGS WERE BADLY DENTED, BEYOND REU	SE. THE BEARINGS, LUBRICANTS, AND BALLS WERE ALL REPLACED AND THE PROPELLER WAS ASSEMBLED.															5	C	P22EA	 
2003013100012	20030131	00012	EA  	2003	1	31	CA030103009      	2	20021223	G	8530	L2W12397	CYLINDER        			DIAMON	DA40  	DA40        	       	GL  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT IN FOR NORMAL MAINTENANCE. LOW COMPRESSION ON NR 2 CYLINDER. REMOVED CYLINDER. DISCOVERED PITTING ON BARR	EL. SURFACE AND INTAKE VALVE WARPED.CYLINDERS NR 1, 3 AND 4 REMOVED ALSO FOUND PITTING, LYCOMING FACTORY TO SUPPLY 4 NEW	 CYLINDER ASSEMBLIES.				1	L	7	1 	3O	3	O	NT	A47CE   	1E10				 
2003013100013	20030131	00013	GL  	2003	1	31	CA030103010      	1	20021220	G	7810		EXHAUST PIPE    			DIAMON	DA40  	DA40        	       	GL  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT IN FOR NORMAL MAINTENANCE INSPECTION REVEALED EXHAUST PIPES CRACKED AT ALL FOUR EXHAUST FLANGES.						1	L	7	1 	3O	3	O	NT	A47CE   	1E10				 
2003013100014	20030131	00014	CE  	2003	1	31	CA030103011      	1	20021223	G	5751	55240051	SKIN            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TWO OF THE BALANCE WEIGHT ATTACHMENT SCREW HOLE HAD 1/2 INCH CRACKS STARTING FROM UNDER THE SCREW HEADS.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003013100029	20030131	00029	CE  	2003	1	31	CA030103017      	1	20021205	G	5320	50110117	SUPPORT         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17944								(CAN) INSPECTION REVEALED PILOT SEAT SUPPORT STRUCTURES CRACKED, GUSSET ASSY LT OUTBOARD, AND GUSSET ASSY LT INBOARD. IN	BOARD GUSSET CRACKED IN INBOARD FLANGE RADIUS ATTACHMENT TO FLOOR, OUTBOARD GUSSET CRACKED ON TOP SURFACE RUNNING THROUG	H TWO ANCHOR NUTS, AND OUTBOARD RADIUS ON ATTACHMENT TO FLOOR, ILLUSTRATION REFERENCE 53-40-00, FIGURE 01.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003011500068	20030115	00068	EA  	2003	1	15	CA030103019      	2	20021206	G	8520	STD2209	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					CRANKSHAFT GEAR	SHEARED         	W				A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) PILOT WAS IN CRUISE FLIGHT WHEN HE FELT A SURGE IN POWER ON THE LT ENGINE AND SUDDEN LOSS OF RPM, ATTEMPTED TO SWI	TCH TANKS AND NOTHING HAPPENED, FEATHERED PROP AND SHUT ENGINE DOWN. PILOT FLEW TO AIRPORT AND LANDED SAFELY ON RT ENGIN	E. AN ENGINE RESTART WAS ATTEMPTED ON THE GROUND AND NOTHING HAPPENED. THE PROP WAS TURNED BY HAND AND NO COMPRESSION WA	S FELT. THE REAR ACCESSORY SECTION WAS REMOVED AND FOUND CRANKSHAFT GEAR BOLT SHEARED AND GEAR TEETH BROKEN OFF. TOTAL T	IME ON ENGINE 1100 HOURS, 400 HOURS SINCE BULK DISASSEMBLY AFTER PROP STIKE, 40 HOURS SINCE AD 02-20-51AND SB 554 AND 47	5B WAS C/W.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003013100041	20030131	00041	NM  	2003	1	31	CA030103022      	1	20021126	G	2422	60B400232	STATIC INVERTER 			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					AC SYS	MALFUNCTIONED   	W				K				NONE                    				S			AFFECT SYSTEMS            			IN	INSP/MAINT     	1			CA											(CAN) WHEN CONDUCTING AN EMERGENCY POWER CHECK THE AC VOLT METER WENT FULL DEFLECTION TO 130 VOLTS.  NR 1 AND 2 AUTO TRA	NFORMER C/B POPPED AND CADC AC AND 26 VAC C/B'S POPPED. SHOP REPORT CONFIRMED THE FAULT THAT THE INVERTER WAS PUTTING OU	T 155 VAC.  THIS WAS BELIEVED TO BE DUE TO POOR SOLDER CONNECTIONS WITHIN THE INTERNAL CIRCUIT BOARDS.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003013100099	20030131	00099	CE  	2003	1	31	CA030106018      	1	20020720	G	2810	04265126	STRAP           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RT AFT FUEL TANK	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAK. RT WING. UPON REMOVAL OF THE FUEL TANK WING PANEL, DISCOVERED THE AFT FUEL TANK STRAP TO BE BROKEN. DUE	 TO THE BROKEN STRAP THE SCREEN ASSEMBLY HAD CHAFED THROUGH THE TOP OF THE  FUEL TANK CAUSING A FUEL LEAK.  FUEL TANK RE	PAIRED AT AN APPROVED REPAIR SHOP. NEW STRAP AND SCREEN ASSEMBLY INSTALLED CARRIED OUT FUEL TANK INSTALLATION AS PER CES	SNA MAINTENANCE MANUAL AND ALL SYSTEM CHECKED SERVICEABLE AND AIRCRAFT WAS RETURNED TO SERVICE.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003013100107	20030131	00107	SO  	2003	1	31	CA030107010      	1	20020120	G	3220	6705403	TRUNNION        			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION, NOSE GEAR TRUNION FOUND CRACKED AROUND UPPER RT ATTACHMENT.						1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003013100109	20030131	00109	SO  	2003	1	31	CA030107011      	1	20020801	G	5520	1279004	STRUCTURE       			PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O320  	O320A2B     	41508	EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT STABILIZER REAR TUBE WAS FOUND CRACKED INBOARD OF THE OUTBOARD ELEVATOR HINGE.						1	H	7	1 	3O	3	O	 	1A2     	E274				 
2003013100110	20030131	00110	CE  	2003	1	31	CA030107012      	1	20021206	G	5511	04320016	RIB             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13957								(CAN) RT HORIZONTAL STAB RIB WAS FOUND CRACKED.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003013100115	20030131	00115	EA  	2003	1	31	CA030107013      	2	20021220	G	8520		CRANKCASE       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					RT ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WHILE CONDUCTING A DAILY INSPECTION, IT WAS NOTED THAT THE RT ENGINE NACELLE WAS FULL OF OIL. WITH THE COWLING REM	OVED AN INSPECTION OF THE ENGINE WAS CARRIED OUT. A CRACK WAS FOUND ON THE RIGHT SIDE OF THE CRANKCASE AT THE FORWARD CY	LINDER, LOWER FORWARD STUD (FORWARD OF CYLINDER NR 2).				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003012100253	20030121	00253	NE  	2003	1	21	CA030107017      	2	20021221	G	7250		BLADE           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NR 1 TURBINE	DAMAGED         	W				A				UNSCHED LANDING         				D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA			13140								(CAN) ON ROUTE TO YVR FROM YYZ AT 130 NM FROM YYC HEARD LOUD BANG, FOLLOWED BY NR 1 ENGINE EPR DROP TO ZERO N1-N2 SPEED 	DECREASING.  ENGINE RETARDED TO IDLE.  PARAMETERS WITHIN LIMITS. DIVERTED TO YYC. PRELIMINARY INSPECTION REVEALS DAMAGED	 TURBINE BLADES. ENGINE WILL BE SENT TO SHOP FOR INVESTIGATION AND REPAIR.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2003013100136	20030131	00136	SO  	2003	1	31	CA030107018      	1	20021224	G	2140	3716742	LINE            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  					HEATER FUEL	CORRODED        	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) DURING A GROUND RUN FOR CALIBRATION OF AN UNRELATED SYSTEM THE ENGINEER NOTICED A STRONG FUEL SMELL IN THE CABIN. 	THE SOURCE WAS FOUND TO BE A CORRODED HEATER FUEL LINE AT APPROXIMATELY FS 165. THE CARPET AHEAD OF PASSENGER SEAT NR 6 	WAS SOAKED WITH FUEL.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2003013100143	20030131	00143	GL  	2003	1	31	CA030108001      	2	20021212	G	7321		FUEL CONTROL    			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	MALFUNCTIONED   	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) NORMAL TAKEOFF. AFTER REDUCING COLLECTIVE TO 70 PERCENT, TURBINE AND ROTOR RPM AT 105 PERCENT. BEEPED DOWN WITH NO	 RESPONSE,  COLLECTIVE WAS LOWERED TO SLOW DOWN AND ROTOR RPM WAS NOW 115-120 PERCENT. PILOT ROLLED BACK THROTTLE TO DIS	ENGAGE GOVERNOR,  RPM REMAINED AT 115-120 PERCENT.  THROTTLE WAS NOW AT FLIGHT IDLE WITH RPM AT 115-120 PERCENT.  REDUCE	D AIRSPEED TO 60 MPH AND DESCENDED. AT APPROX. 300 FT, ENGINE SLOWED DOWN, FULL THROTTLE WAS APPLIED AND 100 PERCENT ROT	OR RPM WAS REACHED & STABLE.  ALL TEMPS AND RPMS WERE NORMAL, FLT WAS CONTINUED FOR 8 MINUTES BACK TO CAMP.  ROTOR RPM W	AS BETWEEN 115-120 PERCENT FOR 20-30 SECONDS. AFTER INSPECTING OIL LEVELS AND CHIP DETECTORS, CONTINUED FLT.	1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2003013100151	20030131	00151	SW  	2003	1	31	CA030108004      	1	20021203	G	2810	43122	ADAPTER         			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					FUEL CAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION CORROSION WAS FOUND IN THE AREA OF THE ADAPTER FOR THE FUEL FILLER CAP WHERE THE O-RING S	EALS AGAINST WATER ENTERING THE FUEL TANK.					1	L	7	1 	3O	3	O	 	2A3     	E286				 
2003013100153	20030131	00153	NE  	2003	1	31	CA030108006      	2	20021206	G	7314	AN4101	PUMP            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67      	52043	NE  					ENG DRIVEN FUEL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A FUEL LEAK WAS DETECTED DURING ANNUAL INSPECTION IN THE PLENUM CHAMBER AREA. IT WAS TRACED TO THE ENGINE DRIVEN F	UEL PUMP.					1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2006061200355	20060612	00355	CE  	2006	6	12	CA030108008      	1	20021211	G	3110	S18802	RHEOSTAT        			CESSNA	172   	172I        	2072426	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	INSTRUMENT PANEL	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											THIS 'SDR' IS BEING RAISED BECAUSE OF AD 93-24-15 AND SEB92-33R1 REGARDING INSTRUCTIONS OF RHEOSTAT P/N RD-0015H-1600.  	WHEN AN AD IS ISSUED, AS THIS ONE WAS, REGARDING AN IMPROVED PART THE REGULATORY BODY SHOULD ENSURE PARTS CATALOGS OR MA	INTENANCE MANUALS ARE CHANGED TO REFLECT THESE CHANGES.  SHOULD THIS PART BE REQUIRED IN THE FUTURE, IT IS POSSIBLE FOR 	THE PART LISTED IN THE PARTS CATALOG BE ORDERED AND INSTRUCTED, WHICH WOULD INVALID THE AD ALAREADY ENTERED IN THE TECH 	LOGS AS BEING CARRIED OUT, THUS REINTRODUCING THE ORIGINAL PROBLEM BACK INTO THE AIRCRAFT.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2006061200356	20060612	00356	EU  	2006	6	12	CA030108012      	1	20021227	G	3010	9598901014	TIMER           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	DE-ICE SYS	ERRATIC         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				8    							THIS DE-ICE TIMER WAS RECEIVED WITH AN "INSPECTED" TAG.  AFTER INSTALLATION, THE SYSTEM FAILED AFTER 7.7HRS.  INVESTIGAT	ION REVEALED THAT THE TIMER WOULD "CHATTER" AND THE BOOT INFLATION SEQUENCE WOULD BECOME ERRATIC.  THE TIMER WAS REPLACE	D AND  THE AIRCRAFT RETURNED TO SERVICE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2006061900244	20060619	00244	WP  	2006	6	19	CA030108017      	1	20021214	G	6420		TAIL ROTOR      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  						DEPARTED        	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AC WAS AT A HEIGHT OF 6-10 FT ABOVE GROUND TRAVELING AT 20MPH IN CROSSWIND.  AT TIME OF PROBLEM, FAIR AMOUNT OF LT	 PEDAL WAS BEING USED.  AC TRAVELED APPROX 30FT CROSSWIND WHEN LOUD BANG WAS HEARD BY PILOT FOLLOWED BY T/R ASSY FLYING 	PASSED PILOTS CHIN BUBBLE.  PILOT ROLLED THROTTLE OFF TO STOP ROTATION OF AC, LANDED AC ON A NEARLY LEVEL OR FAIRLY LEVE	L SPOT.  AC HAD COMPLETED ONE HALF OF A REVOLUTION BY TIME PILOT GOT IT ON GROUND.  NO FURTHER DAMAGE TO AC.  WIND:  SOU	TH 20KMH.  ELEVATION:  8000FT.  TOTAL TIME:  13000HRS.  TT ON TYPE:  6000HRS. PILOT OBSERVATION:  IT APPEARS TO ME THAT 	THE T/R GEARBOX BLEW APART.  AT NO TIME DID THE T/R COME IN CONTACT WITH THE GROUND OR SNOW. (TC NR 20030108017)	1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2003020300003	20030203	00003	SW  	2003	2	3	CA030110003      	1	20020718	G	3230	52002503	PIVOT ASSY      			MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540AF1A  	41532	EA  	MCAULY	3D32C	B3D32C417   	GL  	LT MLG	SEIZED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) THE LT MLG HAD FAILED TO EXTEND.  UPON EXAMINATION IT WAS FOUND THAT THE HINGE PIVOT POINT BETWEEN THE SHOCK STRUT	 AND GEAR LEG SPINDLE ASSEMBLY WAS SEIZED DUE TO A LACK OF LUBRICATION.  THIS CAUSED THE MLG LEG TO RETRACT IMPROPERLY A	ND JAMMED IN THE WHEEL WELL.  EXAMINATION ALSO REVEALED A LACK OF A GREASE FITTINGS FOR THE BEARING SURFACE.  LUBRICATIO	N OF THIS PIVOT POINT WAS EFFECTIVELY IMPOSSIBLE. THE SEIZURE RESULTED IN A GEAR UP LANDING.			1	L	7	1 	3O	3	O	RT	2A3     	E14EA	5	C	P58GL	 
2003020300015	20030203	00015	EU  	2003	2	3	CA030112009      	1	20021227	G	7931	11346AA	TRANSMITTER     			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					RT ENGINE OIL	FALSE INDICATION	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF ROLE THE PILOT IN COMMAND NOTICED OIL PRESSURE FLUCTUATION OF THE RT ENGINE. THE PILOT IN COMMAND 	INITIATED REJECTED TAKE-OFF. AT THIS TIME, THE FLIGHT CREW ADVISED ATC AND RETURNED TO THE MAINTENANCE FACILITY. OUR CON	TRACTED AMO HAS DETERMINED THAT THE OIL PRESSURE TRANSMITTER IDENTIFIED AS AT FAULT, THEREFORE GIVING A FALSE OIL PRESSU	RE INDICATION TO THE FLIGHT CREW. THE OIL PRES SURE TRANSMITTER WAS REPLACED WITH A SERVICEABLE UNIT. THE AIRCRAFT WAS G	ROUND RUN SATISFACTORILY AND WAS RETURNED INTO SERVICE TO RESUME OPERATIONS.		2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2003020300019	20030203	00019	EA  	2003	2	3	CA030113003      	2	20021128	G	7530		LINE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					RT ENG P3 SUPPLY	BLOCKED         	W				A				UNSCHED LANDING         				R	A	J	PARTIAL RPM/PWR LOSS      	FLAME/FIRE                	WARNING INDICATION        	CL	CLIMB          	1			CA								PCE52432			(CAN) AFTER TAKEOFF IN THE CLIMB THROUGH 15,000 FT THE RT ENGINE EXPERIENCED THREE MAJOR SURGES WITH FLUCTUATIONS OF TOR	QUE, NG, ITT, AND FUEL FLOW ALONG WITH FLAMES SHOOTING FROM THE ENGINE EXHAUST.  AFTER EXTENSIVE TROUBLESHOOTING THE ENG	INE WAS DEEMED TO BE INTERNALLY AT FAULT. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED BACK TO SERVICE. THE ENGINE 	REMOVED WAS FOUND TO HAVE A PARTIAL BLOCKAGE OF THE P3 SUPPLY TUBE TO THE BLEED OFF VALVE. THE BLOCKAGE WAS CLEARED AND 	THE ENGINE RETESTED SATISFACTORY AT THE REPAIR FACILITY.		1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2006061200364	20060612	00364	WP  	2006	6	12	CA030113012      	1	20021214	G	2810		FUEL TANK       			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  						CONTAMINATED    	W				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											TANK 2R INBD, QTY HIGHER THAN NORMAL WITH QTY SWITCH LIGHT LATCHED IN.  FUEL QTY GAUGES OK.  INBD QTY READS 4000 LBS, WI	TH TOTAL BELOW 7000LBS.  PER FAULT ISOLATION AMM 28-27-00 P 107, REPLACED BOOST PUMP CHECK VALVES PER AMM 28-24-03 (NIL 	FIX).  FUEL WAS STILL TRANSFERRING FROM OUTER INTO INNER TANK (GRAVITY FLOW).  FAULT FOUND TO BE A PAPER TOWEL (FACE WIP	E) LOGGED IN THE FWD FLAPPER CHECK VALVE OF THE TANK 2R INNER TANK/BOOST PUMP BOX.  PAPER TOWEL REMOVED AND TANK 2R TRAN	SFER CHECKED SERVICEABLE PER AMM 28-27-00.		2	L	7	3 	4F	4	F		A23WE   	E12EU				 
2003020300030	20030203	00030	CE  	2003	2	3	CA030114005      	1	20021231	G	2121	115384007	BLOWER          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					COCKPIT	FAILED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT WAS TAXING FROM TERMINAL TO RUNWAY WHEN SMOKE STARTED FILLING COCKPIT.  ELECTRICAL COMPONENTS WERE TURNED	 OFF AND AIRCRAFT RETURNED TO TERMINAL.  MAINTENANCE WAS CONTACTED AND FORWARD VENT BLOWER WAS REPLACED. GROUND CHECKED 	SERVICEABLE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003021200056	20030212	00056	CE  	2003	2	12	CA030115002      	1	20021205	G	3710	1U128006	PUMP            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	VACUUM SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE SCHEDULED OPERATION NR 2 ENGINE OF THE AIRCRAFT.  A CRACK WAS NOTED ON THE ENGINE ATTACH BRACKET OF THE	 INSTALLED VACUUM PUMP. UPON REMOVAL OF THE PUMP IT WAS DISCOVERED THAT THE ENTIRE ATTACH BRACKET WAS COMPLETELY SEPARAT	ED FROM THE PUMP. FLIGHT CREW HAD NOT NOTED ANY FAILURE AND REPORTED THAT INSTRUMENT AIR PRESSURE WAS NORMAL WHILE IN FL	IGHT. THE DAMAGED PUMP WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT.			1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2006061200366	20060612	00366	GL  	2006	6	12	CA030115007      	2	20021223	G	7310	AN21220D	FITTING         			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  	HOSE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											TWO HOSE ASSEMBLIES (390A20D4.8 AND 390A20D12.5) FROM A FUEL SUPPLY "Y" MANIFOLD WAS REMOVED AND ROUTED TO OUR INTERNAL 	OVERHAUL SHOP FOR REPLACEMENT OF THE HOSES.  UPON DISASSEMBLY, IT WAS DISCOVERED THAT THREE OF THE FOUR FITTINGS (SOCKET	S) (AN212-20D) WERE CORRODED AND CRACKED LONGITUDINALLY.  ONE WAS CRACKED ON BOTH SIDES OF THE FITTING (ACTUALLY SPLIT I	N TWO), THE OTHER TWO WERE CRACKED ON ONE SIDE ONLY WHERE THE FIRE SLEEVES COVER THE FITTINGS.  IT WOULD APPEAR THAT THE	 FIRE SLEEVES TRAPPED MOISTURE AND THUS CORRODED THE FITTINGS.  UNFORTUNATELY, THERE ARE NO PHOTOS AVAILABLE AS THE FITT	INGS WERE DISCARDED ACCIDENTALLY.  PLEASE REFER TO THE PICTURES FROM SDR 20030115004 FOR IDENTICAL PARTS AND CONSISTENT 	2	L	7	2 	4R	4	T		6A6     	E282	6	C	P906	 
2006061200368	20060612	00368	EU  	2006	6	12	CA030115009      	1	20021209	G	5240	A5247007020200	PANEL           			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  						MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											UPON A/C ARRIVAL FROM FLIGHT, FOUND ON WALK AROUND 3 MISSING PANELS (PANELS 134ER; P/N A5247007020600, 134CR; P/N A52470	07020200, 134DR; P/N A5247007020400).  HOLDING BRACKETS THOSE PANELS WERE ALSO FOUND TO BE DAMAGED.  NEW HOLDING BRACKET	S WERE FABRICATED IAW SRM 51-72-10 AND PANELS INSTALLED IAW AMM 53-13-00.  THESE PANELS ARE OFTEN HIT BY CARGO LOADING E	QUIPMENT OR STEPPED ON BY THE CARGO HANDLERS.			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2003020300036	20030203	00036	EA  	2003	2	3	CA030116004      	2	20021224	G	8520	5L13792	SEAL            			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					CRANKSHAFT	BLOWN           	W				A				UNSCHED LANDING         				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) FRONT CRANKSHAFT SEAL BLOWN OUT DUE TO FROZEN ENGINE VENT LINE CANISTER. VENT SYSTEM PURGED AND CLEANED CRANKSHAFT	 SEAL RESEATED. ENGINE RUN-UP AND OIL FILTERS SERVICEABLE (NO METAL).					1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003021300005	20030213	00005	EU  	2003	2	13	CA030121005      	2	20021113	G	8530	854116	EXHAUST VALVE   	ROTAX       		DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912S3  	 	EU  					NR 1 CYLINDER	BROKEN          	W				A				UNSCHED LANDING         				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	CL	CLIMB          	1			CA											(CAN) EXHAUST VALVE IN NR 1 CYLINDER BROKEN AT AREA BETWEEN STEM AND HEAD OF VALVE. VALVE DROPPED INTO COMBUSTION AREA A	ND CAUSED PISTON DAMAGE AND EVENTUALLY ENGINE STOPPAGE.  VISIBLE WEAR ON VALVE TRAIN COMPONENTS CONSISTENT WITH IMPROPER	 PURGING OF LIFTERS AS ADDRESSED BY SB-912-036.  NO ENTRY IN ENGINE LOG BOOK TO SHOW COMPLIANCE TO SB-912-036 OR AD-113.	 AD WAS RELEASED 2 MONTHS BEFORE OCCURRANCE DATE.			1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2003021000090	20030210	00090	GL  	2003	2	10	CA030122004      	3	20021204	G	6114		PROPELLER       	MCAULY      	3AF32C504C  	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	                	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA		 				941261					(CAN) NUMBER 1 BLADE WAS LEAKING OIL FROM THE HUB. PROP WAS REMOVED AND SENT TO O/H SHOP. SEAL IN HUB WAS FOUND TO BE LE	AKING. SEAL REPLACED -PROP WAS REINSTALLED.					1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2006061200421	20060612	00421	CE  	2006	6	12	CA030122005      	1	20021216	G	7931	264600053	INDICATOR       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	OIL PRESSURE	READS HIGH      	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA			1095 								AT HIGH RPM, THE OIL PRESSURE GAUGE WAS READING PAST THE RED LINE.  ENGINE OIL PRESSURE WAS CHECKED USING EXTERNAL GAUGE	 FOUND TO BE WITHIN MANUFACTURES LIMITS.  OIL PRESSURE GAUGE WAS REPLACED.  THE OLD GAUGE WAS INSPECTED AND NOTHING COUL	D BE SEEN CAUSING THE PROBLEM.  OIL PRESSURE LINE WAS CLEANED OUT AND NOTHING WAS FOUND IN IT OTHER THAN OIL.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003021300028	20030213	00028	EA  	2003	2	13	CA030128003      	2	20021218	G	7322	105267	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) ROUGH RUNNING ENGINE WAS NOTICED IN FLIGHT. PILOT THOUGHT IT WAS CARB ICE TRIED TO CLEAR IT OUT BY USING CARB HEAT	. THIS DID NOT WORK, SO HE CAME BACK TO THE HANGER. AIRCRAFT WAS BROUGHT BACK INTO THE HANGER, ALL THE PLUGS WERE CLEANE	D. THEY WERE FULL OF LEAD, THE MAGNETO TIMING WAS CHECKED BUT IT WAS OKAY. AIRCRAFT WAS TAKEN OUTSIDE AND RAN UP, ENGINE	 WAS STILL RUNNING ROUGH SO IT WAS BROUGHT BACKIN AGAIN. ANOTHER CARB WAS INSTALLED AND AIRCRAFT WAS RUN UP AGAIN THIS T	IME THE ENGINE RAN SMOOTH. CARB WAS SENT OUT FOR REPAIRS NOTHING OBVIOUS WAS FOUND AT THE ENGINE SHOP. ENGINE SHOP REPLA	CED THROTTLE SHAFT BUSHINGS. OTHER THAN THAT IT WAS IN GOOD SHAPE.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003032600063	20030326	00063		2003	3	26	CA030204012      	4	20021128	G	2397	5136738	WIRE            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	RADIO MASTER	OVERHEATED      	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) LUG IMPROPERLY CRIMPED TO WIRE PA-6 AT RADIO MASTER SWITCH CAUSING AN OVERHEAT SITUATION WITH EVENTUAL SEPARATION 	OF WIRE FROM LUG. WIRE WAS ORIGINAL FROM CESSNA FACTORY INSTALLATION.					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
2003021300051	20030213	00051	SO  	2003	2	13	CA030205008      	1	20020116	G	8120		HOUSING         	GARRTT      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					TURBOCHARGER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						KHR0371					(CAN) DURING A DETAILED ENGINE INSPECTION, A CRACKED TURBOCHARGER HOUSING WAS DISCOVERED. POSSIBLE TURBOCHARGER BEARING 	WEAR ON INSPECTION WAS INVESTIGATED AND AFTER REMOVAL OF THE TURBO HEATBLANKET, A CRACK WAS FOUND IN THE TURBOCHARGER HO	USING INCLUDING HEAT DAMAGE TO THE BLANKET. AN OVERHAULED TURBOCHARGER AND NEW HEAT BLANKET WAS INSTALLED.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003041400099	20030414	00099	EU  	2003	4	14	CA030228003      	1	20021212	G	3222	5322012200	GUIDE           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) LOUD UNUSUAL SOUND FROM NOSE GEAR WHEN SELECTED DOWN. - FOUND NOSE GEAR OLEO NOT EXTENDING COMPLETELY.- NOSE LANDI	NG GEAR FORK RUBBED ON NOSE GEAR DOOR ACTUATING ROD.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003041400102	20030414	00102	CE  	2003	4	14	CA030228008      	1	20021015	G	5343	07900065	BRACKET         			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  					LT MLG LEG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING INSPECTION OUTER GEAR LEG BRACKET FOR LT MAIN GEAR WAS FOUND SEVERELY CORRODED. CORROSION HAD CAUSED SEVER	E EXFOLIATION. SUSPECT CORROSION INDUCED FROM ENGINE EXHAUST ENTERING AREA. OUTSIDE COVER WAS NOT SEALED WHICH ALLOWED E	XHAUST TO ENTER AND CAUSE CORROSION. PART REPLACED WITH NEW.				1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2003041400103	20030414	00103	CE  	2003	4	14	CA030228009      	1	20021015	G	5751	05238161	HINGE           			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  					AILERON	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION AILERONS WERE ACTUATED FROM THE CONTROL COLUMN AND AILERON MOVEMENT WAS FOUND TO BE SPRINGY. VIS	UAL INSPECTION OF BOTH AILERONS CONFIRMED HINGE PINS WERE SEIZED AND NOT ALLOWING THE HINGE TO MOVE. NEW HINGES INSTALLE	D.				1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2003041400106	20030414	00106	NE  	2003	4	14	CA030228014      	2	20021203	G	8550	3034292	OIL FILTER      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	CLOGGED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) OIL PRESSURE FLUCTUATION IN FLIGHT.  FOUND OIL FILTER PLUGGED WITH CARBON.  OIL FILTER REPLACED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003041400120	20030414	00120	CE  	2003	4	14	CA030306001      	1	20021215	G	5610	10138402522	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) IN FLIGHT THE WINDOW SUDDENLY SHATTERED WITH A LOUD BANG.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003040900023	20030409	00023	EU  	2003	4	9	CA030312010      	1	20020813	G	2750		CONTROL QUADRANT			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FLAP SYSTEM	FAILED          	W				J				DUMP FUEL               				A			FLAME/FIRE                			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THE PILOT SELECTED FLAPS UP. A FLAP WARNING LIGHT ILLUMINATED AND THE FLAPS DID NOT MOVE. (FLAPS REM	AINED AT 15 DEGREES). THE PILOT RETURNED TO LAND AT THE AIRPORT WITHOUT INCIDENT. A FLAP RESET WAS CARRIED OUT ON THE GR	OUND SERVICEABLE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003041400040	20030414	00040	CE  	2003	4	14	CA030312013      	1	20020110	G	5753	58250057	SKIN            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	TE FLAPS	DELAMINATED     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE LT INBOARD FLAP WAS DISCOVERED PARTIALLY SEPARATED  ON THE TOP SURFACE OF THE COMPOSITE STRUCTURE WHERE A NON 	CONFORMANT REPAIR (AS INDICATED IN THE APPLICABLE MANUAL) WAS CARRIED OUT. THIS REPAIR SEEMS TO HAVE BEEN DONE WITHOUT A	NY DOCUMENTATION.THE RT INBOARD FLAP IS STARTING TO DELAMINATE. IT HAS NO TRACES OF WORK CARRIED OUT ON THE FLAP SURFACE	. THE DELAMINATED SURFACE IS IN THE SAME LOCATION AS THE LT FLAP.			1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2003050700116	20030507	00116	EA  	2003	5	7	CA030417006      	1	20020625	G	5741		BUSHING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					WING ATTAHCMENT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MIGRATING BUSHINGS ON WING ATTACHMENT FITTINGS.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003060900183	20030609	00183	EA  	2003	6	9	CA030502002      	2	20020816	G	7414	4371	MAGNETO         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ROUGH RUNNING ENGINE DUE TO LT MAGNETO MALFUNCTION. INTERNAL DEFECTS, THEREFORE EXACT MALFUNCTION UNKNOWN.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003050600255	20030506	00255	EA  	2003	5	6	CA030505001      	1	20020529	G	5610	NP1393221	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) LT SIDE WINDOW SHATTERED IN FLIGHT.  AIRCRAFT LANDED IN CINCINNATI WITHOUT FURTHER INCIDENT.WINDOW REPLACED, AIRCR	AFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082100084	20030821	00084	SO  	2003	8	21	CA030506003      	2	20020623	G	8550	646277	LIFTER          								CONT  	O470  	IO470L      	17026	SO  					ENGINE	WRONG PART      	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA								454939CS			(CAN) A/C EXPERIENCED ENG OIL PRESS PROBLEM. TROUBLESHOT & CONSULTED WITH O/H SHOP, UNABLE TO RECTIFY OIL PRESSURE PROBL	EM.  ENGINE REMOVED/OVERHAULED & INSTALLED. ENG HAD OVER MAX OIL PRESSURE (100 PSI) AT HIGHER RPM SETTING, AT IDLE, OIL 	PRESSURE WOULD DROP  BELOW NORMAL OPERATING RANGE  AIRCRAFT WAS GROUNDED.   AFFECTED ENGINES SENT TO ANOTHER OVERHAUL FA	CILITY FOR ANALYSIS AND REPAIR.ENGINE DISASSEMBLED, DISCOVERED 12 IMPROPER VALVE LIFTERS 646277 HAD BEEN INSTALLED. O/H 	SHOP CONFIRMED THIS WOULD CAUSE POOR OIL PRESSURE. ENGINE REPAIRED AND TESTED AFTER RE-ASSEMBLY, OIL PRESSURE READINGS W	ERE EXCELLENT.						3	O			3E1				 
2003061700075	20030617	00075	EA  	2003	6	17	CA030526006      	2	20020422	G	7414	4381	MAGNETO         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING RUN UP IGNITION SYSTEM CHECK REVEALED POWER LOST ON RT MAGNETO. UNIT REPLACED WITH SERVICEABLE MAGNETO AND 	GROUND RUN OK. UNIT SENT BACK FOR CREDIT THUS INTERNAL PROBLEM IS UNKNOWN AT THIS TIME.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003070300053	20030703	00053	NE  	2003	7	3	CA030526009      	2	20020603	G	7414	SKL32138AN	PLUG            		C2N2181A    	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	MAGNETO	SHORTED         	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA											(CAN) THE ENGINE QUITE IN CRUISE AND THE PILOT MADE A DEAD STICK LANDING ONTO THE WATER. UPON INSPECTION FOUND THE SAFET	Y GROUNDING TAB IN THE FIREWALL PLUG APPEARED TO BE BROKEN OFF AND FELL ACROSS THECONTACT PINS, SHORTING OUT BOTH MAGS. 	 NOT SURE BECAUSE THE PLUG WOULD HAVE TO BE DESTROYED TO GET IT APART.				1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P28EA	 
2003070300023	20030703	00023	EU  	2003	7	3	CA030602003      	1	20020529	G	1430	LN93556X32	BOLT            			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					HYD PACK	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLYING WITH FLEET CAMPAIGN NOTICE 351-73-20-12 IT WAS FOUND THAT THE BOLT CONNECTING THE TWO NR 2 GOVERNO	R CABLES TO THE HYDRAULIC PACK WAS TOO SHORT ONLY ONE THREAD WAS SHOWING THROUGH THE ANCHOR NUT. A NEW BOLT WAS INSTALLE	D AND THE AIRCRAFT WAS RETURNED TO SERVICE.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003070300001	20030703	00001	EU  	2003	7	3	CA030605002      	2	20021111	G	8530		EXHAUST VALVE   			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					NR 1 CYLINDER	DESTROYED       	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) EXHAUST VALVE ON NR 1 CYLINDER FAILED ON TAKEOFF CAUSING IT TO FALL INTO THE COMBUSTION CHAMBER WHERE IT CAME INTO	 CONTACT WITH PISTON AND INTAKE VALVE CAUSING EXTENSIVE DAMAGE TO CYLINDER WALL AND DESTROYING PISTON. ENGINE SEIZED CAU	SING CONNECTING ROD TO TWIST AND CRACK. CYLINDER BASE FLANGE AT TOP OF ENGINE WAS ALSO DAMAGED LEAVING A HOLE IN ENGINE 	CASE JUST BEHIND NR 1 CYLINDER.			1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2003070300046	20030703	00046	SW  	2003	7	3	CA030610003      	1	20020301	G	6520	209011710005	TUBE            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					T/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE TUBE ASSEMBLY WAS REMOVED DURING A NORMAL INSPECTION AND FOUND TO HAVE EXCESSIVE WEAR ON THE SEAL JOURNAL. THE	 TUBE WAS SENT TO A REPAIR STATION TO HAVE THE JOURNAL REPLATED IAW  TB 205-91-89.   THE TUBE WAS INSPECTED BY MAGNETIC 	PARTICAL INSPECTION PRIOR TO REPLATING. A CRACK WAS DISCOVERED AND THE TUBE WAS RETURNED UNSERVICEABLE.  THE TUBE ASSEMB	LY IS MADE IN 3 SECTIONS WELDED TOGETHER. THE CENTER SECTION WAS CRACKED LONGITUDINALLY FROM WELD TO WELD APPROXIMATELY 	19 INCHES.  THE CRACK IS VERY STRAIGHT AND DEEP SUGGESTING A MANUFACTURING DEFECT.		1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2003082100211	20030821	00211	SW  	2003	8	21	CA030722001      	1	20020618	G	2780	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TE FLAP	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE FOUND FRAYED AT THE PULLEY PN 12395.THE AREA TENDS TO BE A HIGH WEAR BECAUSE OF THE SIZE OF PULLEY AND IS MO	NITORED CLOSELY AT ALL INSPECTIONS. FAILURES HAVE OCCURED IN THE PAST WITH THIS COMPANY.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2003082200007	20030822	00007	NE  	2003	8	22	CA030726001      	2	20021007	G	8530		STUD            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					CYLINDER	BROKEN          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CYLINDER FOUND LOOSE BECAUSE OF THE 6 STUDS PARTIALLY BROKEN. 6 STUDS REPAIRED AND NEW GASKET INSTALLED.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003082200008	20030822	00008	CE  	2003	8	22	CA030726003      	1	20020618	G	7603	C2995050101	THROTTLE        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  					ENGINE CONTROL	MALFUNCTIONED   	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) NEW THROTTLE INSTALLED DUE TO MALFUNCTION.						1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2003082200009	20030822	00009	CE  	2003	8	22	CA030726005      	1	20021009	G	2434	DOFF10300J	ALTERNATOR      			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  					ENGINE	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) LOSS OF ALTERNATOR POWER. ALTERNATOR OVERHAULED.						1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2003090900048	20030909	00048	SW  	2003	9	9	CA030825004      	1	20020715	G	2720	315371	PEDAL           	BLANCA      		BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TOE BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A/C ARRIVED FOR SUMMER OPERATION.  THE AME TOOK A QUICK LOOK THROUGH THE COCKPIT AND NOTICED THE RIGHT PEDAL SYSTE	M LOOSE.  ON FURTHER INSPECTION, HE NOTICED THE FORWARD RIGHT PEDAL BENT AND CRACKED ON THE RIGHT MOUNT SUPPORT.					1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012600107	20040126	00107	EA  	2004	1	26	CA031103007      	2	20021128	G	8530		ENGINE          			MOONEY	M20   	M20M        	5870222	SW  	LYC   	0540  	TIO540AF1B  	41532	EA  	MCAULY	3D32C	B3D32C417   	GL  		MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND METAL CONTAMINATION ON OIL FILTER ELEMENT.  MFG LAB REPORTS METAL AREA MS 6274 STEEL LIKELY FROM CAMSHAFT AN	D AMS 4280 ALUMINUM FROM CRANKCASE.  ENGINE WAS REMOVED AS PRECAUTIONARY INVESTIGATION DUE TO SIMILAR METAL CONTAMINATIO	N AND REPAIR ABOUT 100 HOURS AGO.  FURTHER DETAIL WILL BE SUBMITTED AFTER INVESTIGATION BY MFG.				1	L	7	1 	3O	3	O	RT	2A3     	E14EA	5	C	P58GL	 
2003112600086	20031126	00086	SW  	2003	11	26	CA031106002      	1	20021001	G	5302		SKIN            	BELL        		BELL  	206   	206B3       	1181506	SW  										TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BCJN07579					(CAN) 206B3 OWNED BY FOREIGN OPERATOR:  WHILE ROUTINE WALK AROUND, OBSERVED FRACTURE OF THE LOWER SKIN ON THE RT,  FORWA	RD OF THE T/R GEARBOX SUPPORT.					1	G	7	1 	3U			 	H2SW    					 
2004010700015	20040107	00015	SW  	2004	1	7	CA031110005      	1	20020621	G	2910	70612J22OW234	LINE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					HYD SYSTEM	CHAFED          	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING THE PRE-FLIGHT COCKPIT CHECKS WHILE THE AIRCRAFT WAS ON THE GROUND WITH ENGINES STARTED, THE PILOT NOTICED 	NR 2 HYDRAULIC PRESSURE LOSS.  THE AIRCRAFT WAS SHUT DOWN FOR FURTHER INVESTIGATION.  A HYDRAULIC LINE IN THE (HELL HOLE	) WAS FOUND TO BE CHAFED BY A NEARBY BRAIDED LINE CAUSING FLUID LOSS AND THUS PRESSURE LOSS IN NR 2 HYDRAULIC SYSTEM.  T	HE SUBJECT HYDRAULIC LINE WAS REPLACED WITH A NEW LINE AND THE BRAIDED LINE WAS CLAMPED TO PREVENT CONTACT WITH THE SURR	OUNDING LINES. THE AIRCRAFT HYDRAULIC SYSTEM WAS RE-FILLED AND THE AIRCRAFT GROUND RUN FOR LEAKS. NO LEAKS WERE FOUND AN	D THE SYSTEM PRESSURE WAS BACK TO NORMAL.	1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2004012600100	20040126	00100	SW  	2004	1	26	CA031117011      	1	20020909	G	6320		GEARBOX         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CONTAMINATED    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			11888								(CAN) ENGINE CHIP LIGHT ILLUMINATED DURING START.  THE ENGINE WAS REMOVED AND SENT OUT FOR REPAIR.  THE SUSPECTED CAUSE 	OF THE METAL CONTAMINATION WAS THE SPUR ADAPTER GEARSHAFT WHICH WAS A PMA PART OR THE 2.5 BEARING.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004031500052	20040315	00052	NE  	2004	3	15	CA040127009      	2	20020217	G	7230	758378	BLADE           			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ENGINE	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								665399			(CAN) SPARKS WERE REPORTED SEEN COMING FROM ENGINE EXHAUST AND VERIFIED WITH TEST RUNS.  ENGINE WAS REMOVED FEB 17/2002 	AND UNABLE TO IDENTIFY FAULT DURING INSPECTION.  DURING THE SHOP INSPECTION, FAULT WAS IDENTIFIED AS SEPARATION OF AN 8T	H STAGE STATOR BLADE.  MFG  IS LOOKING INTO INVESTIGATING CAUSE OF FAILURE. COMPONENT TSR = 3109.7, CSR = 1625				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2004072900011	20040729	00011	SO  	2004	7	29	CA040622004      	2	20020506	G	8520		CRANKCASE       			CESSNA	182   	182J        	2072722	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WHILE CONDUCTING PRE-FLIGHT CHECK, OIL DRIPS WHERE NOTICED.  AFTER VERIFICATION BY AN AMO, IT WAS DETERMINED THAT 	THERE WAS A SMALL CRACK IN THE CRANKCASE.  ENGINE DISASSEMBLED AND CRANKCASE WAS REPLACED.					1	H	7	1 	3O	3	O	NT	3A13    	E5CE	5	C	P21EA	 
2005041900056	20050419	00056	SO  	2005	4	19	CA041213001      	1	20020111	G	5330	7861901	SKIN            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					WING	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) SKIN ASSY P/N 7861901 MATERIAL AND SKIN THICKNESS IDENTIFIED IN PIPER SENECA SERVICE MANUAL STRUCTURES SECTION FIG	.4-9 NR 5 AS 2024-T3 0.032					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2005041900080	20050419	00080	GL  	2005	4	19	CA041214010      	2	20020603	G	7240	23064570	COMBUSTION LINER			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE847080			(CAN) CRACK FOUND DURING REMOVAL FOR UNRELATED TURBINE CEB. NO CRACKS ALLOWED IN SUBJECT AREA.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2006061900163	20060619	00163	CE  	2006	6	19	CA051109004      	1	20020713	G	3213	508103237	TORQUE LINK     			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											UPON INSPECTION DISCOVERED MLG TORQUE LINKS CRACKED AT CENTER BOLT ATTACH POINTS.  TORQUE LINKS SUBSEQUENTLY REPLACED.						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2006070500245	20060705	00245	EA  	2006	7	5	CA060208008      	1	20020201	G	5411	73507217	LONGERON        			DHAV  	DHC6  	DHC6300     	2802606	EA  										LT NACELLE	FRACTURED       	W				C				ABORTED TAKEOFF         				F	Y		FLT CONT AFFECTED         	ENGINE STOPPAGE           		TO	TAKEOFF        	1			CA			36395								(CAN) ON TAKE-OFF THE ENGINE TORQUE INDICATION OBSERVERED DROPPING OFF, ABORTED TAKE-OFF. OBSERVED LEFT ENGINE SAGGING I	N THE COWLING. (TC# 20060208008)					1	H	7	2 	3T			RT	A9EA    					 
2006061400118	20060614	00118	NE  	2006	6	14	CA060413004      	2	20020221	G	7397	5003T78P04	WIRE HARNESS    								GE    	CT58  	CT581401    	30011	NE  					ENGINE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											SIX NEW HARNESSES WERE SENT TO COLUMBIA HELICOPTERS FOR JET CAL TEST.  ALL SIX FAILED.  THIS WAS THE RESULT OF AN ENGINE	 NOT PASSING TEST ON THE TEST STAND AND THE FAULT WAS FOUND TO BE A NEW T5 HARNESS.  AFTER THAT WE HAVE BEEN SENDING ALL	 NEW T5 HARNESS OUT FOR JET CAL BEFORE BEING INSTALLED ON AN ENGINE.									4	U			1E3				 
2002121700002	20021217	00002	EA  	2002	12	17	DDER146D         	2	20021125	G	8550	LW13388	GASKET          			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					ENG OIL FILTER	DAMAGED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	01	8122Z	482  				288011033				FOUND OIL FILTER CONVERTER GASKET LEAKING.  UPON REPLACEMENT IT WAS NOTICED TO BE DAMAGED.						1	L	7	1 	3O	3	O	 	2A13    	E295				 
2002032700154	20020327	00154	CE  	2002	3	27	DEBA2624D        	1	20020315	G	2897		WIRE HARNESS    			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					BOOST PUMP	CHAFED          	D			DEBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2624D	4209 				4410122				FUEL BOOST PUMP WIRING IN THE WET WING AREA OF EACH WING, WAS CHAFED THROUGH THE INSULATION TO THE CENTER CONDUCTOR. THE	 WIRING, WHERE IT EXITS THE FEED THROUGH CONNETOR PLUG, INTO THE WET WING, AT THE INBOARD MOST RIB, IS CHAFING ON THE BO	X THAT SURROUNDS THE BOOST PUMPS.				1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2002031300123	20020313	00123	NE  	2002	3	13	ERAA077889       	2	20020107	G	7230	PT6T3B	SEAL            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMPRESSOR	LEAKING         	H			ERAA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			FS	01	412EH	8992 				33001				ENGINE HAS 2013.9 HRS SINCE OVERHAUL BY PRATT & WHITNEY.  REMOVED FROM AIRCRAFT DUE TO HIGH OIL CONSUMPTION. USED 5QTS O	F OIL IN 10.8 HRS; SUSPECTED COMP SEAL LEAK.  RETURNING ON ERA REPAIR ORDER RW-887792 REQUESTING WARRANTY REPAIR DUE TO 	SUCH LOW TIME ON ENGINE.				1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002031300124	20020313	00124	EU  	2002	3	13	ERAA077890       	1	20020110	G	6320	4638001001	TRANSMISSION    			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	MAKING METAL    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	125EH	4923 				S562				TRANSMISSION IS  MAKING METAL.  HINGED SUPPORT BEARINGS FROZEN. ONE EACH SLIDING SLEEVE TO CONTROL LINK BRG  MECHANICALL	Y  DAMAGED.  UPPER CENTER HOUSING SLIGHTLY CORRODED ONE PLANETARY AXLE BREAKING DOWN & ONE PLANETARY GEAR PITTED. ACTION	 TAKEN: DISASSEMBLED AS FAR AS NECESSARY FOR REPAIR.  REPLACED ONE PLANETARY GEAR, ONE PLANETARY AXLE,ONE DOUBLE ROWED C	AGE.  REPLACED BOTH HINGED SUPPORT BRGS, ONE CONTROL LINK  TO SLIDING SLEEVE BEARING.  REPLACED LOCK PLATES, AND HARDWAR	E AS NECESSARY. REPAIRED I/A/W BO-105 REM 103 & M/M CHAPTER 41. COPY TO AEC.		1	G	7	2 	3U			 	H3EU    					 
2002031300125	20020313	00125	EU  	2002	3	13	ERAA077891       	1	20020115	G	6320	4638001007	TRANSMISSION    			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	MAKING METAL    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		10465								TRANSMISSION IS MAKING METAL. ALL FOUR CONTROL ROD ASSY BRGS WORN BEYOND LIMITS.  BOTH CENTROL LEVERS BRGS FROZEN.  TWO 	CENTROL LEVER TO SLIDING SLEEVE BRGS FROZEN.  TWO HINGED SUPPORT BRGS FROZEN.  DUST SHIELD CLAMP RUSTED, TOP CASE TO OUT	ER CASE BOLTS MECHANICALLY DAMAGED.  MAST ROLLER BEARING BREAKING DOWN.  ROTOR MAST PITTED ON   FLANGE & BORES.   OIL CO	OLER BLOWER DRIVE BUSHING WORN.  LT INPUT PINION BREAKING DOWN.    RT INPUT PINION LUBRICATE TUBE HAS DAMAGED THREADS. R	T INPUT PINION BREAKING DOWN.  LT BEVEL GEAR BREAKING DOWN.  LT INT SHAFT BRG MECHANICALLY DAMAGED.  LT INT SHAFT ROLLER	 TRACK BREAKING DOWN.  RT BEVEL GEAR BREAKING DOWN.	1	G	7	2 	3U			 	H3EU    					 
2002031300126	20020313	00126	SW  	2002	3	13	ERAA077892       	1	20020116	G	2435	230461030	ARMATURE        			BELL  	412   	412         	1182202	SW  										STARTER GEN	WORN            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	168EH					33067				DRIVE END BEARING JOURNAL  OUT OF LIMITS.						1	G	7	2 	4U			 	H4SW    					 
2002031300127	20020313	00127	SW  	2002	3	13	ERAA077893       	1	20020116	G	2435	230461030	ARMATURE        			BELL  	412   	412         	1182202	SW  										STARTER GEN	MISSING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	418EH									BEARING JOURNAL BASE MISSING.						1	G	7	2 	4U			 	H4SW    					 
2002031300128	20020313	00128	SW  	2002	3	13	ERAA077896       	1	20020117	G	7921	209062502101	IMPELLER        			BELL  	412   	412         	1182202	SW  										COOLER BLOWER	BENT            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	412EH	7755 				33001				IMPELLER BLADES ON OIL COOLER						1	G	7	2 	4U			 	H4SW    					 
2002031300129	20020313	00129	EU  	2002	3	13	ERAA077922       	1	20020215	G	7931	6607190A	SWITCH          			BOLKMS	105   	BO105S      	5626006	EU  										OIL PRESS WARN	INOPERATIVE     	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	128EH	53   				572				OIL PRESSURE WARNING SWITCH IS INOPERABLE.						1	G	7	2 	3U			 	H3EU    					 
2002031300130	20020313	00130	SW  	2002	3	13	ERAA077924       	1	20020219	G	6320	412040002103	HOUSING         			BELL  	412   	412         	1182202	SW  										TRANSMISSION	BROKEN          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	422EH	10475				33068				AUX JET HOUSING CRACKED,  HOUSING BROKEN IN TWO PIECES. ACTION TAKEN:  REMOVED TOP CASE AND UPPER PLANETARY INSTALLED NE	W HOUSING AND GASKET.  REINSTALLED UPPER PLANETARY AND TOP CASE ALL WORK IAW BHT CR&O 63.					1	G	7	2 	4U			 	H4SW    					 
2002041900024	20020419	00024	EU  	2002	4	19	ERAA078421       	1	20020227	G	6320	23008021	HOUSING         			BOLKMS	105   	BO105S      	5626006	EU  										GEARBOX	DEBONDED        	A			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	149EH					S705				(2)  1/4 X 28 STUDS PULLED FROM HOUSING.  RETURNED FROM OVERHAUL.						1	G	7	2 	3U			 	H3EU    					 
2002041900025	20020419	00025	EU  	2002	4	19	ERAA078424       	1	20020314	G	7900		COVER           			BOLKMS	105   	BO105S      	5626006	EU  										SUMP	CORRODED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	134EH					635				SENT FOR REPAIR 11/2001 AND RETURNED 1/18/2002 AND COULD NOT BE USED ON THE AIRCRAFT DUE TO LINE OF CORROSION PITTS ON A	FT SUMP COVER.					1	G	7	2 	3U			 	H3EU    					 
2002042300031	20020423	00031	EU  	2002	4	23	ERAA078446       	1	20020320	G	2421	230322111	ARMATURE        			BOLKMS	105   	BO105S      	5626006	EU  										GENERATOR	ARCED           	H			ERAA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	128EH					572				EXCESSIVE ARCHING DURING TEST.  WAS ISSUED TO AIRCRAFT BUT COULD NOT BE USED.						1	G	7	2 	3U			 	H3EU    					 
2002042300032	20020423	00032	EU  	2002	4	23	ERAA078447       	1	20020326	G	7810	6879879	COLLECTOR RING  			BOLKMS	105   	BO105S      	5626006	EU  										EXHAUST	GROOVED         	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	134EH					635				EXHAUST COLLECTOR RETURNED FROM OVERHAUL AND ISSUED TO AIRCRAFT BUT COULD NOT BE INSTALLED DUE TO GROOVED .100 IN MOUNT 	AREA.					1	G	7	2 	3U			 	H3EU    					 
2002042300033	20020423	00033	EU  	2002	4	23	ERAA078450       	1	20020403	G	7810	6879879	COLLECTOR RING  			BOLKMS	105   	BO105S      	5626006	EU  										EXHAUST	MISOVERHAULED   	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	134EH					635				EXHAUST COLLECTOR REC'D BACK 1-10-02 FROM OVERHAUL AND COULD NOT BE INSTALLED ON A/C ISSUED TO DUE TO TOP TURBINE MOUNT 	BEING DEBONDED.					1	G	7	2 	3U			 	H3EU    					 
2002042300034	20020423	00034	GL  	2002	4	23	ERAA078452       	2	20020403	G	7320	252466715H	GOVERNOR        								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	H			ERAA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01		12618								GOVERNOR DROOPING EXCESSIVELY, OUT OF SERVICE LIMITS.  INTERNAL BEARINGS FOUND ROUGH / RATCHETY, DRIVESHAFT SPLINES WORN	 BEYOND LIMITS, DRIVE SLEEVE SPLINES WORN, GOVERNOR WEIGHTS WORN FLAT.										3	U			E4CE				 
2002042300035	20020423	00035	GL  	2002	4	23	ERAA078453       	2	20020403	G	7320		DIAPHRAGM       			BOLKMS	105   	BO105A      	       	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENG GOVERNOR	DEFORMED        	H			ERAA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			FS	01	291EH	10974				S842				NR 1 STARTS HUNTING UP & DOWN AFTER 10-20 MIN.  GOVERNOR BLEEDS OFF 200 RPM TOO EARLY.  GOVERNOR LEVER, CAM LEVER AND FL	Y WEIGHT BEARINGS FOUND ROUGH AND DRY. PR DIAPHRAGM FOUND DEFORMED.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002042300036	20020423	00036	GL  	2002	4	23	ERAA078455       	2	20020403	G	7320		BEARING         								ALLSN 	250C  	250C20B     	03013	GL  					ENG GOVERNOR	ROUGH           	H			ERAA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			FS	01		11828								GOVERNOR HITS MAX STOP WITH COLLECTIVE UP.  DROOPING AND OVERSPEEDING EARLY.  FOUND CAN LEVER OVERSIZED, ECCENTRIC SHAFT	 UNDERSIZED, SIX INTERNAL BEARINGS FOUND ROUGH/ RATCHETY.										3	U			E4CE				 
2002042300037	20020423	00037	EU  	2002	4	23	ERAA078456       	1	20020404	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	MALFUNCTIONED   	H			ERAA	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			FS	01		8715 								EXCESSIVE RIGHT PEDAL REQUIRED IN A HOVER.  FOUND NO DEFECTS ACTION TAKEN:  REMOVED BLADES AND REPLACED WITH BLADES SN 2	11 & 218 FOR TROUBLESHOOTING PURPOSES.  REMOVED STRAP PACK BOLTS FOR INSPECTION OF BUSHINGS.  FOUND NO DEFCTS & REINSTAL	LED BOLTS.  STATIC BALANCED.  REPAIRED IAW BO105 REM 301, MM CH 33,34,102 & MARVEL MM.				1	G	7	2 	3U			 	H3EU    					 
2002042300038	20020423	00038	EU  	2002	4	23	ERAA078457       	1	20020404	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	MALFUNCTIONED   	H			ERAA	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			FS	01	298EH	10028				S845				HEAVY LEFT PEDAL FORCES WITH MAX WEIGHT ADJUSTMENT.  NO OBVIOUS DEFECTS. ACTION TAKEN:  REMOVED BLADES AND MOUNTING FORK	S.  VISUALLY INSPECTED AND FOUND NO DEFECTS.  RE-ASSEMBLED AND STATIC BALANCED.,  REPAIRED IAW BO-105 REM 301, MM CH 33,	 34, 102 & 106.				1	G	7	2 	3U			 	H3EU    					 
2002042300039	20020423	00039	SW  	2002	4	23	ERAA078458       	1	20020404	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	419EH	8855 								INSPECTION DUE TOP SKIN 1/3 DOWN LENGTH OF BLADE FROM ROOT, VOIDED AREA AS MARKED, EDGES OF INBOARD TAB POPPED UP.  ESTA	NE BOOT DAMAGED, LOWER SURFACE GRIP VOID, INBOARD TRIM TAB VOID WITH GLASS DAMAGE, INBOARD ABRASION STRIP TANG  VOID UPP	ER AND LOWER SURFACE.  WATER IN BLADES AT SKIN PATCH, FILLER CRACKING AT TABS.  WATER IN BLADE 30 TO 40 CELLS.  DETERMIN	ED BY X-RAY INSPECTION OF SUSPECT AREA. ACTION TAKEN:  REPAIRED AS PER 8130-3 BLK #13.			1	G	7	2 	4U			 	H4SW    					 
2002042300040	20020423	00040	NE  	2002	4	23	ERAA078459       	1	20020404	G	6210	6117020201067	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  										MAIN ROTOR	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	563EH	9656 				61808				ABRASION STRIP DEBONDING ABOUT 2 FEET FROM END.  LAST POCKET NR 25 CRACKED ON TOP AND BOTTOM, COMING SEPERATED FROM SPAR	.  CUFF LEAKING AT BOLTS, NR 25 POCKET CRACKED AND VOID, O/B ABRASION STRIP VOID, CTR ABRAISION STRIP VOID, NR`S 13, 15,	 16 POCKETS VOID, NR 12 POCKET CRACKED, POLY SPLICE COVER ERRODED. ACTION TAKEN:  REPAIRED AS PER 8130-3 BLOCK NR 13.				2	G	7	2 	4U			 	1H15    					 
2002042300041	20020423	00041	GL  	2002	4	23	ERAA078460       	2	20020404	G	7210		BEARING         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	WORN            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	130EH	6891 				558				ENGINE IS MAKING METAL.  FOUND ROLLER ON 2 1/2 BEARING DAMAGED.  GEARBOX PN 6894171 SN CAG-39145 INSTALLED.  REPAIRED GE	ARBOX PN 6894171, SN CAG-23194.  GEASHAFT DAMAGED, PN E23031922, SN CI-21-536, O/H OIL CHECK VALVE PN 23031856. ACTION T	AKEN:  INSTALLED REPAIRED GEARBOX PN 6894171, SN CAG-23194, INSTALLED NEW GEAR SHAFT, P/N E63031922, SN DG14-147, INSTAL	LED NEW CHECK VALVE PN 23069740.			1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002042300042	20020423	00042	GL  	2002	4	23	ERAA078461       	2	20020404	G	7250	6898735	TURBINE         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	127EH	8895 				571				TOT INDICATING AMBIENT TEMPERATURE. ACTION TAKEN:  SENT HARNESS OUT FOR REPAIR.  BURNED VANES ON NR 1 NOZZLE.  INSTALLED	 NEW TAT HARNESS AND NR 1 NOZZLE.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002042300043	20020423	00043	SW  	2002	4	23	ERAA078462       	1	20020404	G	6220		BUSHING         			BELL  	412   	412         	1182202	SW  										M/R HEAD	MISSING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	168EH	13544				33067				BUSHINGS 412-010-121-101 MISSING FROM YOKE RED BLADE, COMPLY WITH 2500 HR INSPECTION.  BUSHINGS MISSING, VISUAL INSPECTI	ON APPEARS NORMAL ON YOKE & FITTING. ACTION TAKEN:  DISASSEMBLED, CLEANED, INSPECTED, COMPLIED WITH 2500 HR INSPECTION I	AW 412 CR&O & 412 M/M, INSTALLED YOKE BUSHINGS, SERVICEABLE LOWER CONE SEAT, SPLINE PLATE, LOWER CONE, NEW DAMPER SETS, 	ASSEMBLED IAW 412 CR&O.			1	G	7	2 	4U			 	H4SW    					 
2002042300044	20020423	00044	SW  	2002	4	23	ERAA078463       	1	20020404	G	7921	209062502101	BLOWER          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					OIL COOLER	WORN            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		11234								OIL COOLER BLOWER DUE 1500 HR OVERHAUL.  WORN INBOARD BUSHING IN CASING ASSY.  CRACKED IMPELLER. ACTION TAKEN:  C/W PREL	IMINARY INSPECTION.  NO DEFECTS NOTED.  DISASSEMBLED OIL COOLER, CLEANED, STRIPPED PAINT & PRIMER &  VISUALLY INSPECT AL	L PARTS.  FOUND MECHANICAL DAMAGE ON BEARING BUSHING OF CASING ASSY AND SENT TO H&S TOOL FOR REPAIR. CLEANED UP LIGHT CO	RROSION ON REMAINING PARTS. C/W NDT INSP & FOUND CRACK ON IMPELLAR, PARTS FOUND TO BE IN SERVICEABLE CONDITION.  INSTALL	ED 1EACH NEW BRG IN CASING ASS6Y, 1 EACH NEW BEARING ON SHAFT.  PRIMED PARTS & REASSEMBLED OIL COOLER WITH ALL NEW HARDW	ARE, NEW DECAL & NEW SHAFT O RING. O/H OIL COOLER IAW BHT 412 CR&O9CHAP 79 & BHT-ALL-SPM CHAP 2 .	1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002042300045	20020423	00045	EU  	2002	4	23	ERAA078464       	1	20020404	G	6321	AHA1121MOD1234	BRAKE           			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		10777								INNER PISTON FROZEN.  NEEDED ON ADDITIONAL SHIM INSTALLED UNDER THE DISC SPRINGS ON THE PIN RETRACTION.  PADS MISSING.  	EXCLUDER DUST BOTH TORN. ACTION TAKEN:  REPAIRED AND TESTED.					1	G	7	2 	3U			 	H3EU    					 
2002042300046	20020423	00046	SW  	2002	4	23	ERAA078465       	1	20020404	G	6320	412040002103	TRANSMISSION    			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	MAKING METAL    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	418EH	8093 								TRANSMISSION IS MAKING METAL.   ACCESSORY T/R INPUT QUILL BEARING SET, ROLLERS & RACES MAKING METAL. ACTION TAKEN:  CHAN	GED SUMP CASE, ASSY/ INPUT DRIVE QUILL.  C/W 3100 HOUR INSPECTION.  REPLACED MAIN INPUT PINION AND ALL BRGS.  CLEANED AN	D FLUSHED ALL OIL PASSAGES.TESTED AND TOUCHED UP PAINT.				1	G	7	2 	4U			 	H4SW    					 
2002062500013	20020625	00013		2002	6	25	ERAA079864       	4	20020430	G	3442	40008330208	INDICATOR       			SKRSKY	S61   	S61N        	8142104	NE  										RADAR SYSTEM	CONTAMINATED    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	563EH	1102 				61808				WILL NOT POWER UP ; NO INDICATION.  UNIT HAS MAJOR WATER DAMAGE.   REPAIRED BURNED TRACE, REMOVED CORROSION AND TESTED.						2	G	7	2 	4U			 	1H15    					 
2002071900043	20020719	00043	NE  	2002	7	19	ERAA080332       	1	20020610	G	6210	7615009043050	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										M/R BLADE	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	578EH	1610 				760099				TIP CAP IS CRACKED. FORWARD INTERNAL DOUBLERS VOID. ACTION TAKEN:  REPLACED INTERNAL FWD DOUBLERS AND REBONDED C-CHANNEL	, REFINISHED PAINT AND STATIC BALANCED.					1	G	7	2 	3U			 	H1NE    					 
2002071900048	20020719	00048	NE  	2002	7	19	ERAA080333       	1	20020610	G	6210		BLADE           			SKRSKY	S61   	S61N        	8142104	NE  										MAIN ROTOR	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		7686 								MAIN ROTOR BLADE HAS CRACK IN POCKET NR 9 FROM ROOT END ON BOTTOM. ACTION TAKEN:  REPLACED POCKET NR 17, NR 20 REPLACED 	O/B ABRAISION STRIP, REPLACED RUBBER CAP, TOUCHED UP, AND BALANCED, CHANGED SPAR, REPLACED NUT PLATE.					2	G	7	2 	4U			 	1H15    					 
2002071900054	20020719	00054	NE  	2002	7	19	ERAA080334       	1	20020610	G	6210	6117020201067	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  										MAIN ROTOR	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		8724 								SPAR PRESSURE BELOW MINIMUM CHECK PRESSURE. ACTION TAKEN:  REPAIRED AS PER BLOCK NR 13 OF 8130-3.						2	G	7	2 	4U			 	1H15    					 
2002081300143	20020813	00143		2002	8	13	ERAA080469       	4	20020715	G	3442	40008330207	INDICATOR       			BELL  	412   	412         	1182202	SW  										WX RADAR	CONTAMINATED    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	418EH									INOPERABLE; UNIT WOULD NOT POWER UP.  FOUND MAJOR WATER DAMAGE. ACTION TAKEN:  REPLACED ALL BAD PARTS, REM'D CORROSION, 	REPAIRED BROKEN WIRES, RE-SOLDERED COLD SOLDER JOINTS, ALIGNED AND TESTED.  NS					1	G	7	2 	4U			 	H4SW    					 
2002101500039	20021015	00039	CE  	2002	10	15	FAI001           	1	20021011	G	3230	100951X063XE	WASHER          			BEECH 	200   	200BEECH    	1152920	CE  										MLG	MISSING         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	13	432FA	1700 	1700 			BB592				FOLLOWING TAKEOFF, GEAR RETRACTION FAILED, WITH GEAR STUCK IN-TRANSIT. A NOISE WAS HEARD FROM THE LEFT SIDE OF THE AIRCR	AFT AT THE TIME OF FAILURE. EMERGENCY EXTENSION EFFORTS PRODUCED NO RESULTS, AND THE EMERGENCY EXTENSION HANDLE BECAME S	EIZED. CONTACT WITH MAINTENANCE PERSONNEL CAUSED THE COPILOT TO OPEN THE CABIN FLOOR OVER THE GEAR DRIVE MECHANISM, AND 	REVEALED THAT THE LANDING GEAR MOTOR CONTROLLER CIRCUIT BREAKER WAS OPEN. BREAKER WAS RESET, AND THE LANDING GEAR EXTEND	ED NORMALLY. PRIOR TO LANDING, A FLYOVER OF THE MAINTENANCE PERSONNEL REVEALED THE LEFT MAIN GEAR WHEELS TO BE TURNED AP	PROXIMATELY 20 DEGREES RIGHT. LANDING WAS COMPLETED WITH NO INCIDENT. INVESTIGATION REVEALED THAT THE LEFT MAIN GEAR TOR	1	L	7	2 	4T			 	A24CE   					 
2002101500013	20021015	00013	NE  	2002	10	15	FF6R112443       	2	20020816	G	7210	350A32314306	GEAR            								TMECA 	ARRIEL	ARRIEL1D    	 	NE  					RGB	DENTED          	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11										PINION HAS DENT ON END OF SHAFT.  BEVEL RING GEAR HAS CHATTER MARKS IN 7 HOLES.											3	U			E19EU				 
2002041900026	20020419	00026	EU  	2002	4	19	GSG              	1	20020417	G	4960	211746066	ECU             			AMD   	FALC50	FALCON50MYST	2730106	EU  										APU	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	744X		185  			58				APU WILL NOT START (NO START SEQUENCE AT ALL).  AFTER PRESSING THE APU MASTER, THE APU START BUTTON NEVER ILLUMINATED.  	THE RPM GAUGE INDICATES 120 PERCENT AT ALL TIMES.  THE APU FAULT PANEL INDICATES LOW OIL PRESSURE, OVERSPEED.  DETERMINE	D THAT THE APU ECU WAS DEFECTIVE.  WITH THE APU SHUT DOWN, THE ECU INDICATED THAT THE APU WAS RUNNING.  THE APU WOULD NO	T START BECAUSE THE LOW OIL PRESSURE LOGIC PREVENTED IT FROM STARTING.  REPLACED THE ECU.  APU STARTS AND RUNS NORMAL.			2	L	7	3 	4F			 	A46EU   					 
2002012200037	20020122	00037	NE  	2002	1	22	HEEA077553       	2	20020104	G	7321	0292928540	METERING VALVE  			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					FUEL CONTROL	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	973AE					3229				FUEL CONTROL METERING VALVE HAS INTERNAL FUEL LEAK.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002012200038	20020122	00038	GL  	2002	1	22	HEEA077554       	2	20020104	G	7250	230583299	TURBINE WHEEL   			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	30KH	358  				51527	CAE895129			ENGINE WAS REMOVED DUE TO WHISTLING SOUND AT HOVER AND GRINDING ROAR ON COOL DOWN.  UPON INSPECTION OF TURBINE PARTS NOT	ED NR 1 WHEEL BLADE FAILURE WITH 1/8 INCH OF BLADE REMAINING FROM BLADE ROOT LEADING EDGE.  BLADE TIPS EXHIBIT TIP DRAG 	AND FOD DAMAGE. NR 2 NOZZLE 1ST STAGE TIP PATH RUNOUT AT DISASSEMBLY WAS .002 INCHES AND 1ST STAGE WHEEL TIP CLEARANCE I	S .014 INCHES ASSEMBLY TIP CLEARANCE WAS .0135 INCHES. PART WILL BE RETURNED TO ROLLS ROYCE FOR FAILURE INVESTIGATION.			1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002012200039	20020122	00039	GL  	2002	1	22	HEEA077555       	2	20020111	G	7250	6870832	COUPLING        			BELL  	206   	TH57A       	1180821	SW  	ALLSN 	250C  	250C18A     	03011	GL  					ENGINE	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	128					162814				NEW PART RECEIVED WITH IMPROPER PART NUMBER 6850832 ENGRAVED ON PART.						1	G	7	1 	3U	3	U	 	EXPA1G71	E4CE				 
2002012200040	20020122	00040	GL  	2002	1	22	HEEA077556       	2	20020116	G	7230	6890550	COMPRESSOR      			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1 ENGINE	FAILED          	E			HEEA	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	7136H	3876 				S833				ON SECOND FLIGHT OF THE DAY, IN CRUISE, THE AIRCRAFT YAWED FOLLOWING WITH GENERATOR LIGHT ON, AUDIO ON, DECLINE OF N2, N	1 AND OIL PRESSURE ON NR 1 ENGINE.  SECURED NR 1 ENGINE. MAINTENANCE FOUND NR 1 COMPRESSOR FAILURE.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002012200041	20020122	00041	GL  	2002	1	22	HEEA077558       	2	20020116	G	7230		COMPRESSOR      			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	E			HEEA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	7136H	382  				S833	CAE835247			ENGINE REMOVED DUE TO IN FLIGHT COMPRESSOR DAMAGE.  UPON INSPECTION OF COMPRESSOR PARTS NOTED WIPE OUT OF 2ND THRU 5TH S	TAGE COMPRESSOR WHEEL BLADES, EXCESSIVE FOD TO CASE HALF ASSY, 1ST THRU 6TH STAGE WHEELS, IMPELLER AND TURBINE.  SUSPECT	ED CAUSE IS 2ND STAGE COMPRESSOR BLADE FAILURE.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002012300110	20020123	00110	SW  	2002	1	23	HEEA077658       	1	20020102	G	6300	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	FAILED          	E			HEEA	A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			SW	03	3193E	140  				53276				IN CRUISE, PILOT DETECTED VIBRATION / LOW RUMBLING NOISE FROM AFT AREA OF AIRCRAFT.  NOISE/VIBRATION INCREASED WITH INCR	EASE IN POWER. MAINTENANCE INSPECTED AND FOUND NR 2 SHAFT / OIL COOLER ASSY AFT BEARING FAILURE.					1	G	7	1 	3U			O	H2SW    					 
2002012300111	20020123	00111	SW  	2002	1	23	HEEA077659       	1	20020104	G	5302		STRUCTURE       			BELL  	214   	214ST       	1182106	SW  										TAIL BOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N	9962 				28106				DURING POST FLIGHT INSPECTION, MAINTENANCE DISCOVERED CRACK IN TAIL BOOM VERTICAL PYLON STRUCTURE.						2	G	7	2 	4U			 	H10SW   					 
2002012300112	20020123	00112	SW  	2002	1	23	HEEA077660       	1	20020104	G	2820	222366621101	FUEL FILTER     			BELL  	222   	222         	1182122	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										FUEL FILTER LIGHT WILL NOT COME ON WHEN BUTTON IS PUSHED.						1	G	7	2 	3U			 	H9SW    					 
2002012300113	20020123	00113	SW  	2002	1	23	HEEA077662       	1	20020108	G	5302		STRUCTURE       			BELL  	407   	407         	1182206	SW  										TAIL BOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH	2217 				53399				TAIL BOOM STRUCTURE IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002012300114	20020123	00114	SW  	2002	1	23	HEEA077663       	1	20020108	G	6420	407012101111	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR G/B	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH	2217 				53399				TAIL ROTOR HUB IS STUCK ON GEARBOX.						1	G	7	1 	3U			O	H2SW    					 
2002012300115	20020123	00115	SW  	2002	1	23	HEEA077664       	1	20020108	G	6420		HUB             			BELL  	407   	407         	1182206	SW  										T/R GEARBOX	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH	2217 				53399				T/R HUB ASSY STUCK ON GEARBOX.						1	G	7	1 	3U			O	H2SW    					 
2002012300116	20020123	00116	SW  	2002	1	23	HEEA077665       	1	20020108	G	6420	407012110101	STOP            			BELL  	407   	407         	1182206	SW  										T/R GEARBOX	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH	2217 				53399				STUCK ON GEARBOX. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PARTS PURCHASED.  PHI HAS NOT YET RECEI	VED REPLACEMENTS.  REFERENCE:  DMR#744646.					1	G	7	1 	3U			O	H2SW    					 
2002012300117	20020123	00117	SW  	2002	1	23	HEEA077666       	1	20020109	G	8011		PIN             			BELL  	214   	214ST       	1182106	SW  										CLUTCH SHAFT	SHEARED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					95H1357					250 HOUR INSPECTION, PIN SHEARED IN CLUTCH SHAFT.						2	G	7	2 	4U			 	H10SW   					 
2002012300118	20020123	00118	SW  	2002	1	23	HEEA077670       	1	20020111	G	2140	205072277009	VALVE           			BELL  	412   	412         	1182202	SW  										HEATER	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										HEATER WILL NOT PUT OUT SUFFICIENT HEAT.						1	G	7	2 	4U			 	H4SW    					 
2002012300119	20020123	00119		2002	1	23	HEEA077671       	4	20020111	G	2330	222899604101	CONTROL PANEL   			BELL  	222   	222         	1182122	SW  										PA SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PA INOPERATIVE.						1	G	7	2 	3U			 	H9SW    					 
2002012300120	20020123	00120	SW  	2002	1	23	HEEA077675       	1	20020116	G	2497	214175171103	RELAY           			BELL  	214   	214ST       	1182106	SW  										ELECTRICAL	BURNED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										BURNT CONTACTS.  VOLTAGE ON STARTS WON'T GO ABOVE 32 VDC.						2	G	7	2 	4U			 	H10SW   					 
2002012300121	20020123	00121	SW  	2002	1	23	HEEA077676       	1	20020116	G	2497	214175131103	RELAY           			BELL  	214   	214ST       	1182106	SW  										ELECTRICAL	BURNED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										BURNT CONTACTS.  VOLTAGE ON STARTS WON'T GO ABOVE 32 VDC.						2	G	7	2 	4U			 	H10SW   					 
2002012300122	20020123	00122	SW  	2002	1	23	HEEA077677       	1	20020116	G	2560	222320823119	SEAT BELT       			BELL  	222   	222         	1182122	SW  										COCKPIT	MISINSTALLED    	E			HEEA	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	03										RESTRAINT INSTALLED ON SPOOL BACKWARDS.						1	G	7	2 	3U			 	H9SW    					 
2002012300123	20020123	00123		2002	1	23	HEEA077678       	4	20020116	G	2200	214074303115	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTO FLIGHT	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										WON'T MONITOR TEST.  STICK WANDERS.  DIFFICULT TO ADJUST R91 ON BOARD 11 & 9.						2	G	7	2 	4U			 	H10SW   					 
2002012300124	20020123	00124		2002	1	23	HEEA077679       	4	20020116	G	2200	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTO FLIGHT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										CAUSES ELEVATOR LIGHT TO STAY ON.						2	G	7	2 	4U			 	H10SW   					 
2002012300125	20020123	00125		2002	1	23	HEEA077680       	4	20020116	G	2200	214074303115	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTO FLIGHT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										AMPLIFIER  CAUSING PITCH AXIS TO KICK.						2	G	7	2 	4U			 	H10SW   					 
2002012300126	20020123	00126	EU  	2002	1	23	HEEA077682       	1	20020111	G	6400	355A09103601	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	SEPARATED       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	973AE	224  				3229				TAIL ROTOR BEARING SEPARATION.						1	G	7	1 	3U			 	H9EU    					 
2002012300127	20020123	00127	EU  	2002	1	23	HEEA077683       	1	20020111	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	40466	5465 				3004				TGT BLADE LOWER FACE POLY TAPE SEPARATED AND MISSING.						1	G	7	1 	3U			 	H9EU    					 
2002012300128	20020123	00128	EU  	2002	1	23	HEEA077684       	1	20020111	G	7930	648183031	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	975AE					2777				NEEDLE STICKS ON LOW SIDE AND REAR RING CRACKED.						1	G	7	1 	3U			 	H9EU    					 
2002012300129	20020123	00129	EU  	2002	1	23	HEEA077685       	1	20020111	G	6730	SC5084	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										CYCLIC STICK	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	40466					3004				SERVO LEAKING.						1	G	7	1 	3U			 	H9EU    					 
2002012300132	20020123	00132	EU  	2002	1	23	HEEA077686       	1	20020111	G	6410	355A09103601	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										T/R BLADE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	974AE	384  				2653				BEARING HAS RUBBER SEPARATION.						1	G	7	1 	3U			 	H9EU    					 
2002030100017	20020301	00017	EU  	2002	3	1	HEEA077699       	1	20020123	G	6320		SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  										M/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	4036H	3473 				2919				GEARBOX LEAKING OIL AT AIR / OIL SEPARATOR SEAL AT APPROXIMATELY 2 LITERS PER HOUR.						1	G	7	1 	3U			 	H9EU    					 
2002030100044	20020301	00044	NE  	2002	3	1	HEEA077705       	2	20020219	G	7320	0292958050	VALVE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	971AE	1104 				3230	22072			ENGINE WOULD START INTERMITTENTLY.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002030100045	20020301	00045	SW  	2002	3	1	HEEA077708       	1	20020118	G	6320	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MAIN ROTOR BEARING FAILURE.						1	G	7	1 	3U			O	H2SW    					 
2002030100046	20020301	00046	SW  	2002	3	1	HEEA077709       	1	20020118	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X	3156 				53267				STARTER GEN HAS WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2002030100053	20020301	00053	SW  	2002	3	1	HEEA077714       	1	20020121	G	6330	406040056101	CASE            		206040004107	BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8587X				B51719	51464				CRACK INDICATIONS ON WEBS OF TRANSMISSION.						1	G	7	1 	3U			 	H2SW    					 
2002030100055	20020301	00055	SW  	2002	3	1	HEEA077721       	1	20020122	G	7120	206064105101	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										ENGINE MOUNT LEG IS MISIDENTIFIED BY PART NUMBER.						1	G	7	1 	3U			 	H2SW    					 
2002030100057	20020301	00057		2002	3	1	HEEA077725       	4	20020122	G	3417	214175421101	ADC             			BELL  	214   	214ST       	1182106	SW  										COCKPIT	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										NR 1 POWER ASSURANCE WILL NOT TEST.						2	G	7	2 	4U			 	H10SW   					 
2002030100058	20020301	00058	SW  	2002	3	1	HEEA077726       	1	20020122	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										SLOW STARTS.  HAVING STARTER PROBLEMS.						2	G	7	2 	4U			 	H10SW   					 
2002030100063	20020301	00063	SW  	2002	3	1	HEEA077732       	1	20020125	G	6310	406040500113FM	FREEWHEEL UNIT  			BELL  	206   	206L4       	1182110	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	7077B	361  				52037				FREEWHEEL UNIT IS LEAKING.						1	G	7	1 	3U			NC	H2SW    					 
2002030100064	20020301	00064	SW  	2002	3	1	HEEA077733       	1	20020125	G	3212	407350300101	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				EMERGENCY FLOAT BAG IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002030100065	20020301	00065	SW  	2002	3	1	HEEA077734       	1	20020125	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				TORQUE INDICATOR SPIKED TO 134.1 PERCENT FOR 1.						1	G	7	1 	3U			O	H2SW    					 
2002030100066	20020301	00066	SW  	2002	3	1	HEEA077735       	1	20020125	G	3110	407375002103	INDICATOR       			BELL  	407   	407         	1182206	SW  										COCKPIT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				INTERNAL LIGHTING TOO DIM.  DIFFICULT TO READ IN DAYLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2002030100069	20020301	00069	SW  	2002	3	1	HEEA077739       	1	20020128	G	6700	206076062107	CYCLIC STICK    			BELL  	407   	407         	1182206	SW  										COCKPIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH	2078 				53398				CYCLIC STICK HAS FORWARD BEARING WEAR.						1	G	7	1 	3U			O	H2SW    					 
2002030400008	20020304	00008	SW  	2002	3	4	HEEA077753       	1	20020128	G	2922	206076030111	PUMP            			BELL  	407   	407         	1182206	SW  										FUEL BOOST	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	719PH					53266				FUEL BOOST PUMP LEAKING OUT OF SEAL DRAIN.						1	G	7	1 	3U			O	H2SW    					 
2002030400013	20020304	00013	SW  	2002	3	4	HEEA077760       	1	20020128	G	6300	400040055109	HOUSING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				MAIN ROTOR HOUSING REMOVED FOR AN EVALUATION DUE TO EXCESSIVE CORROSION UNDER PAINT.						1	G	7	1 	3U			O	H2SW    					 
2002030400016	20020304	00016	SW  	2002	3	4	HEEA077763       	1	20020128	G	7712	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										TORQUE	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	510PH					53209				TORQUE TRANSMITTER INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2002030400029	20020304	00029	SW  	2002	3	4	HEEA077779       	1	20020128	G	6300	407340339101	BEARING         		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH				PHI0020	53435				MAIN ROTOR OIL COOLER BLOWER BEARING IS ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002030400030	20020304	00030	SW  	2002	3	4	HEEA077780       	1	20020128	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	493PH					53393				LOW FUEL LIGHT STAYS ON.						1	G	7	1 	3U			O	H2SW    					 
2002030400033	20020304	00033	SW  	2002	3	4	HEEA077788       	1	20020130	G	2822	1C2710	CARTRIDGE       			BELL  	407   	407         	1182206	SW  										FUEL BOOST	FAULTY          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	724PH					53327				FAULTY CARTRIGE CAUSING FUEL BOOST PUMP TO NOT RUN.						1	G	7	1 	3U			O	H2SW    					 
2002030400035	20020304	00035		2002	3	4	HEEA077790       	4	20020130	G	3197		CONNECTOR       			BELL  	407   	407         	1182206	SW  										INSTRUMENT PANEL	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				PINS BENT IN THE CONNECTOR THAT ATTACHES TO AIRFRAME.						1	G	7	1 	3U			O	H2SW    					 
2002030400053	20020304	00053	SW  	2002	3	4	HEEA077808       	1	20020130	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										T/R UNIVERSAL	UNSTAKED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH	1018 			RXFS5791	53400				TAIL ROTOR UNIVERSAL BEARING UNSTAKED.						1	G	7	1 	3U			O	H2SW    					 
2002031100072	20020311	00072	SW  	2002	3	11	HEEA077871       	1	20020219	G	6220	407310101010	BEARING         			BELL  	407   	407         	1182206	SW  										M/R HEAD	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				MAIN ROTOR HEAD BEARINGS CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002031100096	20020311	00096		2002	3	11	HEEA077882       	4	20020219	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTO FLIGHT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										AMPLIFIER KICKS ELEVATORS OFF LINE WHEN ENGAGED.						2	G	7	2 	4U			 	H10SW   					 
2002031100102	20020311	00102	EU  	2002	3	11	HEEA077888       	1	20020208	G	2400	410CC01Y140	CONTACTOR       			SNIAS 	350   	AS350B      	8680801	EU  										ELECTRICAL	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	855PH					3351				CONTACTOR HAS HIGH RESISTANCE.						1	G	7	1 	3U			 	H9EU    					 
2002031800134	20020318	00134	NE  	2002	3	18	HEEA078002       	2	20020226	G	7200	0292005220	ENGINE          			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  						DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	855PH	4813 				3351				NO N1 INDICATION NOISE WHEN TURNING ENGINE.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002031800135	20020318	00135	EU  	2002	3	18	HEEA078003       	1	20020301	G	2611		FIRE LOOP       			SNIAS 	350   	AS350B      	8680801	EU  										ENGINE	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	975AE					2777				PROBE BECAME UNSOLDERED AT PROBE ATTACH NUT AND CAME OUT OF ENGINE.						1	G	7	1 	3U			 	H9EU    					 
2002031900063	20020319	00063	GL  	2002	3	19	HEEA078019       	2	20020311	G	7230	23056634	SPUR ADAPTER    		23051643    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					COMPRESSOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G	704  			CAC90474	760232	CAE890279S			COMPRESSOR WAS REMOVED WITH ENGINE DUE TO TURBINE NR 1 & 2 WHEEL CYCLES.  DECISION MADE TO COMPLY WITH COMPRESSOR 2000 H	OUR INSPECTION AND OVERHAUL FOR IHTI REQUIREMENTS.  SPUR GEAR FAILED NO-GO GAUGE CHECK. SUBMITTAL FOR CREDIT ACCOMPLISHE	D ON AFA 63885A.				1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002031900064	20020319	00064	SW  	2002	3	19	HEEA078021       	1	20020222	G	2730	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										ELEVATORS	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										ELEVATORS WILL NOT TEST.						2	G	7	2 	4U			 	H10SW   					 
2002031900067	20020319	00067		2002	3	19	HEEA078022       	4	20020222	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTO FLIGHT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										ELEVATORS WILL NOT TEST.						2	G	7	2 	4U			 	H10SW   					 
2002031900070	20020319	00070		2002	3	19	HEEA078023       	4	20020222	G	2210	412074030101	ISOLATION AMP   			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT	FAILED          	E			HEEA	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	03	5748M					28102				IN FLIGHT THE CREW DETECTED A SMOKE ODOR.  THE AARS AND NR 2 ELEVATOR SYSTEM WENT OFF LINE.  THE CIRCUIT BREAKER FOR THE	 COPILOT ADI TRIPPED. MAINTENANCE REPLACED THE ISOLATION AMPLIFIER.					2	G	7	2 	4U			 	H10SW   					 
2002031900072	20020319	00072		2002	3	19	HEEA078024       	4	20020222	G	2210	222331617103	ISOLATION MOUNT 			BELL  	230   	230         	1182149	SW  										AUTOFLIGHT	FAILED          	E			HEEA	O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	03	14UH					23028				IN CRUISE FLIGHT, AN AIRFRAME VIBRATION DEVELOPED.  MAINTENANCE FOUND THE LATERAL ISOLATION MOUNT FAILED. MAINTENANCE RE	PLACED THE ISOLATION AMPLIFIER.					1	G	7	2 	3U			NC	H9SW    					 
2002031900073	20020319	00073	SW  	2002	3	19	HEEA078025       	1	20020222	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										STARTER HAS A DEAD SPOT.						2	G	7	2 	4U			 	H10SW   					 
2002031900075	20020319	00075	SW  	2002	3	19	HEEA078026       	1	20020225	G	3246	206053184122	SKID            			BELL  	407   	407         	1182206	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										UPON INSPECTION FOUND PRIMER COULD BE SEEN THROUGH WHITE PAINT ON THE MAJORITY OF TUBE.						1	G	7	1 	3U			O	H2SW    					 
2002031900077	20020319	00077	SW  	2002	3	19	HEEA078027       	1	20020225	G	2841	407375006101	INDICATOR       			BELL  	407   	407         	1182206	SW  										FUEL QTY	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				FUEL QUANTITY INDICATOR LEDS DO NOT LIGHT UP.						1	G	7	1 	3U			O	H2SW    					 
2002031900079	20020319	00079	SW  	2002	3	19	HEEA078029       	1	20020225	G	6300	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH	2771 				53393				MAIN ROTOR LEVER ASSY IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002031900080	20020319	00080	SW  	2002	3	19	HEEA078030       	1	20020225	G	7714	407375008101	INDICATOR       			BELL  	407   	407         	1182206	SW  										DUAL TACH	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH					53396				N2 DUAL TACH WORKING INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW    					 
2002031900081	20020319	00081	SW  	2002	3	19	HEEA078031       	1	20020225	G	7714		NEEDLE          			BELL  	407   	407         	1182206	SW  										DUAL TACH	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH				0062	53209				"T" NEEDLE STICKS AT APPROX. 35 PERCENT.						1	G	7	1 	3U			O	H2SW    					 
2002031900082	20020319	00082	SW  	2002	3	19	HEEA078032       	1	20020225	G	6220		SPRING          			BELL  	407   	407         	1182206	SW  										FRAHM ASSY	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH				LK75	53461				FRAHM ASSY HAS A BROKEN SPRING.						1	G	7	1 	3U			O	H2SW    					 
2002031900083	20020319	00083	SW  	2002	3	19	HEEA078033       	1	20020225	G	6230	406010401117	SUPPORT         			BELL  	407   	407         	1182206	SW  										SWASHPLATE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH	316  				53393				UPPER GREASE SEAL LEAKING GREASE ONTO UNIBALL.						1	G	7	1 	3U			O	H2SW    					 
2002031900084	20020319	00084	SW  	2002	3	19	HEEA078034       	1	20020225	G	6340	407375001105	INDICATOR       			BELL  	407   	407         	1182206	SW  										MGB TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				MAIN ROTOR GEARBOX TACH IS INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2002031900085	20020319	00085	SW  	2002	3	19	HEEA078035       	1	20020225	G	7714	407375002103	INDICATOR       			BELL  	407   	407         	1182206	SW  										ENG NG	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				ENGINE NG TACH INTERNAL LIGHTING EXTREMELY DIM.  DIFFICULT TO READ.						1	G	7	1 	3U			O	H2SW    					 
2002031900086	20020319	00086	SW  	2002	3	19	HEEA078036       	1	20020225	G	6320	407375005101	INDICATOR       			BELL  	407   	407         	1182206	SW  										G/B OIL TEMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				INTERNAL LIGHT IS TOO WEAK.						1	G	7	1 	3U			O	H2SW    					 
2002031900087	20020319	00087	SW  	2002	3	19	HEEA078037       	1	20020225	G	6230	407040011101	MAST            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	491PH	1831 				53386				MAIN ROTOR MAST IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002031900088	20020319	00088	SW  	2002	3	19	HEEA078038       	1	20020225	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	491PH	1829 				53386				SWASHPLATE GREASE LEAKING FROM UPPER SEAL.						1	G	7	1 	3U			O	H2SW    					 
2002031900089	20020319	00089	SW  	2002	3	19	HEEA078039       	1	20020225	G	6320	407040006107	TRANSMISSION    			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH	2677 				53278				MAIN ROTOR GEARBOX TRANSMISSION HAS CORROSION ON SPLIT LINE.						1	G	7	1 	3U			O	H2SW    					 
2002031900090	20020319	00090	SW  	2002	3	19	HEEA078040       	1	20020225	G	6230	406010428109	BUSHING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	2646 				53159				MAIN ROTOR HUB BUSHINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002031900092	20020319	00092	SW  	2002	3	19	HEEA078042       	1	20020225	G	6230	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	1046 				53159				MAIN ROTOR LEVER ASSY IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002031900093	20020319	00093	SW  	2002	3	19	HEEA078043       	1	20020225	G	6230	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	1046 				53159				MAIN ROTOR LEVER WORN.						1	G	7	1 	3U			O	H2SW    					 
2002031900094	20020319	00094	SW  	2002	3	19	HEEA078045       	1	20020226	G	6710	406310404101	ROD END         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH	2036 				53396				MAIN ROTOR ROD END IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002031900096	20020319	00096	SW  	2002	3	19	HEEA078046       	1	20020226	G	2497	407375012101	CONNECTOR       			BELL  	407   	407         	1182206	SW  										ECU	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				FACE ON THE CONNECTOR THAT ATTACHES TO THE ECU IS SCARRED NEAR PINS.						1	G	7	1 	3U			O	H2SW    					 
2002031900098	20020319	00098	SW  	2002	3	19	HEEA078047       	1	20020226	G	6300	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				MAIN ROTOR OIL COOLER BLOWER BEARING GREASE TURNED BLACK.						1	G	7	1 	3U			O	H2SW    					 
2002031900099	20020319	00099	SW  	2002	3	19	HEEA078048       	1	20020226	G	6720	406012129101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				TAIL ROTOR LINK HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002031900112	20020319	00112	SW  	2002	3	19	HEEA078049       	1	20020226	G	6710	PM212302	SWITCH          			BELL  	407   	407         	1182206	SW  										CYCLIC SWITCH	BROKEN          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	493PH					53393				CYCLIC STICK SWITCH IS BROKEN.						1	G	7	1 	3U			O	H2SW    					 
2002031900115	20020319	00115	SW  	2002	3	19	HEEA078050       	1	20020226	G	3340	MS2774318	RELAY           			BELL  	407   	407         	1182206	SW  										EXTERNAL LIGHTS	STUCK           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	495PH					53397				RELAY INTERNAL CONTACTS STUCK SHUT.						1	G	7	1 	3U			O	H2SW    					 
2002031900123	20020319	00123	SW  	2002	3	19	HEEA078051       	1	20020226	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				TAIL ROTOR DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002031900124	20020319	00124	SW  	2002	3	19	HEEA078052       	1	20020226	G	3340	MS2774318	RELAY           			BELL  	407   	407         	1182206	SW  										LANDING LIGHT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				UPPER LANDING LIGHT WOULD NOT SHUT OFF. RELAY FAILED.						1	G	7	1 	3U			O	H2SW    					 
2002031900125	20020319	00125	SW  	2002	3	19	HEEA078055       	1	20020226	G	2510	407370720101	SEAT BELT       			BELL  	407   	407         	1182206	SW  										COCKPIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				SEAT BELT WORN. PART NUMBER TAG MISSING.  HARDWARE RUSTING.						1	G	7	1 	3U			O	H2SW    					 
2002031900127	20020319	00127	SW  	2002	3	19	HEEA078056       	1	20020226	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				LOW LEVEL CAUTION LIGHT WOULD NOT EXTINGUISH.						1	G	7	1 	3U			O	H2SW    					 
2002031900129	20020319	00129	SW  	2002	3	19	HEEA078057       	1	20020226	G	7921	407062021101	DUCT            			BELL  	407   	407         	1182206	SW  										OIL COOLER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				ENGINE OIL COOLER DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002031900131	20020319	00131	SW  	2002	3	19	HEEA078058       	1	20020226	G	6300	407340339103	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				BEARING HAS DETERIORATED RUBBER.						1	G	7	1 	3U			O	H2SW    					 
2002031900133	20020319	00133	SW  	2002	3	19	HEEA078059       	1	20020226	G	3212	206050247132	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				VELCRO UNSEWN FROM COVER.						1	G	7	1 	3U			O	H2SW    					 
2002031900136	20020319	00136	SW  	2002	3	19	HEEA078061       	1	20020226	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										IDLER GEAR	FROZEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				IDLER GEAR BEARING FROZEN.						1	G	7	1 	3U			O	H2SW    					 
2002031900140	20020319	00140	SW  	2002	3	19	HEEA078062       	1	20020226	G	6220		BEARING         			BELL  	407   	407         	1182206	SW  										BELLCRANK	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	2074 			TE219	53003				BELLCRANK BUFFER UNBONDED.						1	G	7	1 	3U			O	H2SW    					 
2002031900145	20020319	00145	SW  	2002	3	19	HEEA078063       	1	20020226	G	6730	206001556001	LINK            			BELL  	407   	407         	1182206	SW  										ROTOR SERVO	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				LINK BEARING RATCHETY.						1	G	7	1 	3U			O	H2SW    					 
2002031900146	20020319	00146	SW  	2002	3	19	HEEA078064       	1	20020226	G	3212	206050247135	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				EMERGENCY FLOAT COVER IS TORN.						1	G	7	1 	3U			O	H2SW    					 
2002031900147	20020319	00147	SW  	2002	3	19	HEEA078066       	1	20020226	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				COOLER BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002031900148	20020319	00148	SW  	2002	3	19	HEEA078067       	1	20020226	G	6720	406012129101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2002031900150	20020319	00150	SW  	2002	3	19	HEEA078069       	1	20020226	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				PRESSURE GAUGE FACE IS  LOOSE.						1	G	7	1 	3U			O	H2SW    					 
2002032000001	20020320	00001	GL  	2002	3	20	HEEA078070       	2	20020226	G	7320	412074101101	TRANSDUCER      			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				TRANSDUCER CAUSES ENGINE DECELERATION ON TAKE OFF.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032000002	20020320	00002	SW  	2002	3	20	HEEA078071       	1	20020226	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				FUEL SYSTEM PRESSURE SWITCH IS INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2002032000003	20020320	00003	SW  	2002	3	20	HEEA078072       	1	20020226	G	3212	206050247135	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				VELCRO COMING UNSEWN FROM END FLAPS OF EMERGENCY FLOAT COVER.						1	G	7	1 	3U			O	H2SW    					 
2002032000004	20020320	00004	SW  	2002	3	20	HEEA078073       	1	20020226	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL INDICATOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				SWITCH STICKING.						1	G	7	1 	3U			O	H2SW    					 
2002032000005	20020320	00005	SW  	2002	3	20	HEEA078074       	1	20020226	G	6710	406310404101	ROD END         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	4159 				53198				ROD END ON MAIN ROTOR IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032000006	20020320	00006	SW  	2002	3	20	HEEA078075       	1	20020226	G	6710	406310404101	ROD END         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				ROD END ON MAIN ROTOR IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032000007	20020320	00007	SW  	2002	3	20	HEEA078076       	1	20020226	G	6710	406310404101	ROD END         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	4159 				53198				ROD END ON MAIN ROTOR IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032000008	20020320	00008	SW  	2002	3	20	HEEA078077       	1	20020226	G	6710	406310404101	ROD END         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	1269 				53198				ROD END ON MAIN ROTOR IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032000009	20020320	00009	SW  	2002	3	20	HEEA078078       	1	20020226	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	STUCK           	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	498PH					53399				STICKING LIGHT STAYS ON WITH FULLTAN.						1	G	7	1 	3U			O	H2SW    					 
2002032000010	20020320	00010	SW  	2002	3	20	HEEA078079       	1	20020226	G	6710		SPRING          			BELL  	407   	407         	1182206	SW  										SWITCH	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH					53461				WILL NOT KEY RADIUS.  BROKEN SPRING.						1	G	7	1 	3U			O	H2SW    					 
2002032000011	20020320	00011	SW  	2002	3	20	HEEA078080       	1	20020226	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	1182206	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				ENGINE EXHAUST STACK IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032000013	20020320	00013	SW  	2002	3	20	HEEA078081       	1	20020226	G	6320	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				COOLER BLOWER BEARING FEELS ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002032000014	20020320	00014	SW  	2002	3	20	HEEA078082       	1	20020226	G	2822	1C2710	CARTRIDGE       			BELL  	407   	407         	1182206	SW  										FUEL PUMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				FUEL PUMP CARTRIDGE IS INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2002032000015	20020320	00015	SW  	2002	3	20	HEEA078083       	1	20020226	G	3212	8226003	FUSEABLE PLUG   			BELL  	407   	407         	1182206	SW  										FLOAT	LEAKING         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				EMERGENCY FLOAT FUSEABLE PLUG IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032000017	20020320	00017	SW  	2002	3	20	HEEA078087       	1	20020226	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	741PH					53457				SWITCH FOR LOW LEVEL LIGHT STAYS ON.						1	G	7	1 	3U			O	H2SW    					 
2002032000019	20020320	00019	SW  	2002	3	20	HEEA078088       	1	20020226	G	6300	406010417101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				MAIN ROTOR BEARING IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032000022	20020320	00022	SW  	2002	3	20	HEEA078089       	1	20020226	G	2510	222320823130	SEAT BELT       			BELL  	407   	407         	1182206	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				COCKPIT SEAT BELT IS FRAYED.						1	G	7	1 	3U			O	H2SW    					 
2002032000023	20020320	00023	SW  	2002	3	20	HEEA078090       	1	20020226	G	6320	206040156001	SEAL            			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	720PH					53277				MAIN ROTOR GEARBOX SEAL IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032000024	20020320	00024	SW  	2002	3	20	HEEA078092       	1	20020226	G	2820	465C63TW	VALVE           			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	406PH					53198				FUEL SYSTEM IS SEEPING FROM VALVE ASSY.						1	G	7	1 	3U			O	H2SW    					 
2002032000025	20020320	00025	SW  	2002	3	20	HEEA078097       	1	20020226	G	6310	204040760109	FILTER ELEMENT  			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH					53461				MAIN ROTOR GEARBOX FILTER CAUSING CHIP LIGHT TO ILLUMINATE.						1	G	7	1 	3U			O	H2SW    					 
2002032000026	20020320	00026	SW  	2002	3	20	HEEA078099       	1	20020226	G	6520	406040072105	SPLINE ADAPTER  			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				TAIL ROTOR SPLINE ADAPTER SHAFT ASSY WORN.  SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2002032000028	20020320	00028	SW  	2002	3	20	HEEA078101       	1	20020227	G	2435	206062200123	STARTER GEN     			BELL  	407   	407         	1182206	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	402PH					53159				STARTER GEN FAILED 300 HOUR INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2002032000031	20020320	00031	SW  	2002	3	20	HEEA078103       	1	20020227	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH	1834 			99333	53327				STARTER GEN HAS WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2002032000032	20020320	00032	SW  	2002	3	20	HEEA078104       	1	20020227	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH	2927 			95175	53378				STARTER GEN HAS WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2002032000034	20020320	00034	SW  	2002	3	20	HEEA078106       	1	20020301	G	3212	407350300101	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	721PH	3067 				53278				EMERGENCY FLOAT IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032000036	20020320	00036	SW  	2002	3	20	HEEA078107       	1	20020301	G	6510	407040325101	SHAFT           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	PEELING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				PAINT PEELING OFF TAIL ROTOR DRIVE SHAFT.						1	G	7	1 	3U			O	H2SW    					 
2002032000039	20020320	00039	SW  	2002	3	20	HEEA078108       	1	20020301	G	6510	406360500101	COOLER          			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	LEAKING         	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	490PH					53378				TAIL ROTOR DRIVE SHAFT COOLER HAS A SLOW LEAK ON ENGINE COOLER SIDE.						1	G	7	1 	3U			O	H2SW    					 
2002032000044	20020320	00044	SW  	2002	3	20	HEEA078109       	1	20020301	G	2822	1C2710	CARTRIDGE       			BELL  	407   	407         	1182206	SW  										FUEL BOOST	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				BOOST PUMP CARTRIDGE IS INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2002032000046	20020320	00046	SW  	2002	3	20	HEEA078110       	1	20020301	G	6520	406040400119	GEARBOX         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH	1000 				53435				TAIL ROTOR GEARBOX HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2002032000051	20020320	00051	SW  	2002	3	20	HEEA078116       	1	20020301	G	6220	407010150103	FRAHM           			BELL  	407   	407         	1182206	SW  										M/R HEAD	VIBRATION       	E			HEEA	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	03	404PH					53188				FRAHM ASSY CAUSING HIGH 4 REV.						1	G	7	1 	3U			O	H2SW    					 
2002032000053	20020320	00053	SW  	2002	3	20	HEEA078118       	1	20020301	G	6710	206062721105	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										MAIN ROTOR ACTUATOR WILL NOT MOVE WITH POWER APPLIED.						1	G	7	1 	3U			 	H2SW    					 
2002032000055	20020320	00055		2002	3	20	HEEA078119       	4	20020301	G	2210	574074264001	CONTROLLER      			BELL  	214   	214ST       	1182106	SW  										ALTITUDE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										AIRCRAFT WILL NOT HOLD ALTITUDE. ALTITUDE CONTROLLER MALFUNCTIONED.						2	G	7	2 	4U			 	H10SW   					 
2002032000059	20020320	00059	SW  	2002	3	20	HEEA078120       	1	20020301	G	6510	206040339103	BEARING         			BELL  	206   	206L3       	1182108	SW  										COOLER HANGER	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										TAIL ROTOR DRIVE SHAFT COOLER HANGER BEARING FAILED.						1	G	7	1 	3U			 	H2SW    					 
2002032000061	20020320	00061	SW  	2002	3	20	HEEA078121       	1	20020301	G	6510	407040316101	FLYWHEEL        			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				TAIL ROTOR FLYWHEEL HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2002032000062	20020320	00062	SW  	2002	3	20	HEEA078122       	1	20020301	G	6710	407001523101	IDLER ASSY      			BELL  	407   	407         	1182206	SW  										M/R CONTROL	WORN            	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				MAIN ROTOR IDLER ASSY HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002032000063	20020320	00063	SW  	2002	3	20	HEEA078123       	1	20020301	G	6720	406012129101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH					53399				MAIN ROTOR LINK HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002032000065	20020320	00065	SW  	2002	3	20	HEEA078125       	1	20020301	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH					53327				ENGINE MOUNT BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032000066	20020320	00066	SW  	2002	3	20	HEEA078126       	1	20020301	G	3242	D01631	PAD             			BELL  	407   	407         	1182206	SW  										BRAKE	FLAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	719PH					53266				BRAKE PAD IS FLAKING,  CAUSED BY VIBRATION.						1	G	7	1 	3U			O	H2SW    					 
2002032000068	20020320	00068	SW  	2002	3	20	HEEA078127       	1	20020301	G	6330	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				LEVER HAS WEAR.						1	G	7	1 	3U			O	H2SW    					 
2002032000070	20020320	00070	SW  	2002	3	20	HEEA078128       	1	20020301	G	3212	206050247135	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				EMERGENCY FLOAT COVER HAS TORN STITCHING.						1	G	7	1 	3U			O	H2SW    					 
2002032000072	20020320	00072	SW  	2002	3	20	HEEA078129       	1	20020301	G	6220		BEARING         			BELL  	407   	407         	1182206	SW  										BELLCRANK	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH	2074 			TI473	53003				PIVOT BEARING IS WORN BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032000075	20020320	00075	SW  	2002	3	20	HEEA078132       	1	20020301	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				CORROSION INSIDE OF FLOAT PRESSURE GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2002032000077	20020320	00077	SW  	2002	3	20	HEEA078133       	1	20020301	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	510PH					53209				MALFUNCTIONING SWITCH IS CAUSING LIGHT NOT TO GO OUT.						1	G	7	1 	3U			O	H2SW    					 
2002032000079	20020320	00079	SW  	2002	3	20	HEEA078134       	1	20020301	G	6420		BEARING         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				WORN TAIL ROTOR BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002032000080	20020320	00080	SW  	2002	3	20	HEEA078135       	1	20020301	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				TAIL ROTOR DRIVE DISC PACK IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032000082	20020320	00082	SW  	2002	3	20	HEEA078136       	1	20020301	G	6310	406040548101	CONE SET        			BELL  	407   	407         	1182206	SW  										FREEWHEEL UNIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				FREEWHEEL UNIT CONE SET IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032000085	20020320	00085	SW  	2002	3	20	HEEA078137       	1	20020301	G	6710	206001396001	SHAFT           			BELL  	407   	407         	1182206	SW  										CYCLIC STICK	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				UNABLE TO ADJUST FRICTION ROD ON CYCLIC STICK SHAFT.						1	G	7	1 	3U			O	H2SW    					 
2002032000086	20020320	00086	SW  	2002	3	20	HEEA078138       	1	20020301	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				TAIL ROTOR DISC PACK IS CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032000089	20020320	00089	SW  	2002	3	20	HEEA078139       	1	20020301	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH	1766 				53288				MAIN ROTOR UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032000093	20020320	00093	SW  	2002	3	20	HEEA078140       	1	20020301	G	6220	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				MAIN ROTOR MOUNT HAS RUBBER SEPARATION.						1	G	7	1 	3U			O	H2SW    					 
2002032000095	20020320	00095	SW  	2002	3	20	HEEA078141       	1	20020301	G	7931	222375077113	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										OIL PRESSURE	FLUCTUATES      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	501PH					53401				OIL PRESSURE TRANSMITTER FLUCTUATING.						1	G	7	1 	3U			O	H2SW    					 
2002032000109	20020320	00109	SW  	2002	3	20	HEEA078142       	1	20020301	G	3212	70079H100F210	HOSE            			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH					53461				EMERGENCY FLOAT HOSE CHAFED.						1	G	7	1 	3U			O	H2SW    					 
2002032000110	20020320	00110	SW  	2002	3	20	HEEA078143       	1	20020301	G	6720		BEARING         			BELL  	407   	407         	1182206	SW  										LINK	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				LINK BEARING HAS WEAR AND CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002032000111	20020320	00111	SW  	2002	3	20	HEEA078144       	1	20020301	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         	1182206	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				INTERMITTENT FADEC FAULTS ON START.						1	G	7	1 	3U			O	H2SW    					 
2002032000123	20020320	00123	SW  	2002	3	20	HEEA078147       	1	20020301	G	7120	407064105102	TUBE            			BELL  	407   	407         	1182206	SW  										ENGINE MOUNT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				ENGINE MOUNT TUBE DAMAGED BEYOND LIMITS.  TUBE WAS FULL OF WATER UPON REMOVAL FROM AIRCRAFT.						1	G	7	1 	3U			O	H2SW    					 
2002032000124	20020320	00124	SW  	2002	3	20	HEEA078148       	1	20020301	G	5210	3161201	HANDLE          			BELL  	407   	407         	1182206	SW  										CREW DOOR	BENT            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				HANDLE ARM IS BENT.						1	G	7	1 	3U			O	H2SW    					 
2002032000125	20020320	00125	SW  	2002	3	20	HEEA078149       	1	20020301	G	5210	407030601103	DOOR            			BELL  	407   	407         	1182206	SW  										CREW DOOR	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				DOOR WAS LOOSE ON IT'S HINGES.						1	G	7	1 	3U			O	H2SW    					 
2002032000126	20020320	00126	SW  	2002	3	20	HEEA078150       	1	20020301	G	5210	407030601105	DOOR            			BELL  	407   	407         	1182206	SW  										CREW	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				DOOR WAS LOOSE ON IT'S HINGES.						1	G	7	1 	3U			O	H2SW    					 
2002032000127	20020320	00127	SW  	2002	3	20	HEEA078153       	1	20020301	G	3200	400052007109	BEAM            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				MOUNT HARDWARE FROZEN IN BEAM ASSY.  FOUND INNER BUSHING FACE CORRODED BEYOND LIMITS.  SENDING FOR AN EVALUATION DUE TO 	NO PREVENTIVE MAINT ON MFG PART.					1	G	7	1 	3U			O	H2SW    					 
2002032000128	20020320	00128	SW  	2002	3	20	HEEA078154       	1	20020301	G	6710	406310404101	ROD END         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X	3464 				53267				ROD END WORN BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032000129	20020320	00129	SW  	2002	3	20	HEEA078157       	1	20020301	G	3212	206050247137	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				EMERGENCY FLOAT COVER HAS WORN STITCHING ON END CAPS.						1	G	7	1 	3U			O	H2SW    					 
2002032000131	20020320	00131	SW  	2002	3	20	HEEA078158       	1	20020301	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				EMERGENCY FLOAT COVER HAS WORN STITCHING ON END CAPS.						1	G	7	1 	3U			O	H2SW    					 
2002032000133	20020320	00133	SW  	2002	3	20	HEEA078159       	1	20020301	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH					53461				TAIL ROTOR DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032000136	20020320	00136	SW  	2002	3	20	HEEA078160       	1	20020301	G	5321	407030713103	FLOOR PANEL     			BELL  	407   	407         	1182206	SW  										CARGO BAY	SEPARATED       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				FLOOR PANEL SEPARATED BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032000141	20020320	00141	SW  	2002	3	20	HEEA078161       	1	20020301	G	6230	406010427109	GIMBAL RING     			BELL  	407   	407         	1182206	SW  										SWASHPLATE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH	2791 				53147				SWASHPLATE GIMBAL RING CORRODED AROUND BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002032000143	20020320	00143	SW  	2002	3	20	HEEA078162       	1	20020301	G	6310	406040550101	ADAPTER         			BELL  	407   	407         	1182206	SW  										TRANSMISSION	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH					53461				TRANSMISSION ADAPTER HAS A WORN WEAR SLEEVE. OUT OF LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032000144	20020320	00144	SW  	2002	3	20	HEEA078163       	1	20020301	G	6310	406040500119	SEAL            			BELL  	407   	407         	1182206	SW  										SUPPORT	LEAKING         	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH					53461				SUPPORT SEAL IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032000148	20020320	00148	SW  	2002	3	20	HEEA078164       	1	20020301	G	6300	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				COOLER BLOWER BEARING ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002032000150	20020320	00150	SW  	2002	3	20	HEEA078165       	1	20020301	G	6310	407060111101	BEARING         			BELL  	407   	407         	1182206	SW  										MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				MAIN ROTOR MOUNT HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002032000151	20020320	00151	SW  	2002	3	20	HEEA078166       	1	20020301	G	6310	406040516101	SHAFT           			BELL  	407   	407         	1182206	SW  										FREEWHEEL UNIT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH				A4845	53386				MAIN ROTOR FREEWHEEL UNIT SHAFT HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2002032100001	20020321	00001		2002	3	21	HEEA078171       	4	20020307	G	2210	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										ELEVATOR	MALFUNCTIONED   	E				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	03										ELEVATOR ACTUATOR OCCASSIONALLY KICKS OFF LINE ON TAKE OFF AND LANDING.						2	G	7	2 	4U			 	H10SW   					 
2002032100002	20020321	00002		2002	3	21	HEEA078172       	4	20020307	G	2210	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										ELEVATOR	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										OPPOSITE ELEVATOR SYSTEM WOULD NOT MONITOR TEST.						2	G	7	2 	4U			 	H10SW   					 
2002032100003	20020321	00003	SW  	2002	3	21	HEEA078173       	1	20020307	G	6320	407375001105	INDICATOR       			BELL  	407   	407         	1182206	SW  										MGT	READS LOW       	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	742PH					53461				MGT INDICATOR INDICATES 10 DEGREES LOW.						1	G	7	1 	3U			O	H2SW    					 
2002032100004	20020321	00004	SW  	2002	3	21	HEEA078174       	1	20020307	G	6320	406340100101	PUMP            			BELL  	407   	407         	1182206	SW  										TRANSMISSION	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	8595X					53267				EXCESSIVE LEAKAGE ON TRANSMISSION DECK.						1	G	7	1 	3U			O	H2SW    					 
2002032100005	20020321	00005	SW  	2002	3	21	HEEA078175       	1	20020307	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										ENG TORQUE	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	719PH					53266				TORQUE INDICATOR WORKS INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW    					 
2002032100006	20020321	00006	SW  	2002	3	21	HEEA078176       	1	20020307	G	6510	206340300105	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	SCRATCHED       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH	842  				53400				TAIL ROTOR DRIVE SHAFT SCRATCHED.						1	G	7	1 	3U			O	H2SW    					 
2002032100007	20020321	00007	SW  	2002	3	21	HEEA078177       	1	20020307	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH	2821 				53283				ROTOR BRAKE HAS EXCESSIVE HOUSING WEAR.						1	G	7	1 	3U			O	H2SW    					 
2002032100008	20020321	00008	SW  	2002	3	21	HEEA078178       	1	20020307	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH	4941 				53114				MAIN ROTOR BRAKE HAS EXCESSIVE HOUSING WEAR.						1	G	7	1 	3U			O	H2SW    					 
2002032100009	20020321	00009	SW  	2002	3	21	HEEA078179       	1	20020311	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	740PH	977  				53435				MAIN ROTOR UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032100010	20020321	00010	SW  	2002	3	21	HEEA078180       	1	20020311	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH	1818 				53390				MAIN ROTOR UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032100011	20020321	00011	SW  	2002	3	21	HEEA078181       	1	20020311	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404PH	1267 				53188				MAIN ROTOR UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032100012	20020321	00012	SW  	2002	3	21	HEEA078182       	1	20020311	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X	1796 				53267				MAIN ROTOR UNIVERAL IS WORN AND HAS A DEAD SPOT IN THE BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002032100014	20020321	00014	SW  	2002	3	21	HEEA078183       	1	20020311	G	2820	206064520103	LINE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				FUEL SYSTEM LINE HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002032100015	20020321	00015	SW  	2002	3	21	HEEA078184       	1	20020311	G	6230	406010427109	GIMBAL RING     			BELL  	407   	407         	1182206	SW  										SWASHPLATE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH	1718 				53209				SWASHPLATE GIMBLE RING IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032100016	20020321	00016	SW  	2002	3	21	HEEA078185       	1	20020311	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				TAIL ROTOR DISC PACK IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032100017	20020321	00017	SW  	2002	3	21	HEEA078186       	1	20020311	G	6220	406310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	SEPARATED       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				MAIN ROTOR HEAD MOUNT HAS SEPARATION.						1	G	7	1 	3U			O	H2SW    					 
2002032100018	20020321	00018	SW  	2002	3	21	HEEA078187       	1	20020311	G	6220	406012129101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				MAIN ROTOR HEAD LINK HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002032100019	20020321	00019	SW  	2002	3	21	HEEA078188       	1	20020311	G	6220	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DEBONDED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				MAIN ROTOR HEAD MOUNT RUBBER IS DEBONDING.						1	G	7	1 	3U			O	H2SW    					 
2002032100020	20020321	00020	SW  	2002	3	21	HEEA078189       	1	20020311	G	6220	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				MAIN ROTOR HEAD MOUNT RUBBER IS DEBONDING.						1	G	7	1 	3U			O	H2SW    					 
2002032100027	20020321	00027	SW  	2002	3	21	HEEA078196       	1	20020311	G	7714	407375002103	INDICATOR       			BELL  	407   	407         	1182206	SW  										NG	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				INDICATOR BLINKS OFF.						1	G	7	1 	3U			O	H2SW    					 
2002032100028	20020321	00028	SW  	2002	3	21	HEEA078197       	1	20020311	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8595X					53267				TORQUE INDICATOR LIGHTING IS DIM.						1	G	7	1 	3U			O	H2SW    					 
2002032100029	20020321	00029	SW  	2002	3	21	HEEA078198       	1	20020311	G	3212	407350301101	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	612PH					53199				EMERGENCY FLOAT BAG LEAKING ON SIX MONTH INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2002032100030	20020321	00030	SW  	2002	3	21	HEEA078199       	1	20020311	G	6310	406040500127FM	FREEWHEEL UNIT  			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	8595X	4599 				53267				MAIN ROTOR FREEWHEEL UNIT LEAKING AT FORWARD AND AFT SEALS.						1	G	7	1 	3U			O	H2SW    					 
2002032100031	20020321	00031	SW  	2002	3	21	HEEA078200       	1	20020311	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				EMERGENCY FLOAT PRESSURE GAUGE STICKING.						1	G	7	1 	3U			O	H2SW    					 
2002032100032	20020321	00032	SW  	2002	3	21	HEEA078201       	1	20020311	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				TAIL ROTOR LINK HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002032100033	20020321	00033	SW  	2002	3	21	HEEA078202       	1	20020311	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	2426 				53199				MAIN ROTOR BRAKE HAS EXCESSIVE HOUSING WEAR.						1	G	7	1 	3U			O	H2SW    					 
2002032100034	20020321	00034	SW  	2002	3	21	HEEA078203       	1	20020311	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	1603 				53003				MAIN ROTOR BRAKE HAS  EXCESSIVE PISTON WEAR IN HOUSING.						1	G	7	1 	3U			O	H2SW    					 
2002032100035	20020321	00035	SW  	2002	3	21	HEEA078204       	1	20020311	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH	1962 				53288				MAIN ROTOR BRAKE HAS EXCESSIVE PISTON WEAR IN HOUSING.						1	G	7	1 	3U			O	H2SW    					 
2002032100036	20020321	00036	SW  	2002	3	21	HEEA078205       	1	20020311	G	6710	406010417101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				MAIN ROTOR BEARING IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032100037	20020321	00037	SW  	2002	3	21	HEEA078206       	1	20020311	G	6520	406040453101	SEAL            			BELL  	407   	407         	1182206	SW  										T/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	407PH					53003				TAIL ROTOR GEARBOX IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032100038	20020321	00038	SW  	2002	3	21	HEEA078207       	1	20020311	G	7931	222375077113	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										ENGINE OIL	FLUCTUATES      	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	496PH					53398				ENGINE OIL PRESSURE TRANSMITTER IS FLUCTUATING.						1	G	7	1 	3U			O	H2SW    					 
2002032100039	20020321	00039	SW  	2002	3	21	HEEA078208       	1	20020311	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH	2740 				53277				MAIN ROTOR BRAKE HAS EXCESSIVE PISTON WEAR IN HOUSING.						1	G	7	1 	3U			O	H2SW    					 
2002032100040	20020321	00040	SW  	2002	3	21	HEEA078209       	1	20020311	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				TAIL ROTOR LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2002032100041	20020321	00041	SW  	2002	3	21	HEEA078210       	1	20020311	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				ENGINE MOUNT HAS MECHANICAL DAMAGE ON ONE LEG BEYOND MAINTENANCE MANUAL LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032100042	20020321	00042	SW  	2002	3	21	HEEA078211       	1	20020311	G	6210	406010120101	BOLT            			BELL  	407   	407         	1182206	SW  										M/R BLADE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				MAIN ROTOR BLADE BOLTS HAS PLATING MISSING AT LOWER END OF BOLT SHANK.						1	G	7	1 	3U			O	H2SW    					 
2002032100043	20020321	00043	SW  	2002	3	21	HEEA078212       	1	20020311	G	7712	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										TORQUE	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	719PH					53266				TORQUE INDICATION INTERMITTENT.						1	G	7	1 	3U			O	H2SW    					 
2002032100044	20020321	00044	SW  	2002	3	21	HEEA078213       	1	20020311	G	7810	407062021101	DUCT            			BELL  	407   	407         	1182206	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				EXHAUST DUCT IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032100045	20020321	00045	SW  	2002	3	21	HEEA078214       	1	20020311	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				TAIL ROTOR COOLER BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032100046	20020321	00046	SW  	2002	3	21	HEEA078215       	1	20020311	G	3212	206050247131	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				EMERGENCY FLOAT COVER HAS FORWARD END FLAP WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032100047	20020321	00047	SW  	2002	3	21	HEEA078216       	1	20020311	G	6310	407340102101	SEAL            			BELL  	407   	407         	1182206	SW  										TRANSMISSION	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	491PH					53386				TRANSMISSION SEAL IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032100048	20020321	00048	SW  	2002	3	21	HEEA078217       	1	20020311	G	6320	214040806003	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				MAIN ROTOR GEARBOX PRESSURE SWITCH HAS NO LIGHT INDICATION ON RUN UP.						1	G	7	1 	3U			O	H2SW    					 
2002032100049	20020321	00049		2002	3	21	HEEA078222       	4	20020228	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	INACCURATE      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				CLOCK GAINS 5 TO 10 MINUTES AN HOUR.						1	G	7	1 	3U			 	H9EU    					 
2002032100050	20020321	00050	EU  	2002	3	21	HEEA078223       	1	20020228	G	6420	350A33214501	PITCH CONTROL   			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	CRACKED         	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4031L					2907				CRACKED BUSHINGS AT ELASTOMERIC END.						1	G	7	1 	3U			 	H9EU    					 
2002032100051	20020321	00051	EU  	2002	3	21	HEEA078224       	1	20020228	G	6420	350A33214501	PITCH CONTROL   			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				TAIL ROTOR PITCH CONTROL ROD HAS BEARING WEAR.						1	G	7	1 	3U			 	H9EU    					 
2002032100052	20020321	00052	EU  	2002	3	21	HEEA078225       	1	20020228	G	6322	9696	MOTOR           			SNIAS 	350   	AS350B      	8680801	EU  										COOLER BLOWER	SEIZED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	855PH					3351				COOLER BLOWER MOTOR HAS IT`S BEARINGS FROZEN.						1	G	7	1 	3U			 	H9EU    					 
2002032100053	20020321	00053		2002	3	21	HEEA078226       	4	20020228	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	INACCURATE      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				CLOCK DOES NOT KEEP PROPER TIME.						1	G	7	1 	3U			 	H9EU    					 
2002032100054	20020321	00054	EU  	2002	3	21	HEEA078227       	1	20020228	G	7931	642790041	TRANSMITTER     			SNIAS 	350   	AS350B      	8680801	EU  										OIL PRESSURE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	975AE					2777				OIL PRESSURE INDICATOR SHOWS NO PRESSURE ON ENGINE START. REPLACED THE OIL PRESSURE TRANSMITTER.						1	G	7	1 	3U			 	H9EU    					 
2002032100056	20020321	00056	EU  	2002	3	21	HEEA078229       	1	20020307	G	6220	350A31191600	STARFLEX        			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	970AE	226  				3235				CRACK IN THICK PART OF STARFLEX WHERE ARMS MEET.						1	G	7	1 	3U			 	H9EU    					 
2002032100057	20020321	00057	EU  	2002	3	21	HEEA078230       	1	20020307	G	6220	350A33215001	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				MAIN ROTOR HAS WORN BEARINGS.						1	G	7	1 	3U			 	H9EU    					 
2002032100058	20020321	00058	EU  	2002	3	21	HEEA078231       	1	20020307	G	7714	614764021	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										TACHOMETER	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	975AE					2777				PILOT REPORTED NR SPLITTING 8-10 RPM HIGH.						1	G	7	1 	3U			 	H9EU    					 
2002032100059	20020321	00059	EU  	2002	3	21	HEEA078232       	1	20020311	G	5243	10562582	DOOR            			BOLKMS	105   	BO105S      	5626006	EU  										HYD PACK	DEPARTED        	E			HEEA	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	03	8199J					S826				WHILE IN FLIGHT, THE HYDRAULIC PACK INSPECTION DOOR ON THE LT SIDE OF TRANSMISSION COWL DEPARTED AIRCRAFT. NO ADDITIONAL	 DAMAGE TO AIRCRAFT.  REPLACED COVER.					1	G	7	2 	3U			 	H3EU    					 
2002032500101	20020325	00101	NE  	2002	3	25	HEEA078251       	1	20020319	G	3110	RCR32G100JM	RESISTOR        			SKRSKY	S76   	S76A        	8143006	NE  										INSTRUMENT PANEL	FAILED          	E			HEEA	C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			SW	03	22342					760096				AFTER TAKEOFF, SMELLED ELECTRICAL BURNING THEN OBSERVED SMOKE COMING FROM THE INSTRUMENT PANEL.						1	G	7	2 	3U			 	H1NE    					 
2002032500103	20020325	00103	GL  	2002	3	25	HEEA078252       	2	20020322	G	7200	23063392	ENGINE          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE BAY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999	1969 				53323				FADEC FAILURE ON ENG START. TOT MAXED AT 1063 DEGREES.  RETURNED ENGINE TO ROLLS ROYCE FOR REPAIR						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032500105	20020325	00105	GL  	2002	3	25	HEEA078253       	2	20020322	G	7250	23007189	NOZZLE          			BELL  	206   	TH57A       	1180821	SW  	ALLSN 	250C  	250C18A     	03011	GL  					TURBINE SECTION	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	116					162678				TURBINE REMOVED FOR OVERHAUL.  LOW AREA FLOW 10.17 CAUSE LOW POWER ON TEST CELL.  POWER WENT FROM -5.3 TO -7.0.  OVERHAU	LED NOZZLE, INSTALLED AND POWER WENT TO -3.					1	G	7	1 	3U	3	U	 	EXPA1G71	E4CE				 
2002032500106	20020325	00106	GL  	2002	3	25	HEEA078254       	2	20020322	G	7200	23071644	ECU             			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999	2548 				53323				FADEC FAILURE ON ENG. START.  T.O.T. MAXED AT 1063 DEGREES. RETURNED TO ROLLS ROYCE						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032500107	20020325	00107	NE  	2002	3	25	HEEA078255       	1	20020322	G	3220		PROXIMITY SWITCH			SKRSKY	S76   	S76A        	8143006	NE  										MLG DOWNLOCK	OUT OF ADJUST   	E			HEEA	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	03	22342					760096				WHEN PREPARING TO LAND, GOT A NOSE GEAR UNSAFE LIGHT. MAINTENANCE ADJUSTED THE DOWN LOCK PROXIMITY SWITCH.						1	G	7	2 	3U			 	H1NE    					 
2002032500113	20020325	00113		2002	3	25	HEEA078256       	4	20020313	G	2210	214074301105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										SCAS	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										WILL NOT MONITOR TEST AND YAW DISENGAGE LIGHT TOO DIM.						2	G	7	2 	4U			 	H10SW   					 
2002032500116	20020325	00116	SW  	2002	3	25	HEEA078257       	1	20020313	G	7800	212061117001	TUBE            			BELL  	412   	412         	1182202	SW  										EXHAUST	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										EXHAUST TUBE BEARINGS WORN.						1	G	7	2 	4U			 	H4SW    					 
2002032500118	20020325	00118	SW  	2002	3	25	HEEA078258       	1	20020313	G	7800	212061117001	TUBE            			BELL  	412   	412         	1182202	SW  										EXHAUST	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										EXHAUST TUBE BEARINGS WORN.						1	G	7	2 	4U			 	H4SW    					 
2002032500120	20020325	00120	SW  	2002	3	25	HEEA078259       	1	20020314	G	3211	412050045107	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										AFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										AFT CROSSTUBE HAS CORROSION BEYOND BHT LIMITS.						1	G	7	2 	4U			 	H4SW    					 
2002032500121	20020325	00121	SW  	2002	3	25	HEEA078260       	1	20020315	G	7120	206064107103	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENG MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										LOWER BEARING WORN.  TUBE OPENING IS TOO LARGE FOR BEARING DIAMETER.  FASTENER HOLES ARE ELONGATED. PART SCRAPPED IN HOU	SE.					1	G	7	1 	3U			 	H2SW    					 
2002032500125	20020325	00125	SW  	2002	3	25	HEEA078261       	1	20020319	G	6710	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										M/R CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ELEVATOR TRIPS OFF LINE.						2	G	7	2 	4U			 	H10SW   					 
2002032500132	20020325	00132	SW  	2002	3	25	HEEA078265       	1	20020320	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	03										STARTER WILL NOT DISENGAGE.						2	G	7	2 	4U			 	H10SW   					 
2002032600001	20020326	00001	SW  	2002	3	26	HEEA078266       	1	20020321	G	3212	206373901103	SOLENOID VALVE  			BELL  	206   	206L3       	1182108	SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MLG SOLENOID VALVE LEAKING.						1	G	7	1 	3U			 	H2SW    					 
2002032600002	20020326	00002	SW  	2002	3	26	HEEA078267       	1	20020321	G	3212	1100891S	TEE FITTING     			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				PART IS CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600014	20020326	00014	SW  	2002	3	26	HEEA078272       	1	20020321	G	5311	206032308121S	FRAME           			BELL  	407   	407         	1182206	SW  										FUSELAGE	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				FRAME CRACK AT RT UPPER CORNER, BOLT HOLE.						1	G	7	1 	3U			O	H2SW    					 
2002032600015	20020326	00015	SW  	2002	3	26	HEEA078273       	1	20020321	G	3212	206050247132	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				EMERGENCY FLOAT COVER IS TORN AND DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2002032600016	20020326	00016	SW  	2002	3	26	HEEA078274       	1	20020321	G	3212	206050247137	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				EMERGENCY FLOAT COVER IS TORN AND DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2002032600017	20020326	00017	SW  	2002	3	26	HEEA078275       	1	20020321	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				EMERGENCY FLOAT COVER IS TORN AND DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2002032600018	20020326	00018	SW  	2002	3	26	HEEA078276       	1	20020321	G	6510	206061432118	INLET           			BELL  	407   	407         	1182206	SW  										COOLER HOUSING	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404PH					53188				OIL COOLER BLOWER HOUSING INLET CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600019	20020326	00019	SW  	2002	3	26	HEEA078277       	1	20020321	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	721PH	649  			Y0292	53278				FOUND WORN BRUSHES ON 300 HOUR INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2002032600020	20020326	00020	SW  	2002	3	26	HEEA078279       	1	20020321	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH	2755 			98008	53461				FAILED 300 HOUR INSPECTION (BRUSHES WORN).						1	G	7	1 	3U			O	H2SW    					 
2002032600021	20020326	00021	SW  	2002	3	26	HEEA078280       	1	20020321	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X	2597 			98084	53267				FAILED 300 HOUR INSPECTION (BRUSHES WORN).						1	G	7	1 	3U			O	H2SW    					 
2002032600022	20020326	00022	SW  	2002	3	26	HEEA078281       	1	20020321	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH				98209	53398				STARTER GEN HAS IT`S BRUSHES WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600024	20020326	00024	SW  	2002	3	26	HEEA078282       	1	20020321	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404PH	709  			99262	53188				STARTER GEN HAS WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2002032600025	20020326	00025	SW  	2002	3	26	HEEA078283       	1	20020321	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH	1289 			99318	53393				BRUSHES WORN ON STARTER GEN.						1	G	7	1 	3U			O	H2SW    					 
2002032600026	20020326	00026	SW  	2002	3	26	HEEA078286       	1	20020321	G	2820	206064263101	LINE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				FUEL LINE CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600027	20020326	00027	SW  	2002	3	26	HEEA078287       	1	20020321	G	2820	206064263101	LINE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				FUEL LINE CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600028	20020326	00028	SW  	2002	3	26	HEEA078288       	1	20020321	G	2820	206064520103	LINE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				FUEL LINE CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600029	20020326	00029	SW  	2002	3	26	HEEA078289       	1	20020321	G	7110	206064804113	COWLING         			BELL  	407   	407         	1182206	SW  										ENG NACELLE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				ENGINE COWL CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600030	20020326	00030	SW  	2002	3	26	HEEA078290       	1	20020321	G	7110	206064804113	COWLING         			BELL  	407   	407         	1182206	SW  										ENG BAY	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				ENGINE COWLING CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600031	20020326	00031	SW  	2002	3	26	HEEA078291       	1	20020321	G	5210	206064819005S	SKIN            			BELL  	407   	407         	1182206	SW  										CREW DOOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X	3264 				53267				CREW DOOR SKIN IS CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600032	20020326	00032	SW  	2002	3	26	HEEA078292       	1	20020321	G	7110	206064819006	COWLING         			BELL  	407   	407         	1182206	SW  										ENGINE BAY	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X	3261 				53267				COWLING CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600033	20020326	00033	SW  	2002	3	26	HEEA078301       	1	20020321	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH	3318 				53114				COMPLY WITH 407-11-30.  FOUND EXCESSIVE WEAR ON HOUSING OR MAIN ROTOR BRAKE.						1	G	7	1 	3U			O	H2SW    					 
2002032600050	20020326	00050	SW  	2002	3	26	HEEA078302       	1	20020321	G	2840	206362002103	CAP             			BELL  	407   	407         	1182206	SW  										FUEL CELL	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				FUEL CAP EARS CORRODED AND BROKEN OFF ALSO STICKING.						1	G	7	1 	3U			O	H2SW    					 
2002032600052	20020326	00052	SW  	2002	3	26	HEEA078303       	1	20020321	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				EMERGENCY FLOAT PRESSURE GAUGE FACEPLATE SPINS INSIDE GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2002032600057	20020326	00057	SW  	2002	3	26	HEEA078304       	1	20020321	G	3201	400052007109	BEAM            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH	2791 				53147				DISSIMILAR METAL, PITTING AROUND FAYING EDGE OF BUSHING AND BEAM ASSY.						1	G	7	1 	3U			O	H2SW    					 
2002032600058	20020326	00058	SW  	2002	3	26	HEEA078305       	1	20020321	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				SWASHPLATE HAS WORN COLLECTIVE LEVER BUSHINGS AND PINS.						1	G	7	1 	3U			O	H2SW    					 
2002032600061	20020326	00061	SW  	2002	3	26	HEEA078306       	1	20020321	G	6710	406010417101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				MAIN ROTOR BEARING UNSTAKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600062	20020326	00062	SW  	2002	3	26	HEEA078307       	1	20020321	G	6710	406010421103	SPACER          			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				MAIN ROTOR SPACER DRIVE LINKS HAVE PLAY.						1	G	7	1 	3U			O	H2SW    					 
2002032600100	20020326	00100	SW  	2002	3	26	HEEA078308       	1	20020321	G	6710		BUSHING         			BELL  	407   	407         	1182206	SW  										LEVER	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH				A2614A2627	53398				MAIN ROTOR LEVER HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002032600101	20020326	00101	SW  	2002	3	26	HEEA078309       	1	20020321	G	6710	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				MAIN ROTOR LINK WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600102	20020326	00102	SW  	2002	3	26	HEEA078310       	1	20020321	G	6230	406010428109	BUSHING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				MAIN ROTOR BUSHING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600103	20020326	00103	SW  	2002	3	26	HEEA078311       	1	20020321	G	6321	406010429101	PIN             			BELL  	407   	407         	1182206	SW  										DRIVE LINK	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				DRIVE LINK PIN HAS PLAY.						1	G	7	1 	3U			O	H2SW    					 
2002032600104	20020326	00104	SW  	2002	3	26	HEEA078312       	1	20020321	G	6230	406010432101	LINK            			BELL  	407   	407         	1182206	SW  										SWASHPLATE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				SWASHPLATE INNER RING ANTI-DRIVE LINK DUE TO BEARING WEAR.						1	G	7	1 	3U			O	H2SW    					 
2002032600105	20020326	00105	SW  	2002	3	26	HEEA078313       	1	20020321	G	6520	406040400115	GEARBOX         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				TAIL ROTOR GEARBOX OUTPUT SHAFT SPLINES CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600106	20020326	00106	SW  	2002	3	26	HEEA078314       	1	20020321	G	6520	406040400117FM	GEARBOX         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH	1701 				53147				TAIL ROTOR GEARBOX SPLINES PITTED ON OUTPUT SHAFT.						1	G	7	1 	3U			O	H2SW    					 
2002032600107	20020326	00107	SW  	2002	3	26	HEEA078315       	1	20020321	G	6510	406040453101	SEAL            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	402PH					53159				TAIL ROTOR SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032600108	20020326	00108	SW  	2002	3	26	HEEA078316       	1	20020321	G	6510	406040453101	SEAL            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				TAIL ROTOR SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032600109	20020326	00109	SW  	2002	3	26	HEEA078317       	1	20020321	G	6310	406040500119	SUPPORT         		406040500123	BELL  	407   	407         	1182206	SW  										FREEWHEEL UNIT	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	417PH				A3344	53038				MAIN ROTOR FREEWHEEL UNIT SUPPORT LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032600110	20020326	00110	SW  	2002	3	26	HEEA078318       	1	20020321	G	6310	406040500119	SUPPORT         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	493PH					53393				MAIN ROTOR SUPPORT IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032600111	20020326	00111	SW  	2002	3	26	HEEA078319       	1	20020321	G	6310	406040532103	BEARING         		406040500119	BELL  	407   	407         	1182206	SW  										M/R SUPPORT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH				A1667	53386				MAIN ROTOR SUPPORT BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600112	20020326	00112	SW  	2002	3	26	HEEA078320       	1	20020321	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	RATCHETING      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				MAIN ROTOR UNIVERSAL IS RATCHETY.						1	G	7	1 	3U			O	H2SW    					 
2002032600113	20020326	00113	SW  	2002	3	26	HEEA078321       	1	20020321	G	6710	406310411101	BOOT            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				MAIN ROTOR BOOT IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600114	20020326	00114	SW  	2002	3	26	HEEA078322       	1	20020321	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404PH					53188				TAIL ROTOR LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2002032600115	20020326	00115	SW  	2002	3	26	HEEA078323       	1	20020321	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				TAIL ROTOR LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2002032600116	20020326	00116	SW  	2002	3	26	HEEA078324       	1	20020321	G	6220	407010100115FM	HUB             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	3747 				53199				MAIN ROTOR HUB HAS SURFACE CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002032600117	20020326	00117	SW  	2002	3	26	HEEA078325       	1	20020321	G	6220	407010100115	HUB             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH	3756 				53400				MAIN ROTOR HUB HAS DAMAGE ON LOWER CONE SEAT SPLINE.						1	G	7	1 	3U			O	H2SW    					 
2002032600118	20020326	00118	SW  	2002	3	26	HEEA078326       	1	20020321	G	6220		BEARING         		407010100115	BELL  	407   	407         	1182206	SW  										M/R HEAD	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH				A262	53147				MAIN ROTOR HEAD HAS SHEAR BEARING SEPARATION.  REPLACED SHEAR BEARING 2 EACH.						1	G	7	1 	3U			O	H2SW    					 
2002032600119	20020326	00119	SW  	2002	3	26	HEEA078327       	1	20020321	G	6220		BEARING         		407010100115	BELL  	407   	407         	1182206	SW  										LAG DAMPER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH				A348	53114				LEAD LAG DAMPER BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600120	20020326	00120	SW  	2002	3	26	HEEA078328       	1	20020321	G	6420		BEARING         		407012101111	BELL  	407   	407         	1182206	SW  										T/R HUB	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH				53198	53038				TAIL ROTOR HEAD HAS A FLAPPING BEARING,.						1	G	7	1 	3U			O	H2SW    					 
2002032600121	20020326	00121	SW  	2002	3	26	HEEA078329       	1	20020321	G	6420	407312100101	BEARING         		407012101111	BELL  	407   	407         	1182206	SW  										T/R HUB	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH				53277	53400				TAIL ROTOR HUB HAS A FLAPPING BEARING OUTER RACE UNBONDED FROM HUB/YOKE.  CLICKING WHEN FLAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002032600132	20020326	00132	SW  	2002	3	26	HEEA078330       	1	20020321	G	6420	407012101111	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR HEAD	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH	2833 				53209				CLICKING.						1	G	7	1 	3U			O	H2SW    					 
2002032600135	20020326	00135	SW  	2002	3	26	HEEA078331       	1	20020321	G	6420		BEARING         		407012101111	BELL  	407   	407         	1182206	SW  										TAIL ROTOR HEAD	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X				53393	53267				TAIL ROTOR HEAD HAS A FLAPPING BEARING						1	G	7	1 	3U			O	H2SW    					 
2002032600136	20020326	00136	SW  	2002	3	26	HEEA078332       	1	20020321	G	6410		BLADE           			BELL  	407   	407         	1182206	SW  										T/R BLADE	PEELING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	443  				53199				PAINT PEELING OFF BLADES.						1	G	7	1 	3U			O	H2SW    					 
2002032600140	20020326	00140	SW  	2002	3	26	HEEA078333       	1	20020321	G	6420	407312100101	BEARING         		407012101111	BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407XM				53464	53464				TAIL ROTOR HEAD BEARING RUBBER IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600142	20020326	00142	SW  	2002	3	26	HEEA078334       	1	20020321	G	6210	407015001117	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				MAIN ROTOR BLADE IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600143	20020326	00143	SW  	2002	3	26	HEEA078335       	1	20020321	G	6210	407015001117	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				MAIN ROTOR BLADE IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600144	20020326	00144	SW  	2002	3	26	HEEA078336       	1	20020321	G	6210	407015001117	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				MAIN ROTOR BLADE LEADING EDGE EROSION STRIP AT INBOARD END OF TOP WEIGHT POCKET CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600146	20020326	00146	SW  	2002	3	26	HEEA078337       	1	20020321	G	5310		BRACKET         			BELL  	407   	407         	1182206	SW  										SLAT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				SLAT BRACKET CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600152	20020326	00152	SW  	2002	3	26	HEEA078338       	1	20020321	G	6300	407040628101	TUBE            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DENTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				TUBE DENTED.						1	G	7	1 	3U			O	H2SW    					 
2002032600156	20020326	00156	SW  	2002	3	26	HEEA078339       	1	20020321	G	3213	407050201103	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				MLG CROSSTUBE SPREAD BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032600158	20020326	00158	SW  	2002	3	26	HEEA078340       	1	20020321	G	3213	407050202101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				CROSSTUBE HAS CORROSION BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032600159	20020326	00159	SW  	2002	3	26	HEEA078341       	1	20020321	G	3213	407050202103	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				CROSSTUBE SPREAD BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032600161	20020326	00161	SW  	2002	3	26	HEEA078342       	1	20020321	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				ENGINE MOUNT LOWER BEARING ON RT SIDE IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600163	20020326	00163	SW  	2002	3	26	HEEA078343       	1	20020321	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				ENGINE MOUNT BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600165	20020326	00165	SW  	2002	3	26	HEEA078344       	1	20020321	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				ENGINE MOUNT BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600167	20020326	00167	SW  	2002	3	26	HEEA078345       	1	20020321	G	7810	407062021101	DUCT            			BELL  	407   	407         	1182206	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				EXHAUST DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600168	20020326	00168	SW  	2002	3	26	HEEA078346       	1	20020321	G	2820	407062532101	TUBE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				FUEL TUBE KINKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600170	20020326	00170	SW  	2002	3	26	HEEA078347       	1	20020321	G	2820	407062532101	TUBE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				FUEL TUBE SLEEVE CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600172	20020326	00172	SW  	2002	3	26	HEEA078348       	1	20020321	G	5310	407064807119	SUPPORT         			BELL  	407   	407         	1182206	SW  										FUSELAGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				HOLES FOR BUSHING AND PIN WORN.						1	G	7	1 	3U			O	H2SW    					 
2002032600174	20020326	00174	SW  	2002	3	26	HEEA078349       	1	20020321	G	5320	407070731101	SUPPORT         			BELL  	407   	407         	1182206	SW  										COCKPIT	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				ADJUSTMENT DETENT SPRINGS BROKEN ON HEADSET SUPPORT BRACKET.						1	G	7	1 	3U			O	H2SW    					 
2002032600176	20020326	00176	SW  	2002	3	26	HEEA078350       	1	20020321	G	5320	407070731103	SUPPORT         			BELL  	407   	407         	1182206	SW  										HEADREST	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				ADJUSTMENT DETENT SPRINGS BROKEN ON HEADREST SUPPORT BRACKET						1	G	7	1 	3U			O	H2SW    					 
2002032600178	20020326	00178	SW  	2002	3	26	HEEA078351       	1	20020321	G	3213	407073854101	TUBE            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				CORROSION UNDER SLEEVE.						1	G	7	1 	3U			O	H2SW    					 
2002032600180	20020326	00180	SW  	2002	3	26	HEEA078353       	1	20020321	G	6300	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				ELASTOMERIC MATERIAL ON CORNER MOUNT IS DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2002032600182	20020326	00182	SW  	2002	3	26	HEEA078354       	1	20020321	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				TAIL ROTOR DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600183	20020326	00183	SW  	2002	3	26	HEEA078355       	1	20020321	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				TAIL ROTOR DISC PACK PITTED.						1	G	7	1 	3U			O	H2SW    					 
2002032600184	20020326	00184	SW  	2002	3	26	HEEA078356       	1	20020322	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				ENGINE MOUNT IS WORN EXCESSIVELY.						1	G	7	1 	3U			O	H2SW    					 
2002032600186	20020326	00186	SW  	2002	3	26	HEEA078357       	1	20020322	G	3212	407350300101	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG	LEAKING         	E			HEEA	O			O	OTHER                   			OTHER                   	O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				EMERGENCY FLOAT BAG LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002032600188	20020326	00188	SW  	2002	3	26	HEEA078358       	1	20020322	G	2910	70061F000X176A	HOSE            			BELL  	407   	407         	1182206	SW  										T/R SERVO	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				TAIL ROTOR SERVO PRESSURE HOSE IS CORRODED AT SLEEVE DUE TO DISSMILAR METAL.						1	G	7	1 	3U			O	H2SW    					 
2002032600190	20020326	00190	SW  	2002	3	26	HEEA078359       	1	20020322	G	2820	70061J000V204A	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				FUEL HOSE END FITTING ON HOSE CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002032600192	20020326	00192	SW  	2002	3	26	HEEA078360       	1	20020322	G	6300	70061J180W164A	HOSE            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	FRAYED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				EXCESSIVE AMOUNT OF RUBBER PROTRUDING FROM BRAIDS.						1	G	7	1 	3U			O	H2SW    					 
2002032600194	20020326	00194	SW  	2002	3	26	HEEA078361       	1	20020322	G	2820	70061J000V204A	FITTING         			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				HOSE IS CORRODED AT FITTING.						1	G	7	1 	3U			O	H2SW    					 
2002032600195	20020326	00195	SW  	2002	3	26	HEEA078362       	1	20020322	G	2820	70079H000Y150	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				FUEL HOSE KINKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600196	20020326	00196	SW  	2002	3	26	HEEA078363       	1	20020322	G	2820	70079H100F210	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				FUEL HOSE KINKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600198	20020326	00198	SW  	2002	3	26	HEEA078364       	1	20020322	G	2820	70079K000Z232	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				FUEL HOSE KINKED.						1	G	7	1 	3U			O	H2SW    					 
2002032600199	20020326	00199	SW  	2002	3	26	HEEA078365       	1	20020322	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										BOOST PUMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				BOOST PUMP CAUTION LIGHT WILL NOT COME ON.						1	G	7	1 	3U			O	H2SW    					 
2002032700002	20020327	00002	SW  	2002	3	27	HEEA078366       	1	20020322	G	2910	B923X0147C	HOSE            			BELL  	407   	407         	1182206	SW  										HYD SYSTEM	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				HYDRAULIC HOSE KINKED.						1	G	7	1 	3U			O	H2SW    					 
2002032700003	20020327	00003	SW  	2002	3	27	HEEA078367       	1	20020322	G	6400	J123131	MOUNT           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				RUBBED IS UNBONDED FROM SHOCK MOUNT.						1	G	7	1 	3U			O	H2SW    					 
2002032700004	20020327	00004	SW  	2002	3	27	HEEA078368       	1	20020322	G	6300	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				OIL COOLER BLOWER AFT BEARING ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002032600254	20020326	00254	SW  	2002	3	26	HEEA078372       	1	20020322	G	6510	407040320101	SHAFT           		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH				PHI0019	53147				COOLER BLOWER SHAFT HAS SPLINE WEAR.						1	G	7	1 	3U			O	H2SW    					 
2002032700005	20020327	00005	SW  	2002	3	27	HEEA078374       	1	20020322	G	6510	407340339101	BEARING         		PHIPBH40701F	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH				PHI0033	53398				OIL COOLER BLOWER BEARING HAS EXCESSIVE PLAY.						1	G	7	1 	3U			O	H2SW    					 
2002032700006	20020327	00006	SW  	2002	3	27	HEEA078375       	1	20020322	G	6510	400040055109	HOUSING         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				TAIL ROTOR HOUSING HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002032700007	20020327	00007	SW  	2002	3	27	HEEA078376       	1	20020322	G	6300	S924EC2	SHROUD          			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				SHROUD COVER ALL CRACKED OUT.  LEXAN COVER CRACKED AND PARTS MISSING.						1	G	7	1 	3U			O	H2SW    					 
2002032700008	20020327	00008	SW  	2002	3	27	HEEA078377       	1	20020322	G	6220		PIN             			BELL  	407   	407         	1182206	SW  										M/R HUB	MISINSTALLED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	109  			LK21	53114				BLADE GRIP PINS INSTALLED UPSIDE DOWN.						1	G	7	1 	3U			O	H2SW    					 
2002032700009	20020327	00009		2002	3	27	HEEA078380       	4	20020322	G	2312	064105430	TRANSCEIVER     			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				CANNOT CHANGE CHANNELS. PERFORMED PRELIMINARY INSPECTION.  COULD NOT DUPLICATE PROBLEM.  FOUND CORRODED FOILS ON DISPLAY	 BOARD BENEATH HEADER.  REPLACED DISPLAY BOARD.  REPAIRED.  ADJUSTED C/N SQUELCH, FREQUENCY AND SIDETONE.  BENCH CHECK G	OOD.				1	G	7	1 	3U			O	H2SW    					 
2002032700010	20020327	00010	SW  	2002	3	27	HEEA078381       	1	20020322	G	5302	206020113255	STRUCTURE       			BELL  	407   	407         	1182206	SW  										TAIL BOOM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				TAIL BOOM FIN IS SEPARATED AND CORRODED BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002032700011	20020327	00011	GL  	2002	3	27	HEEA078383       	2	20020322	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH	9089 				53283				HIGH TOT. REPLACED WITH SERVICEABLE BLEED VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032700012	20020327	00012	GL  	2002	3	27	HEEA078384       	2	20020322	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH	2995 				53283				FAILED POWER ASSURANCE CHECK. REPLACED WITH SERVICEABLE BLEED VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032700013	20020327	00013	GL  	2002	3	27	HEEA078385       	2	20020322	G	7240	23030911	COMBUSTION LINER			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				COMBUSTION LINER CRACKED AT FUEL NOZZLE MOUNT BOSS.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032700016	20020327	00016	GL  	2002	3	27	HEEA078386       	2	20020322	G	7321	23054164	SENSOR          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FADEC	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267	CAE847060			CAUSING NP1, NP1 RATE, OS, NPOS AND NPD FAULTS TO FADEC SYSTEM. REPLACED WITH SERVICEABLE PICKUP ASSY.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032700017	20020327	00017	GL  	2002	3	27	HEEA078388       	2	20020322	G	7421	23064130	IGNITER BOX     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				IGNITER WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032700018	20020327	00018	GL  	2002	3	27	HEEA078389       	2	20020322	G	7230	23064570	LINER           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					COMPRESSOR	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				CHAFING ON FUEL NOZZLE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032700019	20020327	00019	SW  	2002	3	27	HEEA078390       	1	20020322	G	7120		BEARING         			BELL  	407   	407         	1182206	SW  										ENG MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH				10190	53147				ENGINE MOUNT BEARING WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700020	20020327	00020	GL  	2002	3	27	HEEA078391       	2	20020322	G	7320	23072725	HMU             			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  						FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	496PH					53398				ELONGATED DRIVE PIN HOLE, FAILED 300 HOUR BACKLASH INSPECTION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032700021	20020327	00021	GL  	2002	3	27	HEEA078392       	2	20020322	G	7320	23072725	HMU             			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH	2526 				53398				WHEN SWITCH TO MANUAL MODE, ENGINE HAS HIGH ACCELERATION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002032700022	20020327	00022	SW  	2002	3	27	HEEA078393       	1	20020322	G	2432	31908001	BATTERY         			BELL  	407   	407         	1182206	SW  										MAIN	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	723PH					53283				WEAK. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700023	20020327	00023	SW  	2002	3	27	HEEA078394       	1	20020322	G	2432	31908001	BATTERY         			BELL  	407   	407         	1182206	SW  										MAIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				FAILED DURING START CAUSING FADEC HORN AND RAPID RISE IN TOT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700024	20020327	00024	SW  	2002	3	27	HEEA078395       	1	20020322	G	2432	32007001	BATTERY         			BELL  	407   	407         	1182206	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	436PH					51436				BATTERY WEAK. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700025	20020327	00025	SW  	2002	3	27	HEEA078396       	1	20020322	G	6220	407010100115	HUB             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	417PH	3756 				53038				HUB WILL NOT FIT ON MAST. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			O	H2SW    					 
2002032700026	20020327	00026	SW  	2002	3	27	HEEA078397       	1	20020322	G	3213	407050201101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				MLG CROSSTUBE HAS CORROSION PITS. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			O	H2SW    					 
2002032700027	20020327	00027	SW  	2002	3	27	HEEA078398       	1	20020322	G	5230	407070620143	PANEL           			BELL  	407   	407         	1182206	SW  										CARGO DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH					53399				SIDE CARGO (LITTER) DOOR TRIM PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2002032700028	20020327	00028	SW  	2002	3	27	HEEA078399       	1	20020322	G	5230	407070620155	PANEL           			BELL  	407   	407         	1182206	SW  										CARGO DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				CARGO DOOR PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2002032700029	20020327	00029	SW  	2002	3	27	HEEA078400       	1	20020322	G	5200	407070620155	PANEL           			BELL  	407   	407         	1182206	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				GREENHOUSE WINDOW TRIM PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2002032700031	20020327	00031	SW  	2002	3	27	HEEA078401       	1	20020322	G	5210	407070620157	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				LT UPPER DOOR PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2002032700040	20020327	00040	SW  	2002	3	27	HEEA078402       	1	20020322	G	5210	407070620180	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				DOOR PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2002032700041	20020327	00041	SW  	2002	3	27	HEEA078403       	1	20020322	G	2510	407070700103	FRAME           			BELL  	407   	407         	1182206	SW  										SEAT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				LOWER SEAT FRAME SUPPORT AROUND INSERTS HEAVILY CORRODED. REPLACED WITH SERVICEABLE FRAME.						1	G	7	1 	3U			O	H2SW    					 
2002032700042	20020327	00042	SW  	2002	3	27	HEEA078404       	1	20020322	G	3212	407073848101	BOTTLE          			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				RELEASE VALVE TO RESERVOIR ADAPTER CORRODED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700043	20020327	00043	SW  	2002	3	27	HEEA078405       	1	20020322	G	3212	407073848101	BOTTLE          			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				EMERGENCY FLOAT BOTTLE LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700044	20020327	00044	SW  	2002	3	27	HEEA078406       	1	20020322	G	3212	407301110	STEP            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				CORRODED AT BRACKET MOUNT BOLT HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700046	20020327	00046	SW  	2002	3	27	HEEA078407       	1	20020322	G	3212	407303003	STEP            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				CORRODED AND ELONGATED HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700047	20020327	00047	SW  	2002	3	27	HEEA078408       	1	20020322	G	3212	407303003	STEP            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				CORRODED AROUND BOLT HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700048	20020327	00048	SW  	2002	3	27	HEEA078409       	1	20020322	G	5210	407314102	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				PILOT DOOR TRIM PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700051	20020327	00051	SW  	2002	3	27	HEEA078410       	1	20020322	G	2500	407570001117	PANEL           			BELL  	407   	407         	1182206	SW  										CABIN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700052	20020327	00052	SW  	2002	3	27	HEEA078411       	1	20020322	G	5620	407706301106	WINDOW          			BELL  	407   	407         	1182206	SW  										PAX CABIN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				RT PASSENGER WINDOW IS CRACKED NEAR UPPER MOUNTING SCREW HOLE. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002032700053	20020327	00053		2002	3	27	HEEA078412       	4	20020322	G	2562	453015001	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										ELT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				SWITCH INOPERATIVE. SENT TO ARTEX AIRCRAFT SUPPLIES FOR WARRANTY REPAIR.						1	G	7	1 	3U			O	H2SW    					 
2002043000003	20020430	00003	NE  	2002	4	30	HEEA078471       	2	20020326	G	7420	9550168600	LEAD            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					IGNITER	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				IGNITER LEAD CHAFED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002043000004	20020430	00004	NE  	2002	4	30	HEEA078472       	2	20020326	G	7421	9550168760	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				IGNITER HAS EXCESSIVE WEAR.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002043000005	20020430	00005	NE  	2002	4	30	HEEA078473       	2	20020326	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				IGNITER HAS EXCESSIVE WEAR.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002043000006	20020430	00006	GL  	2002	4	30	HEEA078474       	2	20020326	G	7321	0164348810	FUEL CONTROL    			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				FUEL CONTROL ANTICIPATOR SHAFT RATCHETY.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002043000007	20020430	00007	GL  	2002	4	30	HEEA078481       	2	20020329	G	7250	23071309	BEARING RACE    			BELL  	206   	TH57A       	1180821	SW  	ALLSN 	250C  	250C18      	03011	GL  					TURBINE SECTION	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	131	727  				162817				TURBINE WAS REMOVED DUE TO METAL IN OIL.  INSPECTION REVEALED SPALLING ON INNER RACE COUPLING BEARING RACE. INSTALLED NE	W INNER RACE COUPLING.					1	G	7	1 	3U	3	U	 	EXPA1G71	E4CE				 
2002043000008	20020430	00008	NE  	2002	4	30	HEEA078482       	1	20020408	G	7920	9560115450	MAGNETIC SEAL   			SKRSKY	S76   	S76A        	8143006	NE  										AIR/OIL SEP	FAILED          	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	22342	107  				760096				DURING CRUISE FLIGHT NR 2 ENGINE LOST OIL PRESSURE. MAINTENANCE FOUND THE MAGNETIC SEAL ON THE AIR / OIL SEPARATOR GEAR 	HAD FAILED RESULTING IN THE LOSS OF ALL ENGINE OIL.					1	G	7	2 	3U			 	H1NE    					 
2002043000009	20020430	00009	SW  	2002	4	30	HEEA078485       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805	4217 				31106				GEARBOX HAS CORROSION ON CASE.						1	G	7	1 	4U			 	H4SW    					 
2002043000010	20020430	00010	SW  	2002	4	30	HEEA078486       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008	2536 				36004				MAIN ROTOR COMBINING GEARBOX MAKING METAL.						1	G	7	2 	4U			 	H4SW    					 
2002043000011	20020430	00011	SW  	2002	4	30	HEEA078487       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736D	11885				31135				MAIN ROTOR COMBINING GEARBOX MAKING METAL.						1	G	7	1 	4U			 	H4SW    					 
2002043000012	20020430	00012	SW  	2002	4	30	HEEA078488       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	22347	2408 				36005				MAIN ROTOR COMBINING GEARBOX HAS LOW OIL PRESSURE.						1	G	7	2 	4U			 	H4SW    					 
2002043000013	20020430	00013	SW  	2002	4	30	HEEA078489       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X	7162 				33115				MAIN ROTOR COMBINING GEARBOX IS MAKING METAL.						1	G	7	2 	4U			 	H4SW    					 
2002043000014	20020430	00014	SW  	2002	4	30	HEEA078490       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F	13260				33073				MAIN ROTOR COMBINING GEARBOX IS MAKING METAL.						1	G	7	2 	4U			 	H4SW    					 
2002043000015	20020430	00015	SW  	2002	4	30	HEEA078491       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	800Y	2914 				33134				MAIN ROTOR COMBINING GEARBOX IS MAKING METAL.						1	G	7	2 	4U			 	H4SW    					 
2002043000016	20020430	00016	SW  	2002	4	30	HEEA078492       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH	3389 				33150				MAIN ROTOR GEARBOX IS MAKING METAL.						1	G	7	2 	4U			 	H4SW    					 
2002043000017	20020430	00017	SW  	2002	4	30	HEEA078493       	1	20020426	G	6310	3024780	GEARBOX         			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736D	15707				31135				NR 1 MAIN ROTOR COMBINING GEARBOX IS MAKING METAL.						1	G	7	1 	4U			 	H4SW    					 
2002043000018	20020430	00018	GL  	2002	4	30	HEEA078505       	2	20020426	G	7250		SEAL            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TURBINE WHEEL	FAILED          	E			HEEA	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	3107N	1135 				51512	CAE890024			ENGINE REMOVED DUE TO EXCESSIVE OIL CONSUMPTION.  TURBINE WAS REPAIRED DUE TO EXCESSIVE OIL CONSUMPTION AND OIL QUENCHED	 1ST STAGE WHEEL.  GEARBOX SCAVENGE CHECKED OK.  REPLACED 35-37 SEAL P/N 23031494. PART SCRAPPED.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002043000019	20020430	00019	GL  	2002	4	30	HEEA078506       	2	20020426	G	7230	23004513	CARBON SEAL     		23051643    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					COMPRESSOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K	925  			CAC90511	760047	CAE890522S			COMPRESSOR CARBON SEAL HAS WORN TANGS AND SLOTS.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002043000020	20020430	00020	GL  	2002	4	30	HEEA078507       	2	20020426	G	7230	23004513	CARBON SEAL     		23051643    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COMPRESSOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31073	746  			CAC91631	51519	CAE895535			COMPRESSOR CARBON SEAL HAS WORN TANGS AND SLOTS.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002050100001	20020501	00001		2002	5	1	HEEA078508       	4	20020325	G	3457	13824120234	RECEIVER        			BELL  	407   	407         	1182206	SW  										GPS	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	724PH					53327				SENSITIVE TO TOUCH / VIBRATION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100002	20020501	00002		2002	5	1	HEEA078510       	4	20020325	G	3457	13824120234	RECEIVER        			BELL  	407   	407         	1182206	SW  										GPS	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	406PH					53198				SAFEGUARD ENABLED AND NOT DATA BASE INDICATED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100003	20020501	00003	SW  	2002	5	1	HEEA078511       	1	20020325	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	1529 				53199				STARTER GEN HAS WORN BRUSHES, FOUND ON 300 HOUR INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2002050100004	20020501	00004	GL  	2002	5	1	HEEA078512       	2	20020325	G	7297	23065805	HARNESS         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FADEC	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				FADEC FAILURE DUE TO SHORT BETWEEN PINS U & V OF HMU CONNECTOR. REPLACED WITH SERVICEABLE HARNESS.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002050100005	20020501	00005	GL  	2002	5	1	HEEA078513       	2	20020325	G	7297	23065805	HARNESS         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FADEC	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				FADEC FAIL AND FADEC FAULT LIGHTS KEEP COMING ON. REPLACED WITH SERVICEABLE HARNESS.  TO BE SENT TO BELL HELICOPTER TEXT	RON FOR CREDIT.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002050100006	20020501	00006	SW  	2002	5	1	HEEA078514       	1	20020325	G	3340	4596	BULB            			BELL  	407   	407         	1182206	SW  										EXTERIOR	BURNED OUT      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	490PH					53378				LIGHT BURNED OUT. SCRAPPED LOCALLY AND REPLACED WITH SERVICEABLE LIGHT.						1	G	7	1 	3U			O	H2SW    					 
2002050100007	20020501	00007		2002	5	1	HEEA078515       	4	20020325	G	3421	5040017901	INDICATOR       			BELL  	407   	407         	1182206	SW  										ATTITUDE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	724PH					53327				READS TWO DEGREES RIGHT WING DOWN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100008	20020501	00008		2002	5	1	HEEA078516       	4	20020325	G	3421	50400179015	INDICATOR       			BELL  	407   	407         	1182206	SW  										COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	490PH					53378				PRECESSES AND TURNS COMPLETELY UPSIDE DOWN AFTER WARMED UP. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100009	20020501	00009		2002	5	1	HEEA078517       	4	20020325	G	3422	5050031904	INDICATOR       			BELL  	407   	407         	1182206	SW  										GYRO	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	447PH					53114				FLAG WILL NOT STAY PULLED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100010	20020501	00010		2002	5	1	HEEA078518       	4	20020325	G	3422	5050031904	GYRO            			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	724PH					53327				DG SPINS AFTER AIRCRAFT STRAIGHTENS OUT.						1	G	7	1 	3U			O	H2SW    					 
2002050100011	20020501	00011		2002	5	1	HEEA078519       	4	20020325	G	3422	5050031904	GYRO            			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	406PH					53198				COMPASS CARD ON DIRECTIONAL GYRO SPINS OCCASSIONALLY WITHOUT STOPPING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100012	20020501	00012		2002	5	1	HEEA078520       	4	20020325	G	3422	5050031904	GYRO            			BELL  	407   	407         	1182206	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	501PH					53401				TEMPORARILY FAIL. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100013	20020501	00013		2002	5	1	HEEA078521       	4	20020325	G	3422	5050010902	GYRO            			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	406PH					53198				PRECESSES 50 DEGREES IN 6 MINUTES. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100014	20020501	00014	SW  	2002	5	1	HEEA078522       	1	20020325	G	3340	6839	BULB            			BELL  	407   	407         	1182206	SW  										EXTERNAL	BURNED OUT      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	719PH					53266				LIGHT BURNED OUT. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100015	20020501	00015	SW  	2002	5	1	HEEA078523       	1	20020325	G	2910	70030X000D494	HOSE            			BELL  	407   	407         	1182206	SW  										HYD SYSTEM	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				HOSE KINKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100016	20020501	00016		2002	5	1	HEEA078525       	4	20020325	G	3457	8143902240B	GPS             			BELL  	407   	407         	1182206	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	740PH					53435				WILL NOT HOLD SIGNAL. PERFORMED PRELIMINARY INSPECTION AND TESTED.  COULD NOT DUPLICATE PROBLEM.  TIGHTENED ON/OFF SWITC	H.  BENCH CHECK GOOD.					1	G	7	1 	3U			O	H2SW    					 
2002050100017	20020501	00017	SW  	2002	5	1	HEEA078526       	1	20020325	G	5210	90015102156	LATCH           			BELL  	407   	407         	1182206	SW  										PAX DOOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				LATCHES WORN AT HINGE PIN MOUNT HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100018	20020501	00018	SW  	2002	5	1	HEEA078528       	1	20020325	G	2432	BD131	CONTACTOR       			BELL  	407   	407         	1182206	SW  										GENERATOR	BURNED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	447PH					53114				DC GENERATOR CONTACTOR BURNED. SCRAPPED AND REPLACED PART.						1	G	7	1 	3U			O	H2SW    					 
2002050100019	20020501	00019	GL  	2002	5	1	HEEA078529       	2	20020325	G	7421	CH34187A	IGNITER         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8595X					53267				DELAYED STARTING. SCRAPPED LOCALLY DUE TO WORN BEYOND LIMITS.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002050100020	20020501	00020	SW  	2002	5	1	HEEA078530       	1	20020325	G	6510		BEARING         			BELL  	407   	407         	1182206	SW  										T/R DRIVE	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	436PH					51436				ROUGH FWD BEARING. REPLACED BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002050100066	20020501	00066		2002	5	1	HEEA078532       	4	20020326	G	2330	002000002	AMPLIFIER       																	PA SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										BLOWS FUSE WHEN POWER IS APPLIED. VERIFY COMPLAINT.  FOUND FUSE F1 BAD AND INTERMITTENT SHORT WHEN TAP ON TRANSFORMER T2	.  REPLACED FUSE F1 AND RESOLDERED CONNECTIONS ON TRANSFORMER T2.  REPAIRED.																		 
2002050100069	20020501	00069	NE  	2002	5	1	HEEA078533       	2	20020326	G	7314		DRIVE GEAR      			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH				PE4172	30899				WORN DRIVE SPLINES. REPLACED WITH SERVICEABLE FUEL PUMP.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002050100071	20020501	00071	GL  	2002	5	1	HEEA078535       	2	20020326	G	7261	03808808	ELEMENT         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE OIL	BYPASSING       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	31821	124  				51076				FACET FILTER IN BYPASS CONDITION. REPLACED FILTER.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002050100072	20020501	00072	GL  	2002	5	1	HEEA078536       	2	20020326	G	7261	03808808	ELEMENT         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE OIL	BYPASSING       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3905B	128  				45598				FACET FILTER IN BYPASS CONDITION. SCRAPPED AND REPLACED FILTER.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002050100073	20020501	00073		2002	5	1	HEEA078537       	4	20020326	G	3422	060002600	GYRO            			BELL  	230   	230         	1182149	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911RC					23037				INOPERATIVE WITH ATTITUDE FAIL DISPLAYED ON EADI. SENT TO GREATLAKES AVIONICS FOR INSPECTION AND REPAIR.						1	G	7	2 	3U			NC	H9SW    					 
2002050100074	20020501	00074		2002	5	1	HEEA078538       	4	20020326	G	2312	063100700	TRANSCEIVER     			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3208H					31304				TRANSCEIVER FAILED 2 YEAR INSPECTION.						1	G	7	1 	4U			 	H4SW    					 
2002050100075	20020501	00075	SW  	2002	5	1	HEEA078542       	1	20020401	G	3213	AB205050400063	CROSSTUBE       			BELL  	212   	212         	1181420	SW  										MLG	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	03	5736J	2096 				31140				DURING PASSENGER LOADING (ENGINES SECURED) AFT CROSSTUBE FAILED ONE INCH OUTBOARD OF RIGHT HAND ATTACHMENT POINT (STRESS	 MARKS ON TUBE INDICATES FAILURE STARTED AT THE 12 O`CLOCK POSITION).  AIRCRAFT SETTLED TO THE RIGHT RESULTING IN DAMAGE	 TO RIGHT HAND AFT FLOAT BOARD ASSEMBLY AND TO THE RIGHT HAND SKID TUBE IN THE AREA OF THE FWD SADDLE. REPLACED AFT CROS	STUBE AND RT SKID TUBE.			1	G	7	1 	4U			 	H4SW    					 
2002050100076	20020501	00076	SW  	2002	5	1	HEEA078546       	1	20020404	G	6210	407015001107	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH	4194 				53038				CRACKED AT TRIM TAB AREA.  CORROSION AROUND UPPER SCREWS FOR LOWER WEIGHT POCKETS BUILDING.						1	G	7	1 	3U			O	H2SW    					 
2002050100077	20020501	00077	SW  	2002	5	1	HEEA078547       	1	20020404	G	6320	407040006107	GEARBOX         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	721PH	998  				53278				CHIP LIGHT.  3 FLAKES IN LOWER PLUG.  CHIP LIGHT DURING PENALTY RUN.  FLAKES AND BRASS IN FILTER.						1	G	7	1 	3U			O	H2SW    					 
2002050100078	20020501	00078	SW  	2002	5	1	HEEA078549       	1	20020404	G	6230	407040011101	MAST            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH	2496 				53199				MAST 2ND STAGE FORWARD COOLING PLATE CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002050100079	20020501	00079	SW  	2002	5	1	HEEA078554       	1	20020405	G	2822	407362005105	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL BOOST	CORRODED        	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	447PH					53114				CORROSION ON EXTERIOR OF BOOST PUMP SWITCH.						1	G	7	1 	3U			O	H2SW    					 
2002050100080	20020501	00080	SW  	2002	5	1	HEEA078555       	1	20020405	G	6710	406310404101	ROD END BEARING 			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				WORN ROD END BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002050100092	20020501	00092	SW  	2002	5	1	HEEA078556       	1	20020405	G	6510	206061432117	IMPELLER        			BELL  	407   	407         	1182206	SW  										T/R BLOWER	BENT            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH					53209				TAIL ROTOR BLOWER IMPELLER IS BENT.						1	G	7	1 	3U			O	H2SW    					 
2002050100093	20020501	00093	SW  	2002	5	1	HEEA078558       	1	20020405	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404PH					53188				TAIL ROTOR LINK HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002050100094	20020501	00094	SW  	2002	5	1	HEEA078559       	1	20020405	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				TAIL ROTOR LINK HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002050100095	20020501	00095	SW  	2002	5	1	HEEA078560       	1	20020405	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002050100096	20020501	00096	SW  	2002	5	1	HEEA078561       	1	20020405	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				MLG EMERGENCY FLOAT COVER IS WORN AND TORN.						1	G	7	1 	3U			O	H2SW    					 
2002050100098	20020501	00098	SW  	2002	5	1	HEEA078562       	1	20020405	G	6300	407040628101	TUBE            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	721PH					53278				MAIN ROTOR TUBE HAS WORN SPOTS.						1	G	7	1 	3U			O	H2SW    					 
2002050100099	20020501	00099	SW  	2002	5	1	HEEA078563       	1	20020405	G	6300	407040627101	TUBE            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	721PH					53278				MAIN ROTOR TUBE HAS WORN SPOTS.						1	G	7	1 	3U			O	H2SW    					 
2002050100100	20020501	00100	SW  	2002	5	1	HEEA078573       	1	20020405	G	7921	406360500101	OIL COOLER      			BELL  	407   	407         	1182206	SW  										ENGINE OIL	CLOGGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH					53114				ENGINE OIL COOLER IS CLOGGED WITH GREASE.						1	G	7	1 	3U			O	H2SW    					 
2002050100117	20020501	00117	SW  	2002	5	1	HEEA078574       	1	20020405	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH					53399				TAIL ROTOR DISC PACK IS SEPARATED.						1	G	7	1 	3U			O	H2SW    					 
2002050200005	20020502	00005	SW  	2002	5	2	HEEA078575       	1	20020405	G	2821		WARNING LIGHT   			BELL  	407   	407         	1182206	SW  										COCKPIT	ILLUMINATED     	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	612PH					53199				FUEL FILTER LIGHT ILLUMINATED,  CHANGED FILTER AND LIGHT STILL ILLUMINATED.						1	G	7	1 	3U			O	H2SW    					 
2002050200006	20020502	00006	SW  	2002	5	2	HEEA078576       	1	20020405	G	2910	70079H100F210	HOSE            			BELL  	407   	407         	1182206	SW  										HYD SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				HYDRAULIC HOSE CHAFING ON THE FIRE SLEEVE FROM THE MLG DOOR SUPPORT.						1	G	7	1 	3U			O	H2SW    					 
2002050200007	20020502	00007	SW  	2002	5	2	HEEA078577       	1	20020405	G	6220	407001526105	BELLCRANK       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR HEAD	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH	1006 				53461				BELLCRANK WASHERS UNBONDED.						1	G	7	1 	3U			O	H2SW    					 
2002050200008	20020502	00008	SW  	2002	5	2	HEEA078578       	1	20020405	G	6220	407001524105	BELLCRANK       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR HEAD	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH	1006 				53461				WASHERS UNBONDED.						1	G	7	1 	3U			O	H2SW    					 
2002050200009	20020502	00009	SW  	2002	5	2	HEEA078579       	1	20020405	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				DETERIORATED. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#72948902.						1	G	7	1 	3U			O	H2SW    					 
2002050200010	20020502	00010	SW  	2002	5	2	HEEA078580       	1	20020405	G	3212	206050247137	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				DETERIORATED, END CAP TORN.						1	G	7	1 	3U			O	H2SW    					 
2002050200011	20020502	00011	SW  	2002	5	2	HEEA078581       	1	20020405	G	6230	406010126107	DRIVE RING      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	1262 				53038				DRIVE RING SET BLUE EPOXY FLAKING.						1	G	7	1 	3U			O	H2SW    					 
2002050200012	20020502	00012	SW  	2002	5	2	HEEA078582       	1	20020405	G	7714	407375008101	INDICATOR       			BELL  	407   	407         	1182206	SW  										DUAL TACH	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	407PH					53003				DUAL TACHOMETER IS INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2002050200013	20020502	00013	SW  	2002	5	2	HEEA078583       	1	20020405	G	6710	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	3292 				53198				LINK ASSY HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002050200014	20020502	00014	SW  	2002	5	2	HEEA078584       	1	20020405	G	6230	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	1961 				53198				MAIN ROTOR LEVER ASSY HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002050200015	20020502	00015	SW  	2002	5	2	HEEA078585       	1	20020405	G	6230	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	4335 				53198				MAIN ROTOR LEVER ASSY HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002050200016	20020502	00016	SW  	2002	5	2	HEEA078586       	1	20020405	G	6230	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	1706 				53198				LINK ASSY HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002050200017	20020502	00017	SW  	2002	5	2	HEEA078588       	1	20020405	G	6321		PAD             			BELL  	407   	407         	1182206	SW  										ROTOR BRAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				PAD AND BOLTS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002050200018	20020502	00018		2002	5	2	HEEA078592       	4	20020408	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										NR 1 ELEVATOR SYSTEM WILL ONLY STAY ON LINE FROM 15 MINUTES TO ONE HOUR 30 MINUTES.  CAN RE-ENGAGE SYSTEM AND WILL WORK 	FOR ABOUT ANOTHER HOUR BEFORE KICKING OFF LINE.					2	G	7	2 	4U			 	H10SW   					 
2002050200019	20020502	00019	SW  	2002	5	2	HEEA078593       	1	20020408	G	2497		CONNECTOR       			BELL  	407   	407         	1182206	SW  										BUSS BAR	LOOSE           	E			HEEA	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	03	436PH					51436				IN CRUISE FLIGHT PILOT SMELLED SOMETHING BURNING.  SMELL FROM BAGGAGE COMPARTMENT. MAINTENANCE FOUND LOOSE CONNECTIONS A	T STARTER RELAY TO LINE CONTROL RELAY.  ARCING OCCURRED AT STARTER RELAY TERMINAL A2 AND AT LINE CONTROL RELAY TERMINAL 	A2 ALSO FOUND BURNED AND MELTED HEAT SHRINK.				1	G	7	1 	3U			O	H2SW    					 
2002050200020	20020502	00020	SW  	2002	5	2	HEEA078594       	1	20020412	G	6300	412040385101	CASE            			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RE-INFORCEMENT RIB NEXT TO OIL JET BOSS WAS IMPROPERLY MACHINED AND OIL COLLECTOR PAN P/N 212-040-146-001 RUBS ON RIB.						1	G	7	2 	4U			 	H4SW    					 
2002050200021	20020502	00021	SW  	2002	5	2	HEEA078599       	1	20020418	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										STARTER SPINS BUT DOES NOT ENGAGE.						2	G	7	2 	4U			 	H10SW   					 
2002050200022	20020502	00022	SW  	2002	5	2	HEEA078600       	1	20020418	G	5311	205032810115S	FRAME           			BELL  	412   	412         	1182202	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										AIRCRAFT RECEIVED WITH CRACK IN LOWER FORWARD RADIUS ON FLANGE.						1	G	7	2 	4U			 	H4SW    					 
2002050200023	20020502	00023	SW  	2002	5	2	HEEA078601       	1	20020418	G	6710	214001347005	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ROTARY ACTUATOR IS STICKING. WILL NOT RELEASE.						2	G	7	2 	4U			 	H10SW   					 
2002050200024	20020502	00024	SW  	2002	5	2	HEEA078604       	1	20020422	G	5620	206031501133	WINDOW          			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NO RAILS FOR SLIDING WINDOW.  NO PLASTIC BORDER FOR RIVETING TO DOOR.						1	G	7	1 	3U			 	H2SW    					 
2002050200025	20020502	00025	SW  	2002	5	2	HEEA078605       	1	20020422	G	3212	214031792101	COVER           			BELL  	214   	214ST       	1182106	SW  										EMERGENCY FLOAT	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				FOUND LT FLOAT FAIRING LOOSE. FOUND TOP EDGE HAD COME LOOSE FROM SCREWS AND WIND HAD PULLED COVER OPEN.						2	G	7	2 	4U			 	H10SW   					 
2002050200026	20020502	00026	SW  	2002	5	2	HEEA078608       	1	20020423	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										WILL NOT MOTOR ENGINE.  SOUNDS LIKE STARTER PAWL NOT ENGAGING.						2	G	7	2 	4U			 	H10SW   					 
2002050200027	20020502	00027	SW  	2002	5	2	HEEA078611       	1	20020426	G	2435		DAMPENER        			BELL  	407   	407         	1182206	SW  										STARTER GEN	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH	1761 			99261	53399				STARTER GEN HAS A PITTED DAMPNER PLATE.						1	G	7	1 	3U			O	H2SW    					 
2002050200028	20020502	00028	EU  	2002	5	2	HEEA078621       	1	20020326	G	6321	350A32050002	BRAKE           			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH	1137 				3352				ROTOR BRAKE WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2002050200029	20020502	00029	EU  	2002	5	2	HEEA078622       	1	20020326	G	6321	350A32501000	BRAKE           			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				ROTOR BRAKE LINING WORN. SCRAPPED PER AEC.						1	G	7	1 	3U			 	H9EU    					 
2002050200030	20020502	00030	EU  	2002	5	2	HEEA078623       	1	20020326	G	6220	350A32308801	FLANGE          			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	GOUGED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				FACE OF FLANGE ON MAIN ROTOR, HAS DEEP GOUGE.						1	G	7	1 	3U			 	H9EU    					 
2002050200031	20020502	00031	EU  	2002	5	2	HEEA078624       	1	20020326	G	6420	704A33651190	BEARING         		350A33200406	SNIAS 	350   	AS350B      	8680801	EU  										T/R SPIDER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH	1958 			MA0542	3248				T/R SPIDER SLIDER BEARINGS WORN.						1	G	7	1 	3U			 	H9EU    					 
2002050200032	20020502	00032	EU  	2002	5	2	HEEA078625       	1	20020326	G	6420		BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR HEAD	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				TAIL ROTOR HUB HAS WORN BEARINGS.						1	G	7	1 	3U			 	H9EU    					 
2002050200033	20020502	00033	EU  	2002	5	2	HEEA078626       	1	20020326	G	6420		BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										T/R HEAD	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				BEARINGS DELAMINATED. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H9EU    					 
2002050200034	20020502	00034	EU  	2002	5	2	HEEA078627       	1	20020326	G	6420		BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										T/R HEAD	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	855PH					3351				WORN BEARINGS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H9EU    					 
2002050200035	20020502	00035	EU  	2002	5	2	HEEA078628       	1	20020326	G	6720		BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										T/R PITCH CTRL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				T/R PITCH CONTROL BEARING WORN.						1	G	7	1 	3U			 	H9EU    					 
2002050200036	20020502	00036	EU  	2002	5	2	HEEA078629       	1	20020326	G	6720		BUSHING         			SNIAS 	350   	AS350B      	8680801	EU  										T/R PITCH CNTL	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				BUSHINGS CRACKED AND CORRODED. SCRAPPED PER AEC.						1	G	7	1 	3U			 	H9EU    					 
2002050200037	20020502	00037	EU  	2002	5	2	HEEA078630       	1	20020326	G	6520	350A33215300	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE	1120 				3230				TAIL ROTOR BEARING HAS RUBBER CRACKED AND DETERIORATED ON BEARING. SCRAPPED PER AEC.						1	G	7	1 	3U			 	H9EU    					 
2002050200038	20020502	00038	EU  	2002	5	2	HEEA078631       	1	20020326	G	6230		TUBE            			SNIAS 	350   	AS350B2     	8680813	EU  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				SWASHPLATE GUIDE HAS A WORN TUBE.						1	G	7	1 	3U			 	H9EU    					 
2002050200039	20020502	00039	EU  	2002	5	2	HEEA078632       	1	20020326	G	6220	350A37124420	BOLT            			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				M/R ATTACHMENT BOLT WORN THREADS ON SMALL STUD. SCRAPPED.						1	G	7	1 	3U			 	H9EU    					 
2002050200040	20020502	00040	EU  	2002	5	2	HEEA078633       	1	20020326	G	6410	355A09103601	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				TAIL ROTOR HAS A WORN BEARING.						1	G	7	1 	3U			 	H9EU    					 
2002050200041	20020502	00041	EU  	2002	5	2	HEEA078634       	1	20020326	G	6410	355A09103601	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE	238  				3230				TAIL ROTOR LAMINANT SEPARATION AT THE END OF THE BEARINGS. (SCRAPPED)						1	G	7	1 	3U			 	H9EU    					 
2002050200042	20020502	00042	EU  	2002	5	2	HEEA078635       	1	20020326	G	6410	355A09103601	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				TAIL ROTOR BEARING WEAR AND DETERIORATION AND DELAMINATION. (SCRAPPED)						1	G	7	1 	3U			 	H9EU    					 
2002050200043	20020502	00043		2002	5	2	HEEA078636       	4	20020326	G	3421	504001790116	GYRO            			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	856PH					3352				INDICATOR UNRELIABLE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2002050200044	20020502	00044		2002	5	2	HEEA078637       	4	20020326	G	3422	5050010902	GYRO            			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	40466					3004				DG TOTALLY INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2002050200045	20020502	00045	EU  	2002	5	2	HEEA078638       	1	20020326	G	6220	704A33633211	STOP            			SNIAS 	350   	AS350B      	8680801	EU  										STARFLEX	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE	1120 				3230				SEPARATION AT STARFLEX ATTACH POINT.						1	G	7	1 	3U			 	H9EU    					 
2002050200046	20020502	00046	EU  	2002	5	2	HEEA078639       	1	20020326	G	8000	845UN01Q1AA5F	SWITCH          			SNIAS 	350   	AS350B      	8680801	EU  										STARTER	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	971AE	309  				3230				INTERMITTENT STARTING PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2002050200047	20020502	00047	EU  	2002	5	2	HEEA078640       	1	20020326	G	2140	857A1641	VALVE           			SNIAS 	350   	AS350B      	8680801	EU  										HEATER	STIFF           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	856PH					3352				HEATER VALVE HARD TO TURN, WILL NOT TURN OFF.						1	G	7	1 	3U			 	H9EU    					 
2002050200048	20020502	00048	EU  	2002	5	2	HEEA078641       	1	20020326	G	7920	9560158180	FILTER          			SNIAS 	350   	AS350B      	8680801	EU  										OIL SYSTEM	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH					3248				OIL FILTER MESH DAMAGE.						1	G	7	1 	3U			 	H9EU    					 
2002050200049	20020502	00049		2002	5	2	HEEA078642       	4	20020326	G	2312	9710831	RADIO           			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	MALADJUSTMENT   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	970AE					3235				VHF WILL NOT TRANSMIT.						1	G	7	1 	3U			 	H9EU    					 
2002050200050	20020502	00050		2002	5	2	HEEA078643       	4	20020326	G	2312	9710831	RADIO           			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	970AE					3235				RECEPTION ON VHF BAND BREAKS UP GD-1, GD-2 ON VHF BAND.						1	G	7	1 	3U			 	H9EU    					 
2002050200051	20020502	00051		2002	5	2	HEEA078644       	4	20020326	G	3416	D120P2T	ANEROID         			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	READS LOW       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	971AE	982  				3230				READS 100 FEET LOW AND SOMETIMES 300 FEET LOW.						1	G	7	1 	3U			 	H9EU    					 
2002050200052	20020502	00052	EU  	2002	5	2	HEEA078645       	1	20020326	G	2550	S12	GAUGE           			SNIAS 	350   	AS350B      	8680801	EU  										CARGO LIFT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	856PH					3352				SHACKLE GAUGE WOULD NOT INDICATE LOAD WEIGHT.						1	G	7	1 	3U			 	H9EU    					 
2002050200053	20020502	00053		2002	5	2	HEEA078646       	4	20020326	G	3457	0110005400	GPS             			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	135AE					S838				PILOT REPORTS THAT GPS TAKES 5-10 MINUTES TO CHANGE FUNCTIONS. PERFORMED PRELIMINARY INSPECTION.  VERIFIED UNIT TAKES TO	O LONG TO LOCK ON AND CRSR AND ENT BUTTONS INTERMITTENT AND NAV LED NOT WORKING.  SENT TO GARMIN INTERNATIONAL FOR INSPE	CTION AND REPAIR.				1	G	7	2 	3U			 	H3EU    					 
2002050200054	20020502	00054	EU  	2002	5	2	HEEA078647       	1	20020412	G	2510	350A77125807	SEAT            			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AE					3229				COCKPIT SEAT IS CRACKED.						1	G	7	1 	3U			 	H9EU    					 
2002050200055	20020502	00055	EU  	2002	5	2	HEEA078648       	1	20020426	G	6420		BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				TAIL ROTOR HUB HAS A WORN BEARING.						1	G	7	1 	3U			 	H9EU    					 
2002050200056	20020502	00056	EU  	2002	5	2	HEEA078649       	1	20020426	G	6420		BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR HUB	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	855PH					3351				TAIL ROTOR HUB HAS BEARINGS DELAMINATED.						1	G	7	1 	3U			 	H9EU    					 
2002052900001	20020529	00001	NE  	2002	5	29	HEEA078701       	1	20020506	G	7600	70BMA01040	ECU             			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					NR 2 ENGINE	FAILED          	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	505PH					760505				RECEIVED MAJOR FAULT ON NR 2 ENGINE. FOUND NR 2 ENGINE ECU FAILED.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002052900010	20020529	00010	GL  	2002	5	29	HEEA078702       	2	20020514	G	7260	23031219	BEARING         		23008586    	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FAILED          	E			HEEA	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	530JC				CAG97610		CAE900110			REMOVED DUE TO ENGINE RAN WITH LOW OIL PRESSURE. NR 3 AND 4 BEARING FAILURE.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002052900013	20020529	00013	GL  	2002	5	29	HEEA078703       	2	20020514	G	7260	230312681	BEARING         		23008586    	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	530JC				CAG97610		CAE900110			REMOVED DUE TO ENGINE RAN WITH LOW OIL PRESSURE.   NR 3 AND 4 BEARING FAILURE.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002052900020	20020529	00020	GL  	2002	5	29	HEEA078704       	2	20020515	G	7250	23053299	TURBINE WHEEL   			BELL  	230   	230         	1182149	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	14UH	1697 				23028	CAE898258			TURBINE REMOVED FOR OVERHAUL.  UPON INSPECTION OF TURBINE PARTS NOTED LIGHT SULFIDATION ON BACK SIDE OF 1ST STAGE WHEEL 	LEADING EDGE BLADES. SCRAPPED.					1	G	7	2 	3U	3	U	NC	H9SW    	E1GL				 
2002052900021	20020529	00021	GL  	2002	5	29	HEEA078705       	2	20020515	G	7240	23064570	LINER           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				WORN NOZZLE FERRULE AND CRACKS IN VARIOUS WELDMENTS.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002052900022	20020529	00022	SW  	2002	5	29	HEEA078706       	1	20020515	G	7600	23071644	ECU             			BELL  	407   	407         	1182206	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				ECU HAS TWO PINS BENT OVER IN FORWARD CONNECTOR PLUG.						1	G	7	1 	3U			O	H2SW    					 
2002052900024	20020529	00024	NE  	2002	5	29	HEEA078707       	2	20020516	G	7200		ENGINE          			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					NACELLE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	971AE	1558 				3230	22072			ENGINE TAKES SEVERAL ATTEMPTS TO START AFTER THE ENGINE IS RUN AND GETS WARMED UP.  STARTS OK WHEN COLD.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002052900027	20020529	00027	EU  	2002	5	29	HEEA078708       	1	20020516	G	7500	9550166140	TRANSDUCER      			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					P3 PRESSURE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	972AE					3234	22087			INTERMITTENT P3 FAILURES WITH AMBER GOVERNOR CAUTION LIGHT COMING ON.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002052900028	20020529	00028	NE  	2002	5	29	HEEA078709       	2	20020516	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH					3248				ENGINE IGNITER WORN.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002052900031	20020529	00031	NE  	2002	5	29	HEEA078710       	1	20020520	G	7810	0401287410	EXHAUST STACK   			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH					760505				LT ENGINE EXHAUST STACK IS CRACKED.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002052900033	20020529	00033		2002	5	29	HEEA078711       	4	20020520	G	2312	064100900	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4253S					760035				TRANSCEIVER RECEIVES GARBLED. PERFORMED PRELIMINARY INSPECTION.  FOUND RECEIVER VERY WEAK.  REALIGNED RECEIVER.  NO HELP	.  FOUND SEVERAL INCORRECT VOLTAGES IN IF AND DETECTOR CIRCUITS.  SWAPPED CR309 AND CR310 DIODES AND C323 AND C324 CAPAC	ITORS.  REALIGNED PRESELECTOR AND I F, NO HELP.  SWAPPED C376 CAPACITOR.  ALIGNED I F,  NO HELP.  REALIGNED PRESELECTOR 	AND I F AND ADJUSTED R333 IF AGC.  RECEIVER SENSITIVITY GOOD, BUT COULD NOT ADJUST SQUELCH TO SPECS.  REPLACED I303 IC A	ND RECEIVER NOW RECEIVING STRONG.  REPLACED Q304 RESISTOR.  REPLACED I304 IC CHIP AND REALIGNED RECEIVER.  REPAIRED.  BE	NCH CHECK GOOD.	1	G	7	2 	3U			 	H1NE    					 
2002052900036	20020529	00036	NE  	2002	5	29	HEEA078712       	1	20020520	G	2510	1S20B25A4X27	INERTIA REEL    			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	792CH					760193				PILOT AND COPILOT INERTIA REEL WEBBING DETERIORATED. REPLACED WITH SERVICEABLE ASSEMBLIES.						1	G	7	2 	3U			 	H1NE    					 
2002052900037	20020529	00037	GL  	2002	5	29	HEEA078713       	2	20020520	G	7320	23007827	VALVE           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				SOLENOID VALVE STUCK OPEN. REPLACED WITH SERVICEABLE VALVE.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002052900038	20020529	00038	GL  	2002	5	29	HEEA078714       	2	20020520	G	7320	25490925	FUEL CONTROL    			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR 2 ENGINE	SURGES          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V	1689 				760158	CAE890432S			NR 2 ENGINE SURGES. TESTED UNIT AS RECEIVED AND COULD NOT DUPLICATE PROBLEM.  UNIT TESTED SATISFACTORY.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002052900041	20020529	00041	NE  	2002	5	29	HEEA078715       	2	20020520	G	7200	70BMA01080	ECU             			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH					760505				ECU FAULT. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002052900045	20020529	00045	NE  	2002	5	29	HEEA078716       	1	20020520	G	6230	SB5200103	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	913UK					760276				SWASHPLATE BEARING HAS WORN TEFLON. REPLACED WITH SERVICEABLE BEARINGS.						1	G	7	2 	3U			 	H1NE    					 
2002052900046	20020529	00046	NE  	2002	5	29	HEEA078717       	1	20020520	G	6230	SB5200102	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				SWASHPLATE BUSHING WORN. REPLACED WITH SERVICEABLE BEARINGS.						1	G	7	2 	3U			 	H1NE    					 
2002052900048	20020529	00048	NE  	2002	5	29	HEEA078718       	1	20020520	G	6230	SB5200103	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	761PH					760224				SWASHPLATE BEARING HAS WORN TEFLON. REPLACED WITH SERVICEABLE BEARINGS.						1	G	7	2 	3U			 	H1NE    					 
2002052900049	20020529	00049	NE  	2002	5	29	HEEA078719       	1	20020520	G	6210	7615009100051A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ	14894				760231				BLADE SKIN CRACKED ON LOWER SURFACE NEAR THE TIP OF TIP RIB.						1	G	7	2 	3U			 	H1NE    					 
2002052900052	20020529	00052	NE  	2002	5	29	HEEA078720       	1	20020520	G	6210	7615009100051A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S	13778				760035				NICKEL LEADING EDGE STRIP IS COMING OFF AFTER BEING REPAIRED ONLY 378:25 HOURS.						1	G	7	2 	3U			 	H1NE    					 
2002052900053	20020529	00053	NE  	2002	5	29	HEEA078721       	1	20020520	G	6210	7615009100053	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		5266 								MAIN ROTOR BLADE MISMANUFACTURED, UNABLE TO BALANCE.  TOO HEAVY.						1	G	7	2 	3U			 	H1NE    					 
2002052900055	20020529	00055	NE  	2002	5	29	HEEA078722       	1	20020520	G	3020		ANTI-ICE SYSTEM 			SKRSKY	S76   	S76A        	8143006	NE  										BELLMOUTH INTAKE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	792CH					760193				BELLMOUTH HEATS UP BUT WILL NOT EXTINGUISH ANTI ICE CAUTION LIGHT. SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2002052900056	20020529	00056	NE  	2002	5	29	HEEA078723       	1	20020520	G	6420		BUSHING         			SKRSKY	S76   	S76A        	8143006	NE  										FRICTION LEVER	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				ROLL FRICTION ASSEMBLY LEVERS WORN AND BUSHINGS LOOSE. SCRAPPED AND REPLACED WITH SERVICEABLE LEVER.						1	G	7	2 	3U			 	H1NE    					 
2002052900057	20020529	00057	NE  	2002	5	29	HEEA078724       	1	20020520	G	6720	7640003210043	BELLCRANK       			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				TAIL ROTOR BELLCRANK HAS WORN BEARINGS. REPLACED WITH SERVICEABLE BELLCRANK.						1	G	7	2 	3U			 	H1NE    					 
2002052900058	20020529	00058	NE  	2002	5	29	HEEA078725       	1	20020520	G	3110		LIGHT           			SKRSKY	S76   	S76A        	8143006	NE  										TRIPLE TACH	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911MJ					760231				PILOT TRIPLE TACH INSTRUMENT LIGHT INTERMITTENT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2002052900059	20020529	00059	NE  	2002	5	29	HEEA078726       	1	20020520	G	7722	7645001076107	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				INDICATOR READS 100 - 150 DEGREES HIGH THROUGHOUT ITS OPERATIONAL RANGE.						1	G	7	2 	3U			 	H1NE    					 
2002052900060	20020529	00060	NE  	2002	5	29	HEEA078727       	1	20020520	G	7714	7645001076110	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE N1	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	792CH					760193				AFTER START, PILOT N1 INDICATOR DROPPED TO ZERO AND STAYED THERE.						1	G	7	2 	3U			 	H1NE    					 
2002052900061	20020529	00061	NE  	2002	5	29	HEEA078728       	1	20020520	G	2841	7645001078103	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										FUEL QTY	INOPERATIVE     	E			HEEA	K				NONE                    				L	W		NO TEST                   	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	03	5435V					760158				INDICATOR BAD FROM STOCK.  NO INDICATION OR NEEDLE MOVEMENT.						1	G	7	2 	3U			 	H1NE    					 
2002052900062	20020529	00062	NE  	2002	5	29	HEEA078729       	1	20020520	G	2121	7650007901103	BLOWER          			SKRSKY	S76   	S76A        	8143006	NE  										CABIN AIR	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	199CH					760261				VENT BLOWER INOPERATIVE.						1	G	7	2 	3U			 	H1NE    					 
2002052900063	20020529	00063	NE  	2002	5	29	HEEA078730       	1	20020520	G	2121	7650007901103	BLOWER          			SKRSKY	S76   	S76A        	8143006	NE  										CABIN AIR	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5435V					760158				VENT BLOWER INOPERATIVE.						1	G	7	2 	3U			 	H1NE    					 
2002052900064	20020529	00064	NE  	2002	5	29	HEEA078731       	1	20020520	G	6321	7665009803103	POWERPACK       			SKRSKY	S76   	S76A        	8143006	NE  										ROTOR BRAKE	MALFUNCTIONED   	E			HEEA	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	03	15460					760223				ROTOR BRAKE CAUTION LIGHT DOES NOT ILLUMINATE WHEN ROTOR BRAKE IS SWITCHED ON. RETURNED TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2002052900066	20020529	00066	NE  	2002	5	29	HEEA078732       	1	20020520	G	6730	7665009807101	SERVO           			SKRSKY	S76   	S76C        	8143008	NE  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH					760505				MAIN ROTOR SERVO HAS WORN UPPER BEARING. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2002052900067	20020529	00067		2002	5	29	HEEA078733       	4	20020520	G	3442	78806059008	DISPLAY         			SKRSKY	S76   	S76A        	8143006	NE  										WX RADAR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1546G					760076				WEATHER RADAR DISPLAY PRODUCING DOUBLE IMAGING.						1	G	7	2 	3U			 	H1NE    					 
2002052900069	20020529	00069		2002	5	29	HEEA078734       	4	20020520	G	3120	811B	CLOCK           			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	792CH					760193				PILOT CLOCK WILL NOT KEEP TIME. REPLACED WITH SERVICEABLE CLOCK.						1	G	7	2 	3U			 	H1NE    					 
2002052900070	20020529	00070		2002	5	29	HEEA078735       	4	20020520	G	3457		SCREW           			SKRSKY	S76   	S76A        	8143006	NE  										GPS ON/OFF KNOB	STRIPPED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				INTERMITTENTLY LOSES RAIM. PERFORMED PRELIMINARY INSPECTION.  COULD NOT DUPLICATE PROBLEM.  FOUND SEVERAL BUTTONS UNREAD	ABLE AND FOUND SET SCREW ON/OFF KNOB STRIPPED.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	3U			 	H1NE    					 
2002052900071	20020529	00071		2002	5	29	HEEA078736       	4	20020520	G	3457	8143902240B	GPS             			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911UK					760275				WILL NOT HOLD COORDINATES. PERFORMED PRELIMINARY INSPECTION.  FOUND BATTERY DEAD AND CORROSION ON BOARD NEAR BATTERY.  R	EMOVED CORROSION FROM BOARD.  FOUND L212 COIL BROKEN.  ALSO DISPLAY IS BLURRY AND MISSING ON/OFF KNOB.  SENT TO ASM FREE	FLIGHT FOR INSPECTION AND REPAIR.				1	G	7	2 	3U			 	H1NE    					 
2002052900073	20020529	00073		2002	5	29	HEEA078737       	4	20020520	G	3457	8144002241D	GPS             			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	505PH					760505				GPS FALLS OFF LINE.						1	G	7	2 	3U			NC	H1NE    					 
2002052900074	20020529	00074	NE  	2002	5	29	HEEA078738       	1	20020520	G	2110	JBS2014	COMPRESSOR      			SKRSKY	S76   	S76A        	8143006	NE  										AIR CONDITIONER	DAMAGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	792CH					760193				INSUFFICIENT COOLING FROM AIR CONDITIONER SYSTEM.  EQUAL PRESSURES READ ON HIGH AND LOW SIDES. REPAIRED.						1	G	7	2 	3U			 	H1NE    					 
2002052900075	20020529	00075		2002	5	29	HEEA078740       	4	20020520	G	3442	MI5852013	DISPLAY         			SKRSKY	S76   	S76A        	8143006	NE  										WX RADAR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4253S					760035				WEATHER RADAR SYSTEM HAS NO TEST PATTERN ON DISPLAY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2002052900076	20020529	00076		2002	5	29	HEEA078741       	4	20020520	G	3442	MI5852013	DISPLAY         			SKRSKY	S76   	S76A        	8143006	NE  										WX RADAR	DISTORTED       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	22342					760096				SCREEN DISTORTED AFTER 10 MINUTES OF OPERATION. COULD NOT DUPLICATE PROBLEM.  BENCH CHECK GOOD.						1	G	7	2 	3U			 	H1NE    					 
2002052900077	20020529	00077		2002	5	29	HEEA078742       	4	20020520	G	2340	PHI20004	MIXER BOX       			SKRSKY	S76   	S76A        	8143006	NE  										CABIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1545X					760050				BLEED OVER TO OTHER CHANNELS OF MIXER BOX WITHOUT SWITCH SELECTED. PERFORMED PRELIMINARY INSPECTION.  FOUND SWITCH S1 AN	D SELECTOR KNOB BAD.  REPLACED AND REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	3U			 	H1NE    					 
2002052900078	20020529	00078		2002	5	29	HEEA078743       	4	20020524	G	3457	8143902240B	GPS             			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4253S					760035				GPS DOES NOT DRIVE YELLOW NEEDLE ON HSI IN CAL MODE.  UNABLE TO CHANGE FUEL FROM GALLONS TO POUNDS. TO BE SENT TO VENDOR	 FOR REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2002052900079	20020529	00079		2002	5	29	HEEA078744       	4	20020524	G	2350	AA38300	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										ICS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4253S					760035				ICS AMPLIFIER INOPERATIVE. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2002052900080	20020529	00080	SW  	2002	5	29	HEEA078747       	1	20020501	G	6710	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										WOULD NOT COMPLETE MONITOR TEST AFTER INSTALLATION.  WOULD MOVE SLOW OR VERY LITTLE.						2	G	7	2 	4U			 	H10SW   					 
2002052900081	20020529	00081	SW  	2002	5	29	HEEA078748       	1	20020501	G	6710	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										MAIN ROTOR ACTUATOR WON'T COMPLETE TEST.						2	G	7	2 	4U			 	H10SW   					 
2002052900082	20020529	00082		2002	5	29	HEEA078749       	4	20020501	G	2210	214074303115	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	03										ACTUATOR ROLL DROPS OFF DURING FLIGHT.						2	G	7	2 	4U			 	H10SW   					 
2002052900084	20020529	00084	SW  	2002	5	29	HEEA078750       	1	20020501	G	2932	222375019105	TRANSMITTER     			BELL  	222   	222         	1182122	SW  										HYD INDICATOR	READS LOW       	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03										HYDRAULIC PRESSURE INDICATOR READS LOW PRESSURE. REPLACED HYD PRESSURE INDICATOR TRANSMITTER.						1	G	7	2 	3U			 	H9SW    					 
2002052900085	20020529	00085	SW  	2002	5	29	HEEA078751       	1	20020501	G	5260		ARM             			BELL  	412   	412         	1182202	SW  										STEP ACTUATOR	CORRODED        	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03					RT34006					STEP ACTUATOR HAS A CORRODED ARM.						1	G	7	2 	4U			 	H4SW    					 
2002052900086	20020529	00086	SW  	2002	5	29	HEEA078752       	1	20020501	G	7120	206064107101	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8590X					51494				IN SERVICE FOR 11 1/2 MONTHS.  REMOVED DUE TO WEAR OF THE BEARING.  ALSO NOTED THE TUBE INSIDE DIAMETER IS MUCH LARGER T	HAT THE FITTING OUTSIDE DIAMETER CREATING A LOOSE FIT BETWEEN THE TWO.  CAUSES THE HI LOC TO BECOME OVERSIZED AND BEYOND	 LIMITS. SCRAPPED ENGINE MOUNT.				1	G	7	1 	3U			 	H2SW    					 
2002052900087	20020529	00087	SW  	2002	5	29	HEEA078753       	1	20020506	G	7120	206064105101	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										ENGINE MOUNT MIS-IDENTIFIED.  P/N SHOULD BE -102.						1	G	7	1 	3U			 	H2SW    					 
2002052900089	20020529	00089		2002	5	29	HEEA078756       	4	20020506	G	3422	060001500	GYRO            			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	407PH					53003				DIRECTIONAL GYRO HEADING FLAP WILL NOT MOVE.						1	G	7	1 	3U			O	H2SW    					 
2002052900090	20020529	00090		2002	5	29	HEEA078757       	4	20020506	G	2312	064105430	TRANSCEIVER     			BELL  	407   	407         	1182206	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	402PH					53159				DOES NOT TRANSMIT. PERFORMED PRELIMINARY INSPECTION AND FOUND CHANNELING KNOBS BENT AND CHANNELING INTERMITTENT.  REPLAC	ED S101 SWITCH, MHZ AND KHZ KNOBS AND WAFER SWITCHES.  CLEANED CHANNELING CONTACTS ON DISPLAY BOARD.  REPAIRED CHANNELIN	G PROBLEM BUT FOUND TRANSMITTER WORKING INTERMITTENTLY.				1	G	7	1 	3U			O	H2SW    					 
2002052900092	20020529	00092		2002	5	29	HEEA078758       	4	20020506	G	3452	066106200	TRANSCEIVER     			BELL  	407   	407         	1182206	SW  										VOR SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	491PH					53386				WOULD NOT TRANSMIT. PERFORMED PRELIMINARY INSPECTION, FOUND V101 BAD, AND R477 BAD.  REPLACED.  REPAIRED.  ADJUSTED TO S	PECS.  BENCH CHECK GOOD.					1	G	7	1 	3U			O	H2SW    					 
2002052900093	20020529	00093	SW  	2002	5	29	HEEA078759       	1	20020506	G	3212	1100891S	TEE FITTING     			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				CORROSION BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002052900094	20020529	00094		2002	5	29	HEEA078760       	4	20020506	G	3457	13824120234	GPS             			BELL  	407   	407         	1182206	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	721PH					53278				GPS RECEIVER HAS NO DISPLAY.						1	G	7	1 	3U			O	H2SW    					 
2002052900095	20020529	00095	SW  	2002	5	29	HEEA078765       	1	20020506	G	3270	206020110103	SKID            			BELL  	407   	407         	1182206	SW  										TAIL	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				TAIL SKID ASSY IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002052900096	20020529	00096	SW  	2002	5	29	HEEA078766       	1	20020506	G	5302		STRUCTURE       			BELL  	407   	407         	1182206	SW  										TAIL BOOM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				TAIL BOOM HAS CORROSION AT TOP CAP AND LOWER STRINGER MOUNT AREAS.						1	G	7	1 	3U			O	H2SW    					 
2002052900097	20020529	00097	SW  	2002	5	29	HEEA078767       	1	20020506	G	3270	206050129001	SHOE            			BELL  	407   	407         	1182206	SW  										TAIL SKID	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				TAIL SKID SHOE WELDED BEADS ARE WORN.						1	G	7	1 	3U			O	H2SW    					 
2002052900099	20020529	00099	SW  	2002	5	29	HEEA078768       	1	20020506	G	3212	206050247101	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				EMERGENCY FLOAT COVER IS WORN, TORN AND DIRTY.						1	G	7	1 	3U			O	H2SW    					 
2002052900100	20020529	00100	SW  	2002	5	29	HEEA078769       	1	20020506	G	3212	206050247132	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				EMERGENCY FLOAT COVER HAS A TORN END FLAP.						1	G	7	1 	3U			O	H2SW    					 
2002052900101	20020529	00101	SW  	2002	5	29	HEEA078770       	1	20020507	G	3212	206050247135	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				EMERGENCY FLOAT COVER IS DETERIORATED.  END CAPS TORN.						1	G	7	1 	3U			O	H2SW    					 
2002052900103	20020529	00103	SW  	2002	5	29	HEEA078771       	1	20020507	G	3212	206050247137	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				EMERGENCY FLOAT COVER IS TORN.						1	G	7	1 	3U			O	H2SW    					 
2002052900105	20020529	00105	SW  	2002	5	29	HEEA078772       	1	20020507	G	3246	206053184121	SKID            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				SKID TUBE HAS CORROSION OUT OF LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002052900106	20020529	00106	SW  	2002	5	29	HEEA078774       	1	20020507	G	3246	206053184122	SKID            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				SKID TUBE HAS CORROSION OUT OF LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002052900107	20020529	00107	SW  	2002	5	29	HEEA078775       	1	20020507	G	3246	206053184122	SKID            			BELL  	407   	407         	1182206	SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				WORN ON AFT SECTION OF SKID TUBE.						1	G	7	1 	3U			O	H2SW    					 
2002052900108	20020529	00108	SW  	2002	5	29	HEEA078776       	1	20020507	G	6510	206061432119	BLOWER          			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				BLOWER HAS A CRACK NEAR TOP LEFT HAND SECTION.						1	G	7	1 	3U			O	H2SW    					 
2002052900109	20020529	00109	SW  	2002	5	29	HEEA078777       	1	20020507	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				TAIL ROTOR BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002052900110	20020529	00110	SW  	2002	5	29	HEEA078778       	1	20020507	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				TAIL ROTOR BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002052900111	20020529	00111	SW  	2002	5	29	HEEA078780       	1	20020507	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH	3443 			97332	53277				STARTER GEN HAS BRUSHES WORN, BRUSH PIGTAILS HAVE BROKEN STRANDS, ONE FAN COVER SCREW HEAD CORRODED OFF.						1	G	7	1 	3U			O	H2SW    					 
2002052900112	20020529	00112	SW  	2002	5	29	HEEA078781       	1	20020507	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	741PH	2741 				53457				STARTER GEN HAS BRUSHES WORN.						1	G	7	1 	3U			O	H2SW    					 
2002052900113	20020529	00113	SW  	2002	5	29	HEEA078782       	1	20020507	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	2493 			98136	53159				STARTER GEN HAS BRUSHES WORN.						1	G	7	1 	3U			O	H2SW    					 
2002052900114	20020529	00114	SW  	2002	5	29	HEEA078783       	1	20020507	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	1529 			98262	53199				STARTER GEN HAS BRUSHES WORN.						1	G	7	1 	3U			O	H2SW    					 
2002052900120	20020529	00120	SW  	2002	5	29	HEEA078788       	1	20020507	G	2820	206064263101	LINE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				FUEL LINE HAS CORROSION AROUND SLEEVES.						1	G	7	1 	3U			O	H2SW    					 
2002052900121	20020529	00121	SW  	2002	5	29	HEEA078789       	1	20020507	G	2820	206064264101	LINE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				FUEL LINE HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002052900123	20020529	00123	SW  	2002	5	29	HEEA078790       	1	20020507	G	7921	206064515001	SUPPORT         			BELL  	407   	407         	1182206	SW  										OIL COOLER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				OIL COOLER SUPPORT ASSY IS CRACKED IN TWO PLACES.						1	G	7	1 	3U			O	H2SW    					 
2002052900126	20020529	00126	SW  	2002	5	29	HEEA078792       	1	20020507	G	5210	206064819005S	SKIN            			BELL  	407   	407         	1182206	SW  										CREW DOOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH					53378				SKIN ON CREW DOOR HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002052900127	20020529	00127	SW  	2002	5	29	HEEA078793       	1	20020507	G	5210	206064819005S	SKIN            			BELL  	407   	407         	1182206	SW  										CREW DOOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH					53378				SKIN ON CREW DOOR HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002052900135	20020529	00135	SW  	2002	5	29	HEEA078795       	1	20020507	G	7160	206064819159	COWLING         			BELL  	407   	407         	1182206	SW  										AIR INLET	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				COWLING HAS CORROSION AND CRACKED IN SEVERAL PLACES.						1	G	7	1 	3U			O	H2SW    					 
2002052900165	20020529	00165	SW  	2002	5	29	HEEA078798       	1	20020507	G	7160	206064912103	SEAL            			BELL  	407   	407         	1182206	SW  										COWLING	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				COWLING SEAL TORN. SCRAPPED AND REPLACED WITH SERVICEABLE SEAL.						1	G	7	1 	3U			O	H2SW    					 
2002053000001	20020530	00001	SW  	2002	5	30	HEEA078799       	1	20020507	G	2120	206070471010	NOZZLE          			BELL  	407   	407         	1182206	SW  										WINDSHIELD DEFOG	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				WINDSHIELD DE-FOG NOZZLE IS CRACKED AT MOUNTING HOLE.						1	G	7	1 	3U			O	H2SW    					 
2002053000002	20020530	00002	SW  	2002	5	30	HEEA078801       	1	20020507	G	2810	206362002103	CAP             			BELL  	407   	407         	1182206	SW  										FUEL STORAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				TABS AROUND OUTER EDGE OF FUEL CAP MISSING.						1	G	7	1 	3U			O	H2SW    					 
2002053000005	20020530	00005	SW  	2002	5	30	HEEA078802       	1	20020507	G	6320	214040805001	THERMOSWITCH    			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				MAIN ROTOR GEARBOX THERMOSWITCH DAMAGED, STUD TURNS FREELY IN HOUSING.						1	G	7	1 	3U			O	H2SW    					 
2002053000017	20020530	00017	SW  	2002	5	30	HEEA078803       	1	20020507	G	2560	222320823129	SEAT BELT       			BELL  	407   	407         	1182206	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				CREW SEAT BELTS FRAYED AND CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002053000019	20020530	00019	SW  	2002	5	30	HEEA078804       	1	20020507	G	2560	222320823130	SEAT BELT       			BELL  	407   	407         	1182206	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				CREW SEAT BELTS FRAYED AND CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002053000023	20020530	00023	GL  	2002	5	30	HEEA078805       	2	20020507	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				ENGINE POWER OSCILLATIONS AT HIGH POWER SETTINGS. REPLACED WITH SERVICEABLE BLEED VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000038	20020530	00038	GL  	2002	5	30	HEEA078806       	2	20020507	G	7510	23007827	VALVE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				VALVE INOPERATIVE. REPLACED WITH SERVICEABLE VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000040	20020530	00040	GL  	2002	5	30	HEEA078807       	2	20020507	G	7510	23007827	VALVE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				VALVE STUCK IN ON POSITION. REPLACED WITH SERVICEABLE VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000042	20020530	00042	GL  	2002	5	30	HEEA078808       	2	20020507	G	7321	23054164	SENSOR          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				SENSOR PICKUP CAUSING NP1, NP1 RATE, OS, NPOS AND NPD FAULTS TO FADED SYSTEM. REPLACED WITH SERVICEABLE SENSOR PICKUP AS	SY.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000043	20020530	00043	GL  	2002	5	30	HEEA078809       	2	20020507	G	7310	23056649	HOSE            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					FUEL SYSTEM	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				FIRE SHIELD TO FUEL NOZZLE HOSE KINKED. REPLACED WITH SERVICEABLE HOSE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000045	20020530	00045	GL  	2002	5	30	HEEA078810       	2	20020507	G	7310	23060435	LINE            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				FUEL LINE LEAKING. REPLACED WITH SERVICEABLE LINE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000047	20020530	00047	GL  	2002	5	30	HEEA078811       	2	20020507	G	7412	23064130	IGNITER BOX     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	490PH					53378				IGNITOR BOX WEAK.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000048	20020530	00048	SW  	2002	5	30	HEEA078812       	1	20020507	G	2821	23066697	FILTER          			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				FILTER BYPASSED. SCRAPPED LOCALLY AND REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U			O	H2SW    					 
2002053000051	20020530	00051	SW  	2002	5	30	HEEA078813       	1	20020507	G	7722	23071644	ECU             			BELL  	407   	407         	1182206	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				NP AND OVERSPEED SENSOR FAILURES (FADEC FAULT & DEGRADE LIGHTS) REPLACED WITH SERVICEABLE ECU.						1	G	7	1 	3U			O	H2SW    					 
2002053000052	20020530	00052	SW  	2002	5	30	HEEA078814       	1	20020507	G	7722	23071644	ECU             			BELL  	407   	407         	1182206	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				BOTTOM PLATE OPEN TO SEARCH FOR MOISTURE.						1	G	7	1 	3U			O	H2SW    					 
2002053000054	20020530	00054	GL  	2002	5	30	HEEA078815       	2	20020507	G	7320	23072725	HMU             			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					FUEL CONTROL	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	493PH					53393				HMU HAS METERING VALVE CIRCUIT FAULT. REPLACED WITH SERVICEABLE HMU.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000055	20020530	00055	SW  	2002	5	30	HEEA078816       	1	20020507	G	7722	23072790	ECU             			BELL  	407   	407         	1182206	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	719PH					53266				FADEC FAULT AND FADEC DEGRADE LIGHTS ILLUMINATED.  CLEARED FAULT. REPLACED WITH SERVICEABLE ECU.						1	G	7	1 	3U			O	H2SW    					 
2002053000059	20020530	00059	SW  	2002	5	30	HEEA078819       	1	20020507	G	3201	400052009101	BOLT            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				MLG ROCKER BEAM BOLT PITTED.						1	G	7	1 	3U			O	H2SW    					 
2002053000060	20020530	00060	SW  	2002	5	30	HEEA078820       	1	20020507	G	6210	406010120101	BOLT            			BELL  	407   	407         	1182206	SW  										M/R BLADES	FRETTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				BOLT HAS FRETTING ON SHANK.						1	G	7	1 	3U			O	H2SW    					 
2002053000062	20020530	00062	SW  	2002	5	30	HEEA078821       	1	20020507	G	6230	406010413117	PITCH LINK      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				PITCH LINK HAS CORROSION ON TUBE NEAR COLLAR.						1	G	7	1 	3U			O	H2SW    					 
2002053000063	20020530	00063	SW  	2002	5	30	HEEA078822       	1	20020507	G	6710		PAD             			BELL  	407   	407         	1182206	SW  										LEVER ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LEVER ASSY HAS PHENOLIC WEAR PAD MISSING TWO SIDES.						1	G	7	1 	3U			O	H2SW    					 
2002053000064	20020530	00064	SW  	2002	5	30	HEEA078823       	1	20020507	G	6230	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				CORROSION AROUND BASE MOUNT AREA LIGHTLY PAINTED AREA.						1	G	7	1 	3U			O	H2SW    					 
2002053000065	20020530	00065	SW  	2002	5	30	HEEA078825       	1	20020507	G	6230		BUSHING         			BELL  	407   	407         	1182206	SW  										LINK ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH				AFS2265	53198				LINK ASSY HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002053000066	20020530	00066	SW  	2002	5	30	HEEA078826       	1	20020507	G	6230	406010427109	GIMBAL RING     			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				GIMBAL RING HAS CORROSION AROUND MOUNT PINS.						1	G	7	1 	3U			O	H2SW    					 
2002053000068	20020530	00068	SW  	2002	5	30	HEEA078827       	1	20020507	G	6220	406010428109	BUSHING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR HUB	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				MAIN ROTOR HUB BUSHING HAS CORROSION AROUND SPLINE AREA.						1	G	7	1 	3U			O	H2SW    					 
2002053000070	20020530	00070	SW  	2002	5	30	HEEA078828       	1	20020507	G	6710		BUSHING         			BELL  	407   	407         	1182206	SW  										IDLER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH				AFS1179	53386				WORN BUSHING.						1	G	7	1 	3U			O	H2SW    					 
2002053000071	20020530	00071	SW  	2002	5	30	HEEA078829       	1	20020507	G	6220	406012129101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				LINK ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053000072	20020530	00072	SW  	2002	5	30	HEEA078832       	1	20020507	G	6520	406040406109	CASE            			BELL  	407   	407         	1182206	SW  										T/R GEARBOX	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				TAIL ROTOR GEARBOX HAS EXCESSIVE PITTING BETWEEN CHIP DETECTOR AND RIGHT FORWARD MOUNTING STUD.						1	G	7	1 	3U			O	H2SW    					 
2002053000076	20020530	00076	SW  	2002	5	30	HEEA078833       	1	20020507	G	6510	406040450101	BREATHER TUBE   			BELL  	407   	407         	1182206	SW  										T/R DRIVESHAFT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				STEP WORN AROUND OUTSIDE OF FLARE.						1	G	7	1 	3U			O	H2SW    					 
2002053000077	20020530	00077	SW  	2002	5	30	HEEA078836       	1	20020507	G	6300		BEARING         			BELL  	407   	407         	1182206	SW  										UNIVERSAL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH				RXFS5555	53188				UNIVERSAL HAS WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002053000078	20020530	00078	SW  	2002	5	30	HEEA078837       	1	20020507	G	6300		BEARING         			BELL  	407   	407         	1182206	SW  										UNIVERSAL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH				RXFS5989	53398				UNIVERSAL HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002053000080	20020530	00080	SW  	2002	5	30	HEEA078838       	1	20020507	G	6720		BEARING         			BELL  	407   	407         	1182206	SW  										LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH				NHFS5192	53327				LINK ASSY HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002053000083	20020530	00083	SW  	2002	5	30	HEEA078839       	1	20020507	G	6720		BEARING         			BELL  	407   	407         	1182206	SW  										LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH				NHFS5246	53327				LINK ASSY HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002053000086	20020530	00086	SW  	2002	5	30	HEEA078840       	1	20020507	G	6720		BEARING RACE    			BELL  	407   	407         	1182206	SW  										LINK	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH				NHFS5853	53199				CRACKED AT BEARING HOLE.  CORROSION BLEEDING FROM BEARING RACE.						1	G	7	1 	3U			O	H2SW    					 
2002053000089	20020530	00089	SW  	2002	5	30	HEEA078841       	1	20020507	G	6720		BEARING RACE    			BELL  	407   	407         	1182206	SW  										LINK	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH				NHFS5867	53199				CORROSION BLEEDING FROM BEARING RACE.						1	G	7	1 	3U			O	H2SW    					 
2002053000090	20020530	00090	SW  	2002	5	30	HEEA078842       	1	20020507	G	6320	406340100101	PUMP            			BELL  	407   	407         	1182206	SW  										M/R XMSN OIL	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH					53461				TRANSMISSION OIL PUMP LEAKING PAST INTERNAL SEAL.						1	G	7	1 	3U			O	H2SW    					 
2002053000091	20020530	00091	GL  	2002	5	30	HEEA078843       	2	20020507	G	7230		BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					TUBE ASSY.	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				BEARINGS WORN.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053000092	20020530	00092	SW  	2002	5	30	HEEA078845       	1	20020507	G	6220		BEARING         			BELL  	407   	407         	1182206	SW  										IDLER ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH				CT427	53199				IDLER ASSY HAS BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053000093	20020530	00093	SW  	2002	5	30	HEEA078846       	1	20020507	G	6220		BEARING         			BELL  	407   	407         	1182206	SW  										IDLER ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				IDLER ASSY HAS BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053000094	20020530	00094	SW  	2002	5	30	HEEA078847       	1	20020507	G	6220	407001524105	BELLCRANK       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				MAIN ROTOR HEAD BELLCRANK HAS THE RUBBER BUMPER UNBONDED.						1	G	7	1 	3U			O	H2SW    					 
2002053000095	20020530	00095	SW  	2002	5	30	HEEA078848       	1	20020507	G	6220	407001524105	BELLCRANK       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR HEAD	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				MAIN ROTOR HEAD BELLCRANK HAS THE RUBBER BUMPER UNBONDED.						1	G	7	1 	3U			O	H2SW    					 
2002053000096	20020530	00096	SW  	2002	5	30	HEEA078849       	1	20020507	G	6220	407001528101	BELLCRANK       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR HEAD	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				MAIN ROTOR BELLCRANK HAS THE RUBBER BUMPER UNBONDED.						1	G	7	1 	3U			O	H2SW    					 
2002053000098	20020530	00098	SW  	2002	5	30	HEEA078850       	1	20020507	G	6720	407001732101	BELLCRANK       			BELL  	407   	407         	1182206	SW  										T/R CONTROL	WORN            	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				TAIL ROTOR CONTROL BELLCRANK IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053000099	20020530	00099	SW  	2002	5	30	HEEA078851       	1	20020507	G	6220	407010100115FM	HUB             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	3369 				53038				MAIN ROTOR HUB IS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002053000100	20020530	00100	SW  	2002	5	30	HEEA078852       	1	20020507	G	6220		BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR BLADE	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH				A289	53198				MAIN ROTOR HUB HAS A SHEAR BEARING ON ORANGE BLADE SEPARATED.						1	G	7	1 	3U			O	H2SW    					 
2002053000102	20020530	00102	SW  	2002	5	30	HEEA078854       	1	20020507	G	6220	407010150103	FRAHM           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR HUB	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				FRAHM ASSY HAS CORROSION AROUND SPRING ACCESS PLATES AND CAP NUTPLATES.						1	G	7	1 	3U			O	H2SW    					 
2002053000105	20020530	00105	SW  	2002	5	30	HEEA078855       	1	20020507	G	6300	407010221101	STOP            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				MAIN ROTOR STOPS WORN, TORN, DELAMINATED.						1	G	7	1 	3U			O	H2SW    					 
2002053000109	20020530	00109	SW  	2002	5	30	HEEA078856       	1	20020507	G	6220	407010221101	STOP            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				MAIN ROTOR STOP WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053000126	20020530	00126	SW  	2002	5	30	HEEA078860       	1	20020507	G	6420	407312100101	BEARING         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				BEARING HAS WORN ELASTOMER.						1	G	7	1 	3U			O	H2SW    					 
2002053000127	20020530	00127	SW  	2002	5	30	HEEA078861       	1	20020507	G	6420		BEARING         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				BEARING HAS WORN ELASTOMER.						1	G	7	1 	3U			O	H2SW    					 
2002053000128	20020530	00128	SW  	2002	5	30	HEEA078862       	1	20020507	G	6410		BLADE           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				BLADE HAS CRACK IN ROOT END, INTERIOR OF LEADING EDGE.						1	G	7	1 	3U			O	H2SW    					 
2002053000129	20020530	00129	SW  	2002	5	30	HEEA078863       	1	20020507	G	6420	407312100101	BEARING         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	741PH					53457				BEARING BELOW NOMINAL LENGTH.						1	G	7	1 	3U			O	H2SW    					 
2002053000130	20020530	00130	SW  	2002	5	30	HEEA078864       	1	20020507	G	5610	407030115123	WINDSHIELD      			BELL  	407   	407         	1182206	SW  										COCKPIT	CRAZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				WINDSHEILD CRAZED.						1	G	7	1 	3U			O	H2SW    					 
2002053000131	20020530	00131	SW  	2002	5	30	HEEA078865       	1	20020507	G	5610	407030115125	WINDSHIELD      			BELL  	407   	407         	1182206	SW  										COCKPIT	CRAZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				WINDSHIELD CRAZED.						1	G	7	1 	3U			O	H2SW    					 
2002053000132	20020530	00132	SW  	2002	5	30	HEEA078866       	1	20020507	G	5610	407030115125	WINDSHIELD      			BELL  	407   	407         	1182206	SW  										COCKPIT	CRAZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				WINDSHIELD CRAZED.						1	G	7	1 	3U			O	H2SW    					 
2002053000133	20020530	00133	SW  	2002	5	30	HEEA078867       	1	20020507	G	5610	407030115125	WINDSHIELD      			BELL  	407   	407         	1182206	SW  										COCKPIT	CRAZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				WINDSHIELD CRAZED.						1	G	7	1 	3U			O	H2SW    					 
2002053000134	20020530	00134	SW  	2002	5	30	HEEA078868       	1	20020507	G	5610	407030118103	CHIN BUBBLE     			BELL  	407   	407         	1182206	SW  										COCKPIT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				CHIN BUBBLE CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002053000135	20020530	00135	SW  	2002	5	30	HEEA078869       	1	20020507	G	5610	407030118105	CHIN BUBBLE     			BELL  	407   	407         	1182206	SW  										COCKPIT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				CHIN BUBBLE CRACKED AT OUTBOARD CORNER.						1	G	7	1 	3U			O	H2SW    					 
2002053000137	20020530	00137	SW  	2002	5	30	HEEA078871       	1	20020507	G	5610	407030403116	WINDOW          			BELL  	407   	407         	1182206	SW  										COCKPIT	CRAZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				SKYLIGHT CRAZED.						1	G	7	1 	3U			O	H2SW    					 
2002053100001	20020531	00001	SW  	2002	5	31	HEEA078872       	1	20020507	G	5630	407030607101	WINDOW          			BELL  	407   	407         	1182206	SW  										LITTER DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				LITTER DOOR WINDOW CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002053100002	20020531	00002	SW  	2002	5	31	HEEA078873       	1	20020507	G	5321	407030713113	FLOOR PANEL     			BELL  	407   	407         	1182206	SW  										CARGO AREA	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				CARGO FLOOR PANEL SEPARATED/CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002053100003	20020531	00003	SW  	2002	5	31	HEEA078874       	1	20020508	G	7714	407375002103	INDICATOR       			BELL  	407   	407         	1182206	SW  										ENGINE NG	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				FADEC NG2 FAULT AND NG2 CONTINUITY FAULT.						1	G	7	1 	3U			O	H2SW    					 
2002053100004	20020531	00004	GL  	2002	5	31	HEEA078875       	2	20020508	G	7297	407375012101	WIRE HARNESS    			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					FADEC	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				BREAK IN CABLE CAUSING FADEC NG1 FAULT AND NG1 CONTINUITY FAULT.  BREAK IS APPROXIMATELY 3 INCHES FROM ECU CONNECTOR PLU	G.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053100005	20020531	00005	SW  	2002	5	31	HEEA078878       	1	20020510	G	6230	406010428109	BUSHING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH	3142 				53278				MAIN ROTOR BUSHING SET WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053100006	20020531	00006	SW  	2002	5	31	HEEA078879       	1	20020510	G	6720	407001526101	BELLCRANK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	4209 				53038				BELLCRANK ON TAIL ROTOR HAS RUBBER DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2002053100007	20020531	00007	SW  	2002	5	31	HEEA078880       	1	20020510	G	6230	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH	1942 				53386				WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002053100008	20020531	00008	SW  	2002	5	31	HEEA078881       	1	20020510	G	6230	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH	1942 				53386				MAIN ROTOR LINK HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002053100009	20020531	00009	SW  	2002	5	31	HEEA078882       	1	20020510	G	6220	407010100115	HUB             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	VIBRATION       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH	1778 				53397				MAIN ROTOR HUB HAS VERTICAL VIBRATION.						1	G	7	1 	3U			O	H2SW    					 
2002053100010	20020531	00010	SW  	2002	5	31	HEEA078883       	1	20020510	G	6230	406010428109	BUSHING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				MAIN ROTOR HUB HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002053100011	20020531	00011	SW  	2002	5	31	HEEA078884       	1	20020510	G	3213	407050201101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				MLG CROSSTUBE HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002053100012	20020531	00012	SW  	2002	5	31	HEEA078885       	1	20020510	G	7714	407375012101	WIRE HARNESS    			BELL  	407   	407         	1182206	SW  										FADEC	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				FADEC WIRE HARNESS IS OIL SOAKED AND DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2002053100013	20020531	00013	SW  	2002	5	31	HEEA078886       	1	20020510	G	5210	407070620138	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				CREW DOOR PANEL IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002053100014	20020531	00014	SW  	2002	5	31	HEEA078887       	1	20020510	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH					53378				ENGINE MOUNT BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053100015	20020531	00015	SW  	2002	5	31	HEEA078890       	1	20020510	G	6710	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				MAIN ROTOR LINK HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002053100016	20020531	00016	SW  	2002	5	31	HEEA078891       	1	20020510	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				TAIL ROTOR BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002053100017	20020531	00017	SW  	2002	5	31	HEEA078892       	1	20020513	G	6710	406010429101	PIN             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				MAIN ROTOR PIN WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053100018	20020531	00018	SW  	2002	5	31	HEEA078893       	1	20020513	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH	1968 				53266				MAIN ROTOR UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053100019	20020531	00019	SW  	2002	5	31	HEEA078894       	1	20020513	G	6310	407340107101	SHAFT           			BELL  	407   	407         	1182206	SW  										XMSN COUPLING	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2002053100020	20020531	00020	SW  	2002	5	31	HEEA078895       	1	20020513	G	6310	407340108101	ADAPTER         			BELL  	407   	407         	1182206	SW  										XMSN COUPLING	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				TRANSMISSION/ENGINE COUPLING ADAPTER HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2002053100021	20020531	00021	SW  	2002	5	31	HEEA078896       	1	20020513	G	6710	206001396001	SHAFT           			BELL  	407   	407         	1182206	SW  										CYCLIC STICK	STRIPPED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				STRIPPED BARREL NUT ON SHAFT.						1	G	7	1 	3U			O	H2SW    					 
2002053100022	20020531	00022	SW  	2002	5	31	HEEA078897       	1	20020513	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				TAIL ROTOR LINK HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002053100023	20020531	00023	SW  	2002	5	31	HEEA078898       	1	20020513	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										BOOST PUMP	FAILED          	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	724PH					53327				BOOST PUMP CAUTION LIGHT WILL NOT COME ON. REPLACED FAILED PRESSURE SWITCH.						1	G	7	1 	3U			O	H2SW    					 
2002053100024	20020531	00024		2002	5	31	HEEA078899       	4	20020513	G	3120	M803B205VBATT	CLOCK           			BELL  	407   	407         	1182206	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				COCKPIT CLOCK DAMAGED, BATTERY MOUNT CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002053100025	20020531	00025	SW  	2002	5	31	HEEA078900       	1	20020513	G	6520	406040072105	SPLINE ADAPTER  			BELL  	407   	407         	1182206	SW  										T/R GEARBOX	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				SPLINE ADAPTER HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2002053100026	20020531	00026	SW  	2002	5	31	HEEA078901       	1	20020513	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	1182206	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				EXHAUST STACK IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002053100028	20020531	00028	SW  	2002	5	31	HEEA078902       	1	20020513	G	6520	407040330101	SHAFT           			BELL  	407   	407         	1182206	SW  										T/R GEARBOX	PEELING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				PAINT PEELING FROM SHAFT.						1	G	7	1 	3U			O	H2SW    					 
2002053100039	20020531	00039	SW  	2002	5	31	HEEA078903       	1	20020513	G	3210	407030112103	STRAP           			BELL  	407   	407         	1182206	SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				MLG STRAP WORN AND CHAFED BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002053100055	20020531	00055	GL  	2002	5	31	HEEA078904       	2	20020513	G	7230	407070211102	PLENUM          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				PLENUM CRACKED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053100060	20020531	00060	GL  	2002	5	31	HEEA078905       	2	20020513	G	7230	407070211101	PLENUM          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				PLENUM CRACKED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002053100061	20020531	00061	SW  	2002	5	31	HEEA078906       	1	20020513	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         	1182206	SW  										COCKPIT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				RELAY CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002053100062	20020531	00062	SW  	2002	5	31	HEEA078907       	1	20020513	G	3212	206050247135	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				EMERGENCY FLOAT COVER TORN.						1	G	7	1 	3U			O	H2SW    					 
2002053100064	20020531	00064	SW  	2002	5	31	HEEA078908       	1	20020513	G	2820	70079H000D142	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	COLLAPSED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				FUEL HOSE COLLAPSED.						1	G	7	1 	3U			O	H2SW    					 
2002053100065	20020531	00065	SW  	2002	5	31	HEEA078909       	1	20020513	G	2810	F507ST	FUEL CAP        			BELL  	407   	407         	1182206	SW  										FUEL CELL	MISSING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				FUEL CELL CAP MISSING.						1	G	7	1 	3U			O	H2SW    					 
2002053100066	20020531	00066	SW  	2002	5	31	HEEA078910       	1	20020513	G	2432	28SP100	CELL            			BELL  	407   	407         	1182206	SW  										BATTERY	BURNED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				BATTERY CELL BURNED.						1	G	7	1 	3U			O	H2SW    					 
2002053100068	20020531	00068	SW  	2002	5	31	HEEA078911       	1	20020513	G	7710	407375021103	SENSOR          			BELL  	407   	407         	1182206	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	457PH					53147				WARNING HORN ACTIVATED AT 100 PERCENT NR.						1	G	7	1 	3U			O	H2SW    					 
2002053100078	20020531	00078	SW  	2002	5	31	HEEA078912       	1	20020513	G	7100		BEARING         			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2002053100082	20020531	00082	SW  	2002	5	31	HEEA078914       	1	20020513	G	5320	407064807117	SUPPORT         			BELL  	407   	407         	1182206	SW  										FUSELAGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				SUPPORT WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053100083	20020531	00083	SW  	2002	5	31	HEEA078915       	1	20020513	G	5320	407064807119	SUPPORT         			BELL  	407   	407         	1182206	SW  										FUSELAGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				SUPPORT WORN.						1	G	7	1 	3U			O	H2SW    					 
2002053100086	20020531	00086	SW  	2002	5	31	HEEA078916       	1	20020513	G	3213	407050202101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				CORROSION ON CROSSTUBE.						1	G	7	1 	3U			O	H2SW    					 
2002053100087	20020531	00087	SW  	2002	5	31	HEEA078921       	1	20020513	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				TAIL ROTOR DRIVE SHAFT DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002053100089	20020531	00089	SW  	2002	5	31	HEEA078925       	1	20020513	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										IDLER ASSY	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				IDLER ASSY BEARINGS ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002053100090	20020531	00090	SW  	2002	5	31	HEEA078926       	1	20020513	G	5210	206064819005S	DOOR            			BELL  	407   	407         	1182206	SW  										PAX/CREW	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				CORROSION ON DOOR ASSY.						1	G	7	1 	3U			O	H2SW    					 
2002053100102	20020531	00102	SW  	2002	5	31	HEEA078927       	1	20020513	G	3210	400052009101	BOLT            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				MLG BOLT HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002053100103	20020531	00103	SW  	2002	5	31	HEEA078928       	1	20020513	G	5311	206032308121S	FRAME           			BELL  	407   	407         	1182206	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				FRAME CRACKED ABOVE RIGHT HAND UPPER BOLT HOLE.						1	G	7	1 	3U			O	H2SW    					 
2002053100104	20020531	00104	SW  	2002	5	31	HEEA078931       	1	20020514	G	3212	407073848101	BOTTLE          			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				EMERGENCY FLOAT INFLATION BOTTLE HAS CORROSION ON FITTING BETWEEN BOTTLE AND VALVE.						1	G	7	1 	3U			O	H2SW    					 
2002053100106	20020531	00106	SW  	2002	5	31	HEEA078932       	1	20020514	G	6730	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  											FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										ELEVATOR WILL NOT STAY ON LINE.						2	G	7	2 	4U			 	H10SW   					 
2002060400001	20020604	00001		2002	6	4	HEEA078933       	4	20020514	G	2214	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										ELEVATOR	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										ELEVATOR AMPLIFIER WILL NOT MONITOR TEST ON NR 1 SIDE.						2	G	7	2 	4U			 	H10SW   					 
2002060400002	20020604	00002		2002	6	4	HEEA078934       	4	20020514	G	3460	214074108101	TRANSDUCER      			BOLKMS	105   	BO105S      	5626006	EU  										FLT COMPUTER	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										YAW DROPS OFF LINE AND HAS NO RESISTANCE MOVEMENT.						1	G	7	2 	3U			 	H3EU    					 
2002060400003	20020604	00003	SW  	2002	6	4	HEEA078935       	1	20020515	G	6300	407010206103	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				BEARING WEAR AND MAIN ROTOR VIBRATION.						1	G	7	1 	3U			O	H2SW    					 
2002060400004	20020604	00004	SW  	2002	6	4	HEEA078947       	1	20020515	G	2520	407030504103	PANEL           			BELL  	407   	407         	1182206	SW  										PAX SEAT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	2545 				53199				PANEL ON PASSENGER SEAT IS CORROSION BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002060400005	20020604	00005	SW  	2002	6	4	HEEA078948       	1	20020515	G	6510	407340339101	BEARING         		407040302101	BELL  	407   	407         	1182206	SW  										T/R DRIVESHAFT	FAILED          	E			HEEA	O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			SW	03	407PH				A926	53003				BEARING ON TAIL ROTOR DRIVESHAFT OVERHEATED AND FAILED.						1	G	7	1 	3U			O	H2SW    					 
2002060400006	20020604	00006	SW  	2002	6	4	HEEA078949       	1	20020515	G	6510		BEARING         			BELL  	407   	407         	1182206	SW  										T/R DRIVESHAFT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH	2056 				53288				TAIL ROTOR DRIVESHAFT BEARING PRODUCING BLACK GREASE, AND FEELS ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002060400007	20020604	00007	SW  	2002	6	4	HEEA078951       	1	20020515	G	7920	407040623101	LINE            			BELL  	407   	407         	1182206	SW  										OIL DISTRIBUTION	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				OIL LINE HAS CORROSION UNDER SLEEVE AT FITTING.						1	G	7	1 	3U			O	H2SW    					 
2002060400008	20020604	00008	SW  	2002	6	4	HEEA078952       	1	20020515	G	7920	407040623101	LINE            			BELL  	407   	407         	1182206	SW  										OIL DISTRIBUTION	TWISTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				TUBE IS TWISTED ON TOP WHERE IT CONNECTS TO OIL COOLER.						1	G	7	1 	3U			O	H2SW    					 
2002060400009	20020604	00009	SW  	2002	6	4	HEEA078953       	1	20020515	G	7920	407040624101	LINE            			BELL  	407   	407         	1182206	SW  										OIL DISTRIBUTION	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				OIL LINE HAS CORROSION UNDER SLEEVE AT FITTING.						1	G	7	1 	3U			O	H2SW    					 
2002060400010	20020604	00010	SW  	2002	6	4	HEEA078954       	1	20020515	G	3212	407050003105	RETAINER        			BELL  	407   	407         	1182206	SW  										EMERGENY FLOAT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				MLG EMERGENCY FLOAT RETAINER IS CORRODED. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2002060400011	20020604	00011	SW  	2002	6	4	HEEA078955       	1	20020515	G	3213	407050201101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				FWD CROSSTUBE CORRODED AT RT SADDLE ZONE A2 MAXIMUM ALLOWED .005 INCH MEASURED CORROSION .008 INCH.						1	G	7	1 	3U			O	H2SW    					 
2002060400012	20020604	00012	SW  	2002	6	4	HEEA078956       	1	20020515	G	3213	407050201101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				CROSSTUBE IS CORROSION OUT OF LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002060400013	20020604	00013	SW  	2002	6	4	HEEA078957       	1	20020515	G	3213	407050201103	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				CROSSTUBE IS SPREAD ON RT SIDE.						1	G	7	1 	3U			O	H2SW    					 
2002060400014	20020604	00014	SW  	2002	6	4	HEEA078958       	1	20020515	G	3213	407050201103	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				LANDING GEAR CROSSTUBE SPREAD OUT OF LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002060400015	20020604	00015	SW  	2002	6	4	HEEA078959       	1	20020515	G	3213	407050202101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				FOUND PITS OF CORROSION UNDER "T" BOLT AT A DEPTH OF .032. SCRAPPED CROSSTUBE.						1	G	7	1 	3U			O	H2SW    					 
2002060400016	20020604	00016	SW  	2002	6	4	HEEA078967       	1	20020515	G	3213	407050202103	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				LANDING GEAR CROSSTUBE SPREAD OUT OF LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002060400017	20020604	00017	SW  	2002	6	4	HEEA078968       	1	20020515	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				ENGINE MOUNT BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060400018	20020604	00018	SW  	2002	6	4	HEEA078969       	1	20020515	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				ENGINE MOUNT BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060400019	20020604	00019	SW  	2002	6	4	HEEA078970       	1	20020515	G	7920	407062532101	TUBE            			BELL  	407   	407         	1182206	SW  										OIL DISTRIBUTION	DENTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				OIL TUBE DENTED.						1	G	7	1 	3U			O	H2SW    					 
2002060400020	20020604	00020	SW  	2002	6	4	HEEA078971       	1	20020515	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	1182206	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				EXHAUST STACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400021	20020604	00021	SW  	2002	6	4	HEEA078972       	1	20020515	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	1182206	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				EXHAUST STACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400022	20020604	00022	GL  	2002	6	4	HEEA078973       	2	20020515	G	7230	407070211102	PLENUM          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				CRACKED AT BOTTOM AND NUTPLATE BROKE LOOSE FROM PLENUM.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002060400023	20020604	00023	SW  	2002	6	4	HEEA078974       	1	20020515	G	5320	407070620112	PANEL           			BELL  	407   	407         	1182206	SW  										FUSELAGE TRIM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				TRIM PANEL CRACKED IN SEVERAL PLACES.						1	G	7	1 	3U			O	H2SW    					 
2002060400024	20020604	00024	SW  	2002	6	4	HEEA078975       	1	20020515	G	5320	407070620113	PANEL           			BELL  	407   	407         	1182206	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				FUSELAGE PANEL CRACKED IN SEVERAL PLACES.						1	G	7	1 	3U			O	H2SW    					 
2002060400025	20020604	00025	SW  	2002	6	4	HEEA078976       	1	20020515	G	5320	407070620155	PANEL           			BELL  	407   	407         	1182206	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				FUSELAGE PANEL CRACKED IN SEVERAL PLACES. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400026	20020604	00026	SW  	2002	6	4	HEEA078977       	1	20020515	G	5320	407070620156	PANEL           			BELL  	407   	407         	1182206	SW  										HEADLINER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				HEADLINER CRACKED IN SEVERAL PLACES. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400027	20020604	00027	SW  	2002	6	4	HEEA078978       	1	20020515	G	2510	407070620152	PANEL           			BELL  	407   	407         	1182206	SW  										CREW SEAT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				SEAT PANEL CRACKED. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400028	20020604	00028	SW  	2002	6	4	HEEA078979       	1	20020515	G	5210	407070620151	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				CREW DOOR PANEL CRACKED. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400029	20020604	00029	SW  	2002	6	4	HEEA078980       	1	20020515	G	5320	407070620150	PANEL           			BELL  	407   	407         	1182206	SW  										INTERIOR TRIM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				INTERIOR TRIM PANEL CRACKED. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400030	20020604	00030	SW  	2002	6	4	HEEA078981       	1	20020515	G	2510	407070620149	PANEL           			BELL  	407   	407         	1182206	SW  										CREW SEAT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				CREW SEAT PANEL CRACKED. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400031	20020604	00031	SW  	2002	6	4	HEEA078982       	1	20020515	G	5320	407070620113	PANEL           			BELL  	407   	407         	1182206	SW  										INTERIOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				INTERIOR PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400032	20020604	00032	SW  	2002	6	4	HEEA078983       	1	20020515	G	5210	407070620137	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				CREW DOOR PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400033	20020604	00033	SW  	2002	6	4	HEEA078984       	1	20020515	G	5210	407070620205	COVER           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				STRIKER COVER CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400034	20020604	00034	SW  	2002	6	4	HEEA078985       	1	20020515	G	5320	407070620207	STRUCTURE       			BELL  	407   	407         	1182206	SW  										HAT BIN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				HAT BIN STRUCTURE CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400035	20020604	00035	SW  	2002	6	4	HEEA078986       	1	20020515	G	5210	407070620217	PANEL           			BELL  	407   	407         	1182206	SW  										PAX DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				PAX / CREW DOOR CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400036	20020604	00036	SW  	2002	6	4	HEEA078987       	1	20020515	G	2510	407070731103	BRACKET         			BELL  	407   	407         	1182206	SW  										SEAT HEADREST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				DETENT PINS FOR HEADREST BRACKET NOT WORKING AND STICKING.						1	G	7	1 	3U			O	H2SW    					 
2002060400040	20020604	00040	SW  	2002	6	4	HEEA078988       	1	20020515	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT BOTTLE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				EMERGENCY FLOAT BOTTLE GUAGE HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002060400050	20020604	00050	SW  	2002	6	4	HEEA078989       	1	20020515	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT BOTTLE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				EMERGENCY FLOAT BOTTLE GAUGE HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002060400059	20020604	00059	SW  	2002	6	4	HEEA078990       	1	20020515	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	1182206	SW  										FLOAT BOTTLE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				EMERGENCY FLOAT BOTTLE SOLENOID VALVE LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002060400060	20020604	00060	SW  	2002	6	4	HEEA078991       	1	20020515	G	2910	407073854101	TUBE            			BELL  	407   	407         	1182206	SW  										HYD SYSTEM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				MLG TUBE PITTING UNDER SLEEVES AND FLARE IS DAMAGED.						1	G	7	1 	3U			O	H2SW    					 
2002060400061	20020604	00061	SW  	2002	6	4	HEEA078994       	1	20020515	G	5260	407301108	STEP            			BELL  	407   	407         	1182206	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				HEAVY CORROSION AROUND MOUNT HOLES ON AIRSTAIR STEP.						1	G	7	1 	3U			O	H2SW    					 
2002060400063	20020604	00063	SW  	2002	6	4	HEEA078995       	1	20020515	G	5260	407301109	STEP            			BELL  	407   	407         	1182206	SW  										AIRSTAIR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				CORRODED BEYOND LIMITS ON AIRSTAIR STEP. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400064	20020604	00064	SW  	2002	6	4	HEEA078996       	1	20020515	G	5260	407301110	STEP            			BELL  	407   	407         	1182206	SW  										AIRSTAIR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				CORRODED BEYOND LIMITS ON AIRSTAIR STEP. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400065	20020604	00065	SW  	2002	6	4	HEEA078997       	1	20020515	G	5260	407301110	STEP            			BELL  	407   	407         	1182206	SW  										AIRSTAIR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				CORRODED BEYOND LIMITS AIRSTAIR STEP.  SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060400066	20020604	00066	SW  	2002	6	4	HEEA078998       	1	20020515	G	6420	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				ELASTOMERIC RUBBER DETERIORATED ON TAIL ROTOR MOUNT.						1	G	7	1 	3U			O	H2SW    					 
2002060400067	20020604	00067	SW  	2002	6	4	HEEA078999       	1	20020515	G	6420	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				ELASTOMERIC SEPARATION AROUND CIRCUMFERENCE ON TAIL ROTOR MOUNT.						1	G	7	1 	3U			O	H2SW    					 
2002060400068	20020604	00068	SW  	2002	6	4	HEEA079000       	1	20020515	G	6420	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				MOUNT COLLAPSED, DELAMINATED ON TAIL ROTOR.						1	G	7	1 	3U			O	H2SW    					 
2002060400070	20020604	00070	SW  	2002	6	4	HEEA079002       	1	20020515	G	6321	407340302101FM	CALIPER         			BELL  	407   	407         	1182206	SW  										ROTOR BRAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH	1956 				53400				REMOVED ROTOR BRAKE FOR OVERHAUL.  FOUND EXCESSIVE WEAR ON HOUSING AND PAD RETAINER BOLTS.						1	G	7	1 	3U			O	H2SW    					 
2002060400072	20020604	00072	SW  	2002	6	4	HEEA079003       	1	20020515	G	6510	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	741PH					53457				COOLER BLOWER BEARING COMING APART AND MAKING NOISE.						1	G	7	1 	3U			O	H2SW    					 
2002060400077	20020604	00077	SW  	2002	6	4	HEEA079004       	1	20020515	G	6510	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH					53378				COOLER BLOWER BEARING PRODUCING BLACK GREASE.						1	G	7	1 	3U			O	H2SW    					 
2002060400079	20020604	00079	SW  	2002	6	4	HEEA079005       	1	20020515	G	6510	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				COOLER BLOWER HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002060400081	20020604	00081	SW  	2002	6	4	HEEA079006       	1	20020515	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				TAIL ROTRO DISC PACK IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400083	20020604	00083	SW  	2002	6	4	HEEA079007       	1	20020515	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				TAIL ROTOR DISC PACK HAS FRETTING CORROSION BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002060400085	20020604	00085	SW  	2002	6	4	HEEA079008       	1	20020515	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				TAIL ROTOR DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400087	20020604	00087	SW  	2002	6	4	HEEA079009       	1	20020515	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				TAIL ROTOR DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400090	20020604	00090	SW  	2002	6	4	HEEA079010       	1	20020515	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				TAIL ROTOR DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400091	20020604	00091	SW  	2002	6	4	HEEA079011       	1	20020515	G	3212	407350301101	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	612PH					53199				EMERGENCY FLOAT FAILED 6 MONTH INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2002060400092	20020604	00092	SW  	2002	6	4	HEEA079012       	1	20020515	G	3212	407350302101	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				EMERGENCY FLOAT FAILED 6 MONTH INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2002060400097	20020604	00097	SW  	2002	6	4	HEEA079013       	1	20020515	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				LOW LEVEL SWITCH HAS CORROSION WHERE WIRING EXITS HOUSING.						1	G	7	1 	3U			O	H2SW    					 
2002060400100	20020604	00100	SW  	2002	6	4	HEEA079014       	1	20020515	G	2897	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										FUEL BOOST	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				FUEL BOOST PUMP PRESSURE SWITCH WIRES CORRODED AND BROKEN.						1	G	7	1 	3U			O	H2SW    					 
2002060400102	20020604	00102	SW  	2002	6	4	HEEA079015       	1	20020515	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										FUEL BOOST	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	490PH					53378				CAUTION WOULD NOT COME ON WHEN PUMPS WERE SWITCHED OFF.  REPLACE PRESSURE SWITCH.						1	G	7	1 	3U			O	H2SW    					 
2002060400103	20020604	00103	SW  	2002	6	4	HEEA079016       	1	20020515	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										FUEL BOOST	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				FUEL BOOST PRESSURE SWITCH INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2002060400104	20020604	00104	SW  	2002	6	4	HEEA079017       	1	20020515	G	2560	407370720101	RESTRAINT       			BELL  	407   	407         	1182206	SW  										COCKPIT SEATBELT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				RESTRAINT ASSY FRAYED AND CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002060400106	20020604	00106	SW  	2002	6	4	HEEA079018       	1	20020515	G	2560	407370721101	RESTRAINT       			BELL  	407   	407         	1182206	SW  										COCKPIT SEATBELT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				FRAYED AND CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002060400108	20020604	00108	SW  	2002	6	4	HEEA079019       	1	20020515	G	2560	407370721105	RESTRAINT       			BELL  	407   	407         	1182206	SW  										COCKPIT SEATBELT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				RESTRAINT ASSY FRAYED AND CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002060400109	20020604	00109	SW  	2002	6	4	HEEA079020       	1	20020515	G	6340	407375001105	INDICATOR       			BELL  	407   	407         	1182206	SW  										MGT	ILLUMINATED     	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	742PH					53461				MGT INDICATOR ILLUMINATED IN CRUISE FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2002060400111	20020604	00111	SW  	2002	6	4	HEEA079021       	1	20020515	G	7714	407375002103	INDICATOR       			BELL  	407   	407         	1182206	SW  										ENGINE NG	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	720PH					53277				NG INDICATOR WILL NOT DISPLAY RPM BUT WILL TEST.						1	G	7	1 	3U			O	H2SW    					 
2002060400112	20020604	00112	SW  	2002	6	4	HEEA079022       	1	20020515	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	407PH					53003				TORQUE INDICATOR HAS NO INDICATION ON LINEAR OR NUMERIC DISPLAYS.						1	G	7	1 	3U			O	H2SW    					 
2002060400114	20020604	00114	SW  	2002	6	4	HEEA079023       	1	20020515	G	7933	407375004101	INDICATOR       			BELL  	407   	407         	1182206	SW  										ENG OIL TEMP	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	457PH					53147				ENGINE OIL TEMP INDICAOTR RECEIVED FROM STOCK AND WOULD NOT INDICATE OIL PRESSURE.						1	G	7	1 	3U			O	H2SW    					 
2002060400115	20020604	00115	SW  	2002	6	4	HEEA079025       	1	20020515	G	7797	407375012101	WIRE HARNESS    			BELL  	407   	407         	1182206	SW  										FADEC	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				WIRE HARNESS OUTER INSULATION COVER OIL SOAKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400116	20020604	00116	SW  	2002	6	4	HEEA079026       	1	20020515	G	3340	4596	LIGHT           			BELL  	407   	407         	1182206	SW  										EXTERIOR	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	402PH					53159				EXTERIOR LIGHT INOPERATIVE. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2002060400117	20020604	00117	GL  	2002	6	4	HEEA079027       	2	20020515	G	7313	47101	NOZZLE          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE FUEL	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				INTERMITTENT STARTING PROBLEMS. REPLACED WITH SERVICEABLE FUEL NOZZLE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002060400119	20020604	00119		2002	6	4	HEEA079028       	4	20020515	G	3421	5040017901	INDICATOR       			BELL  	407   	407         	1182206	SW  										ATTITUDE	PRECESSES       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	407PH					53003				ATTITUDE INDICATOR PRECESSES. REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			O	H2SW    					 
2002060400120	20020604	00120		2002	6	4	HEEA079029       	4	20020515	G	3421	50400179015	INDICATOR       			BELL  	407   	407         	1182206	SW  										ATTITUDE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	407PH					53003				WILL NOT CAGE, SPINS CONTINUOUSLY. REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			O	H2SW    					 
2002060400121	20020604	00121	GL  	2002	6	4	HEEA079030       	2	20020515	G	7320	6839	BULB            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					FADEC	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	496PH					53398				FADEC MANUAL SWITCH BULB INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002060400122	20020604	00122	GL  	2002	6	4	HEEA079031       	2	20020515	G	7313	6899001	NOZZLE          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				N1, TOT, AND TORQUE OSCILLATION AFTER 20 MINUTES OF FLIGHT. REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002060400124	20020604	00124	SW  	2002	6	4	HEEA079033       	1	20020515	G	7920	70079H000D142	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	COLLAPSED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				FUEL DISTRIBUTION HOSE COLLAPSED.						1	G	7	1 	3U			O	H2SW    					 
2002060400125	20020604	00125	SW  	2002	6	4	HEEA079034       	1	20020515	G	3212	8226003	FUSIBLE PLUG    			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	LEAKING         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	492PH					53390				EMERGENCY FLOAT FUSIBLE PLUG LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002060400126	20020604	00126		2002	6	4	HEEA079035       	4	20020515	G	2350	AMS44	CONTROLLER      			BELL  	407   	407         	1182206	SW  										DUAL AUDIO SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	495PH					53397				INTERMITTENT FM HOT MIKE ON PASSENGER SIDE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002060400127	20020604	00127	SW  	2002	6	4	HEEA079036       	1	20020515	G	3411	AN58131	PITOT TUBE      			BELL  	407   	407         	1182206	SW  										STATIC/PITOT SYS	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				CORROSION ON INSIDE AND ON BACKSIDE OF PITOT TUBE.  CONNECTION TUBE IS TWISTED, PITOT TUBE HAS SMALL DENT ON EXTERIOR.						1	G	7	1 	3U			O	H2SW    					 
2002060400128	20020604	00128	SW  	2002	6	4	HEEA079037       	1	20020515	G	3340	DK202	LIGHT           			BELL  	407   	407         	1182206	SW  										EXTERIOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LIGHT PLASTIC RETAINER FOR LENS CRACKED AROUND SCREW HOLES.						1	G	7	1 	3U			O	H2SW    					 
2002060400130	20020604	00130	SW  	2002	6	4	HEEA079038       	1	20020515	G	6420	J123131	MOUNT           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				TAIL ROTOR RUBBER IS UNBONDING FROM MOUNT.						1	G	7	1 	3U			O	H2SW    					 
2002060400131	20020604	00131	SW  	2002	6	4	HEEA079042       	1	20020515	G	6510		BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				ROUGH BEARING ON COOLER BLOWER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2002060400132	20020604	00132	SW  	2002	6	4	HEEA079044       	1	20020515	G	6510		BEARING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				ROUGH BEARINGS ON COOLER BLOWER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2002060400134	20020604	00134	SW  	2002	6	4	HEEA079045       	1	20020515	G	3300	PM212302	SWITCH          			BELL  	407   	407         	1182206	SW  										LIGHT SYSTEM	BROKEN          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	490PH					53378				LIGHTING SYSTEM SWITCH BROKEN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002060400135	20020604	00135	SW  	2002	6	4	HEEA079047       	1	20020515	G	2110	S3008EC6	COMPRESSOR      			BELL  	407   	407         	1182206	SW  										AIR CONDITIONER	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	8595X	1161 				53267				AIR CONDITIONER COMPRESSOR WAS LEAKING OIL.						1	G	7	1 	3U			O	H2SW    					 
2002060400136	20020604	00136	SW  	2002	6	4	HEEA079048       	1	20020515	G	2432	SM20ACD300A21	RELAY           			BELL  	407   	407         	1182206	SW  										MAIN BATTERY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407XM					53464				BATTERY WON'T COME ON LINE.						1	G	7	1 	3U			O	H2SW    					 
2002060400138	20020604	00138		2002	6	4	HEEA079049       	4	20020515	G	3452	066106200	TRANSCEIVER     			BELL  	407   	407         	1182206	SW  										ATC	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	724PH					53327				ATC TRANSCEIVER MODE "C" INTERMITTENT AND TWO DIGITS OFF. IN SHOP FOR REPAIR.						1	G	7	1 	3U			O	H2SW    					 
2002060400140	20020604	00140	SW  	2002	6	4	HEEA079052       	1	20020515	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	494PH					53396				RECEIVED COVER WITH P/N 206-050-247-138 FOR RIGHT HAND AFT POSITION.  COVER FWD AND AFT FLAPS ARE SET UP FOR LEFT HAND.						1	G	7	1 	3U			O	H2SW    					 
2002060400141	20020604	00141	SW  	2002	6	4	HEEA079053       	1	20020515	G	3246	206053184121	SKID            			BELL  	407   	407         	1182206	SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				MLG SKID TUBE WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060400143	20020604	00143	SW  	2002	6	4	HEEA079054       	1	20020515	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				TAIL ROTOR COOLER BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400145	20020604	00145	SW  	2002	6	4	HEEA079055       	1	20020515	G	7810	206064203101	DUCT            			BELL  	407   	407         	1182206	SW  										EXHAUST SYS	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				EXHAUST DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060400149	20020604	00149	SW  	2002	6	4	HEEA079059       	1	20020515	G	6720	209001053001	BEARING         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				TAIL ROTOR BEARING HAS RADIAL PLAY OF .007 INCH AND LIMIT IS .005 INCH.						1	G	7	1 	3U			O	H2SW    					 
2002060400151	20020604	00151	GL  	2002	6	4	HEEA079060       	2	20020515	G	7250	23001832	NOZZLE          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	BENT            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				ENGINE NOZZEL TUBE BENT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002060400154	20020604	00154	GL  	2002	6	4	HEEA079061       	2	20020515	G	7261	23063144	FILTER ELEMENT  			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE OIL	CLOGGED         	E			HEEA	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	742PH					53461				ENGINE OIL FILTER CLOGGED, OIL BYPASS INDICATOR POPPING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002060400157	20020604	00157	GL  	2002	6	4	HEEA079062       	2	20020515	G	7261	23066697	FILTER          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE OIL	CLOGGED         	E			HEEA	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	4999					53323				BYPASS BUTTON EXTENDED ON DAILY.  ENGINE OIL FILTER CLOGGED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002060400161	20020604	00161	SW  	2002	6	4	HEEA079064       	1	20020515	G	3211	400052015103	SUPPORT         			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				MLG SUPPORT HAS CORROSION AROUND BOLT HOLES.						1	G	7	1 	3U			O	H2SW    					 
2002060400162	20020604	00162	SW  	2002	6	4	HEEA079065       	1	20020515	G	6230	206010421011	BUSHING         		406010401117	BELL  	407   	407         	1182206	SW  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH				A685	53228				BUFFER ON BUSHING IS WORN ON SWASHPLATE.						1	G	7	1 	3U			O	H2SW    					 
2002060400163	20020604	00163	SW  	2002	6	4	HEEA079070       	1	20020515	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										PITCH CONTROL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				MAIN ROTOR UPPER PC LINK BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060400165	20020604	00165	SW  	2002	6	4	HEEA079071       	1	20020515	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										PITCH CONTROL	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				MAIN ROTOR PITCH CONTROL LINK BEARING ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002060400168	20020604	00168	SW  	2002	6	4	HEEA079072       	1	20020515	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										PITCH LINK	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				CORROSION BLEEDING FROM BEARING RACE AND AROUND EXTERIOR OF PITCH LINK.						1	G	7	1 	3U			O	H2SW    					 
2002060400179	20020604	00179	SW  	2002	6	4	HEEA079073       	1	20020516	G	3340	01077005813	LIGHT           			BELL  	214   	214ST       	1182106	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806					28140				EXTERIOR STROBE LIGHT INOPERATIVE.						2	G	7	2 	4U			 	H10SW   					 
2002060400180	20020604	00180		2002	6	4	HEEA079074       	4	20020516	G	2312	064102300	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										VHF SYSTEM	DAMAGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3897N					28106				INTERMITTENTLY BREAKS SQUELCH AND WEAK. PERFORMED PRELIMINARY INSPECTION.  REMOVED CORROSION FROM CHASSIS.  REPLACED COR	RODED Q109 AND Q110 TRANSISTORS AND INSULATORS, BAD Q102, Q104 AND Q106 TRANSISTOR INSULATORS, BAD Q110 SOCKET AND BROKE	N NAMEPLATE.  REPLACED BURNED F101 FUSE.  FOUND RECEIVER WEAK AND NO TRANSMIT.  RESOLDERED RF CONNECTOR.  REPAIRED.  ALI	GNED TRANSMITTER.  BENCH CHECK GOOD.			2	G	7	2 	4U			 	H10SW   					 
2002060400181	20020604	00181	SW  	2002	6	4	HEEA079075       	1	20020516	G	6710	209001051001	BEARING         			BELL  	214   	214ST       	1182106	SW  										COLLECTIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				COLLECTIVE CONTROL ASSY HAS WORN BEARINGS.						2	G	7	2 	4U			 	H10SW   					 
2002060400182	20020604	00182		2002	6	4	HEEA079076       	4	20020516	G	2300	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										RADIO SYSTEM	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5748M					28102				LIGHTS WOULD NOT COME ON DURING MONITOR TEST.						2	G	7	2 	4U			 	H10SW   					 
2002060400185	20020604	00185	SW  	2002	6	4	HEEA079077       	1	20020516	G	7720	3036T52G01	WIRE HARNESS    			BELL  	214   	214ST       	1182106	SW  										ENG TEMP IND	DAMAGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T					28101				NR 2 ENGINE TEMPERATURE CONNECTOR ON GREEN HARNESS IS CAUSING THE ENGINE TEMPERATURE INDICATOR TO PEG OUT AT VARIOUS TIM	ES.					2	G	7	2 	4U			 	H10SW   					 
2002060400186	20020604	00186		2002	6	4	HEEA079078       	4	20020516	G	3442	40016702513	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										WX RADAR SYS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	822H					28139				DOES NOT TURN ON. SCRAPPED.						2	G	7	2 	4U			 	H10SW   					 
2002060400188	20020604	00188		2002	6	4	HEEA079079       	4	20020516	G	3442	7021450601	COMPUTER        			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806					28140				WEATHER RADAR CENTRAL COMPUTER GOES TO FAIL MODE WHEN TURNED ON.						2	G	7	2 	4U			 	H10SW   					 
2002060400192	20020604	00192	SW  	2002	6	4	HEEA079080       	1	20020516	G	6310	214040849105	SEAL            		214040014105	BELL  	214   	214ST       	1182106	SW  										M/R DRIVESHAFT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T				A00000003	28101				FOUND BOOTS CRACKED, CORRODED AND DAMAGED ON 250 HOUR COUPLING LUBE INSPECTION. REPLACED WITH SERVICEABLE PARTS.						2	G	7	2 	4U			 	H10SW   					 
2002060400196	20020604	00196	SW  	2002	6	4	HEEA079081       	1	20020516	G	6420		HUB             			BELL  	214   	214ST       	1182106	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				FOUND 4 PITCH HORN BOLTS CORRODED, ONE GRIP BOLT CORRODED AND DAMAGED, 2 BLADE BOLTS CORRODED AND 2 FEATHERING BEARINGS 	WORN. (ADP)					2	G	7	2 	4U			 	H10SW   					 
2002060400199	20020604	00199	SW  	2002	6	4	HEEA079082       	1	20020516	G	2840	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL INDICATOR	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										INDICATOR READS ZERO. REPLACE FAILED SIGNAL CONDITIONING UNIT.						1	G	7	2 	4U			 	H4SW    					 
2002060400200	20020604	00200		2002	6	4	HEEA079084       	4	20020516	G	3417	214175421101	ADC             			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										ADC SHOWS BOTH ENGINES ZERO POWER AT 40 PERCENT.						2	G	7	2 	4U			 	H10SW   					 
2002060400211	20020604	00211		2002	6	4	HEEA079085       	4	20020516	G	2200	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										ELEVATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ELEVATOR AMPLIFIER DRIVES ACTUATOR WITH NO A/S SIGNAL.						2	G	7	2 	4U			 	H10SW   					 
2002060400212	20020604	00212		2002	6	4	HEEA079086       	4	20020516	G	2200	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										ELEVATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ELEVATOR AMPLIFIER COULD NOT ALIGN AMP TO STAY ENGAGED WITH OTHER SYSTEM.						2	G	7	2 	4U			 	H10SW   					 
2002060400213	20020604	00213	SW  	2002	6	4	HEEA079087       	1	20020516	G	6700	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										FLY BY WIRE SYS	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ELEVATOR FLY BY WIRE ACTUATOR MOVEMENT IS ROUGH AND RATCHETY.						2	G	7	2 	4U			 	H10SW   					 
2002060400214	20020604	00214		2002	6	4	HEEA079089       	4	20020516	G	3451	064100900	TRANSCEIVER     			BELL  	212   	212         	1181420	SW  										DME/TACAN SYS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5736J					31140				DME/TACAN TRANSCEIVER WILL NOT TRANSMIT OR RECEIVE. REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	4U			 	H4SW    					 
2002060400215	20020604	00215	SW  	2002	6	4	HEEA079090       	1	20020516	G	6320	212040233001	LINE            			BELL  	212   	212         	1181420	SW  										TRANSMISSION	CRACKED         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5736D					31135				CRACKED LINE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	4U			 	H4SW    					 
2002060400216	20020604	00216	SW  	2002	6	4	HEEA079091       	1	20020516	G	7714	222375022111	INDICATOR       			BELL  	230   	230         	1182149	SW  										ENGINE NG	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RC					23037				ENGINE NG INDICATOR HAS A FLUCTUATING NEEDLE.						1	G	7	2 	3U			NC	H9SW    					 
2002060400220	20020604	00220		2002	6	4	HEEA079096       	4	20020520	G	2200	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										ELEVATOR	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										ELEVATOR AMPLIFIER WILL NOT MONITOR TEST.						2	G	7	2 	4U			 	H10SW   					 
2002060400222	20020604	00222	SW  	2002	6	4	HEEA079097       	1	20020520	G	7720	212075067119	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE ITT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ITT INDICATOR WOULD NOT INDICATE.						1	G	7	2 	4U			 	H4SW    					 
2002060400226	20020604	00226	GL  	2002	6	4	HEEA079098       	2	20020520	G	7261	174000101	FILTER          			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	30KH					51527				ENGINE OIL FILTER LEAKING FROM HOSE.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002060400227	20020604	00227	SW  	2002	6	4	HEEA079099       	1	20020520	G	5310	205030280141	STRUCTURE       			BELL  	412   	412         	1182202	SW  										WORK DECK	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	800Y					33134				NEWLY INSTALLED WORK DECK FOUND TO BE SEPARATED ON BOTTOM.  THE SEPARATED AREA WAS 5 INCHES IN DIAMETER NEAR FWD CENTER 	OF DECK ASSY.					1	G	7	2 	4U			 	H4SW    					 
2002060400229	20020604	00229	SW  	2002	6	4	HEEA079100       	1	20020520	G	2822	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										FUEL BOOST	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				FUEL BOOST PUMP INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2002060400230	20020604	00230	SW  	2002	6	4	HEEA079101       	1	20020520	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3905B	2968 				45598				BLADE HAS A BULGE OVER THE SPAR AT STA. 96.25 INCHES ON THE UPPER SURFACE WHICH APPEARS TO BE EXFOLIATION.  BLADE HAS EX	CESSIVE CORROSION AND SEPARATION ON THE LOWER SURFACE NEAR THE TIP.					1	G	7	1 	3U			 	H2SW    					 
2002060400233	20020604	00233	SW  	2002	6	4	HEEA079102       	1	20020521	G	6220		BEARING         			BELL  	206   	206L3       	1182108	SW  										PITCH LINK	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				RUBBER IS POOCHING OUT OF THE UPPER ELASTOMERIC BEARING.						1	G	7	1 	3U			 	H2SW    					 
2002060400234	20020604	00234	SW  	2002	6	4	HEEA079103       	1	20020521	G	6220		BEARING         			BELL  	206   	206L3       	1182108	SW  										PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				PITCH LINK ASSY HAS A WORN BEARING.						1	G	7	1 	3U			 	H2SW    					 
2002060400235	20020604	00235	SW  	2002	6	4	HEEA079104       	1	20020521	G	6220		BEARING         			BELL  	206   	206L3       	1182108	SW  										PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116P					51530				PITCH LINK ASSY HAS A WORN BEARING.						1	G	7	1 	3U			 	H2SW    					 
2002060400237	20020604	00237	SW  	2002	6	4	HEEA079105       	1	20020521	G	6220		BEARING         			BELL  	206   	206L3       	1182108	SW  										PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				PITCH LINK ASSY HAS A WORN BEARING.						1	G	7	1 	3U			 	H2SW    					 
2002060400238	20020604	00238	SW  	2002	6	4	HEEA079106       	1	20020521	G	6220		BEARING         			BELL  	206   	206L3       	1182108	SW  										PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				PITCH LINK ASSY HAS A WORN BEARING.						1	G	7	1 	3U			 	H2SW    					 
2002060400239	20020604	00239	SW  	2002	6	4	HEEA079107       	1	20020521	G	3246	206324007	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8594X					51531				SKID TUBE HAS SEVER CORROSION IN SEVERAL AREAS.						1	G	7	1 	3U			 	H2SW    					 
2002060400241	20020604	00241	SW  	2002	6	4	HEEA079108       	1	20020521	G	7720	206375007101	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE TOT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	363BH					51345				ENGINE TOT READS TEMP HIGH.						1	G	7	1 	3U			 	H2SW    					 
2002060400242	20020604	00242	SW  	2002	6	4	HEEA079110       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	800Y					33134				CROSSTUBE HAS SEVERAL AREAS OF PITTED CORROSION BETWEEN SADDLES.						1	G	7	2 	4U			 	H4SW    					 
2002060400244	20020604	00244	SW  	2002	6	4	HEEA079111       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				CROSSTUBE HAS SEVERAL AREAS OF PITTED CORROSION BETWEEN SADDLES.						1	G	7	2 	4U			 	H4SW    					 
2002060400245	20020604	00245	SW  	2002	6	4	HEEA079112       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				CROSSTUBE HAS SEVERAL AREAS OF PITTED CORROSION BETWEEN SADDLES.						1	G	7	2 	4U			 	H4SW    					 
2002060400246	20020604	00246	SW  	2002	6	4	HEEA079113       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				CROSSTUBE IS CORRODED BEYOND LIMITS ON TOP SIDE BETWEEN SADDLES.						1	G	7	2 	4U			 	H4SW    					 
2002060400248	20020604	00248	SW  	2002	6	4	HEEA079114       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				CROSSTUBE CORRODED BEYOND LIMITS IN SEVERAL AREAS.						1	G	7	2 	4U			 	H4SW    					 
2002060400249	20020604	00249	SW  	2002	6	4	HEEA079115       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				CROSSTUBE CORRODED BEYOND LIMITS IN SEVERAL AREAS.						1	G	7	2 	4U			 	H4SW    					 
2002060400250	20020604	00250	SW  	2002	6	4	HEEA079116       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P	7741 				33012				CROSSTUBE CORRODED BEYOND LIMITS IN SEVERAL AREAS.						1	G	7	2 	4U			 	H4SW    					 
2002060400252	20020604	00252	SW  	2002	6	4	HEEA079117       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F					33073				CROSSTUBE CORRODED BEYOND LIMITS.						1	G	7	2 	4U			 	H4SW    					 
2002060400254	20020604	00254	SW  	2002	6	4	HEEA079118       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N	1025 				33010				CORROSION PITS IN ZONE 1 ON TOP SIDE OF TUBE AT A DEPTH OF .010 OF AN INCH DEEP NEAR SADDLE MOUNT.						1	G	7	2 	4U			 	H4SW    					 
2002060400256	20020604	00256	SW  	2002	6	4	HEEA079119       	1	20020521	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				MLG CROSSTUBE HAS CORROSION IN ZONE 1 & 2 RADIAL DAMAGED AREAS TO BE BEYOND LIMITS.						1	G	7	2 	4U			 	H4SW    					 
2002060400263	20020604	00263	SW  	2002	6	4	HEEA079120       	1	20020521	G	6340	212040805001	SENSOR          			BELL  	206   	206B3       	1181506	SW  										XMSN TEMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2275Y					3626				SENSOR CAUSING TRANSMISSION TEMP LIGHTS EVEN WITH THE TEMPS IN THE GREEN.						1	G	7	1 	3U			 	H2SW    					 
2002060400265	20020604	00265	SW  	2002	6	4	HEEA079123       	1	20020521	G	2510	222320823119	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				SEAT BELT WORN.						1	G	7	1 	3U			 	H2SW    					 
2002060400272	20020604	00272	SW  	2002	6	4	HEEA079124       	1	20020521	G	2510	222320823119	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				SEAT BELT WORN AND FRAYED.						1	G	7	1 	3U			 	H2SW    					 
2002060400278	20020604	00278	SW  	2002	6	4	HEEA079125       	1	20020521	G	2510	222320823119	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				SEAT BELT FRAYED.						1	G	7	1 	3U			 	H2SW    					 
2002060400283	20020604	00283	SW  	2002	6	4	HEEA079127       	1	20020521	G	5320		BRACKET         			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8594X					51531				MOUNT BRACKET FOR THE SHOULER HARNESS TO AIRFRAME WERE ELONGATED.						1	G	7	1 	3U			 	H2SW    					 
2002060400288	20020604	00288	SW  	2002	6	4	HEEA079128       	1	20020522	G	5310	412030009107	STRUCTURE       			BELL  	412   	412         	1182202	SW  										SERVICE DECK	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				ENGINE DECK SEPARATION.						1	G	7	2 	4U			 	H4SW    					 
2002060400292	20020604	00292	SW  	2002	6	4	HEEA079129       	1	20020522	G	3212	412050017135	COVER           			BELL  	412   	412         	1182202	SW  										EMERGENCY FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				EMERGENCY FLOAT COVER WORN.						1	G	7	2 	4U			 	H4SW    					 
2002060400308	20020604	00308		2002	6	4	HEEA079130       	4	20020522	G	3442	7007700705	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	WORN            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				RADAR SYS WON'T PAINT TARGETS.						1	G	7	2 	4U			 	H4SW    					 
2002060400309	20020604	00309		2002	6	4	HEEA079131       	4	20020522	G	2350	A3016W	INTERPHONE      			BELL  	412   	412         	1182202	SW  										CABIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				INTERPHONE BOX HAS ERRATIC VOLUME CONTROL ON ALL RADIOS.						1	G	7	2 	4U			 	H4SW    					 
2002060400310	20020604	00310		2002	6	4	HEEA079132       	4	20020522	G	2350	A3016W	INTERPHONE      			BELL  	412   	412         	1182202	SW  										CABIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	22608					33075				ADF SELECTOR SWITCH WILL NOT TURN IT'S AUDIO OFF (INTERMITTENTLY).  FACEPLATE NEEDS REFURBISH.						1	G	7	2 	4U			 	H4SW    					 
2002060500001	20020605	00001		2002	6	5	HEEA079133       	4	20020522	G	2350	A3016W	INTERPHONE      			BELL  	412   	412         	1182202	SW  										CABIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5759N					33002				INTERPHONE BOX HAS STATIC ON ALL CHANNELS.						1	G	7	2 	4U			 	H4SW    					 
2002060500002	20020605	00002		2002	6	5	HEEA079134       	4	20020522	G	3442	MI5851345V	INDICATOR       			BELL  	412   	412         	1182202	SW  										WX RADAR SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				RADAR CAUSES STREAKS AND FALSE TARGETS IN MAP AND WEATHER MODE.						1	G	7	2 	4U			 	H4SW    					 
2002060500003	20020605	00003		2002	6	5	HEEA079135       	4	20020522	G	3442	MI5851352	INDICATOR       			BELL  	412   	412         	1182202	SW  										WX RADAR SYS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WEATHER RADAR SYSTEM IS INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2002060500004	20020605	00004		2002	6	5	HEEA079136       	4	20020522	G	3442	MI585136	INDICATOR       			BELL  	412   	412         	1182202	SW  										WX RADAR SYS	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WEATHER RADAR SYSTEM INTERMITTENTLY GOES OFF AND ON.						1	G	7	2 	4U			 	H4SW    					 
2002060500005	20020605	00005		2002	6	5	HEEA079137       	4	20020522	G	3442	MI5852013	INDICATOR       			BELL  	412   	412         	1182202	SW  										WX RADAR SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				WEATHER RADAR SYSTEM SHOWS NOISE BAND TEST PATTERN ONLY.						1	G	7	2 	4U			 	H4SW    					 
2002060500006	20020605	00006		2002	6	5	HEEA079141       	4	20020523	G	2300	407530014101	MOUNT           			BELL  	407   	407         	1182206	SW  										ANTENNA	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH	3680 				53327				CORROSION AT RADIO ANTENNA MOUNT.						1	G	7	1 	3U			O	H2SW    					 
2002060500007	20020605	00007	SW  	2002	6	5	HEEA079143       	1	20020523	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				EMERGENCY FLOAT COVER IS TORN.						1	G	7	1 	3U			O	H2SW    					 
2002060500008	20020605	00008	SW  	2002	6	5	HEEA079146       	1	20020523	G	5240	206064819006S	ACCESS DOOR     			BELL  	407   	407         	1182206	SW  										XMSN COWLING	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				RT TRANSMISSION COWL ACCESS DOOR CORRODED. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060500009	20020605	00009	SW  	2002	6	5	HEEA079147       	1	20020523	G	5320	206072215101	SUPPORT         			BELL  	407   	407         	1182206	SW  										FUSELAGE	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				FUSELAGE SUPPORT STRUCTURE BROKEN - HAS EXCESSIVE WEAR.						1	G	7	1 	3U			O	H2SW    					 
2002060500010	20020605	00010	SW  	2002	6	5	HEEA079150       	1	20020523	G	2821	23066697	FILTER          			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				FUEL FILTER BYPASSING BUTTON POPPED.						1	G	7	1 	3U			O	H2SW    					 
2002060500011	20020605	00011	SW  	2002	6	5	HEEA079151       	1	20020523	G	5310	400052007115	BEAM            			BELL  	407   	407         	1182206	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				FUSELAGE BEAM HAS CORROSION UNDER BUSHING AND BEARING CAP.						1	G	7	1 	3U			O	H2SW    					 
2002060500012	20020605	00012	SW  	2002	6	5	HEEA079152       	1	20020523	G	6720	406001704101	BELLCRANK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				TAIL ROTOR BELLCRANK LUG IS CHAFED BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2002060500013	20020605	00013	SW  	2002	6	5	HEEA079153       	1	20020523	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH	636  				53396				MAIN ROTOR SWASHPLATE PUSHING UP GREASE THROUGH UPPER SEAL.						1	G	7	1 	3U			O	H2SW    					 
2002060500014	20020605	00014	SW  	2002	6	5	HEEA079154       	1	20020523	G	6230		PITCH LINK      			BELL  	407   	407         	1182206	SW  										SWASHPLATE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH				A6565	53159				MAIN ROTOR SWASHPLATE PITCH CONTROL LINK CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2002060500015	20020605	00015	SW  	2002	6	5	HEEA079155       	1	20020523	G	6230	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										SWASHPLATE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				SWASHPLATE PITCH CONTROL LINK HAS SURFACE CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002060500016	20020605	00016	SW  	2002	6	5	HEEA079161       	1	20020523	G	6520		SEAL            			BELL  	407   	407         	1182206	SW  										GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	447PH				A682	53114				TAIL ROTOR GEARBOX INPUT SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002060500017	20020605	00017	SW  	2002	6	5	HEEA079163       	1	20020523	G	6520	406040453101	SEAL            			BELL  	407   	407         	1182206	SW  										GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	612PH					53199				TAIL ROTOR GEARBOX INPUT SEAL HAS AN OIL LEAK.						1	G	7	1 	3U			O	H2SW    					 
2002060500018	20020605	00018	SW  	2002	6	5	HEEA079164       	1	20020523	G	6220	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				MAIN ROTOR HEAD UNIVERSAL BUSHING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060500022	20020605	00022	SW  	2002	6	5	HEEA079165       	1	20020523	G	6420	406310411101	BOOT            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR HEAD	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				TAIL ROTOR HEAD BOOT IS TORN.						1	G	7	1 	3U			O	H2SW    					 
2002060500024	20020605	00024	SW  	2002	6	5	HEEA079166       	1	20020523	G	6220		BEARING         			BELL  	407   	407         	1182206	SW  										IDLER ASSY	UNSTAKED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				MAIN ROTOR HEAD BEARING UNSTAKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500025	20020605	00025	SW  	2002	6	5	HEEA079167       	1	20020523	G	6220	407001524105	BELLCRANK       			BELL  	407   	407         	1182206	SW  										M/R HEAD	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				MAIN ROTOR HEAD BELLCRANK WEAR PAD UNBONDED.						1	G	7	1 	3U			O	H2SW    					 
2002060500029	20020605	00029	SW  	2002	6	5	HEEA079174       	1	20020523	G	5320	407023800118S	SUPPORT         			BELL  	407   	407         	1182206	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				FUSELAGE SUPPORT STRUCTURE CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500030	20020605	00030	SW  	2002	6	5	HEEA079175       	1	20020523	G	3210	407030112103	STRAP           			BELL  	407   	407         	1182206	SW  										MLG	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				STRAP ON MLG CHAFED.						1	G	7	1 	3U			O	H2SW    					 
2002060500031	20020605	00031	SW  	2002	6	5	HEEA079181       	1	20020523	G	3213	407050202101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				CORROSION ON AFT CROSSTUBE.						1	G	7	1 	3U			O	H2SW    					 
2002060500032	20020605	00032	SW  	2002	6	5	HEEA079182       	1	20020523	G	2510	407070620125	PANEL           			BELL  	407   	407         	1182206	SW  										SEAT TRIM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				RT CREW SEAT TRIM PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500033	20020605	00033	SW  	2002	6	5	HEEA079183       	1	20020523	G	5230	407070620143	PANEL           			BELL  	407   	407         	1182206	SW  										LITTER DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				LITTER DOOR TRIM PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500034	20020605	00034	SW  	2002	6	5	HEEA079184       	1	20020523	G	5230	407070620157	PANEL           			BELL  	407   	407         	1182206	SW  										LITTER DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				LT AFT DOOR UPPER TRIM PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500035	20020605	00035	SW  	2002	6	5	HEEA079185       	1	20020523	G	5230	407070620158	PANEL           			BELL  	407   	407         	1182206	SW  										LITTER DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				UPPER TRIM PANEL ON RT AFT DOOR CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500036	20020605	00036	SW  	2002	6	5	HEEA079186       	1	20020523	G	5210	407070620205	COVER           			BELL  	407   	407         	1182206	SW  										DOOR STRIKER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				CREW DOOR STRIKER COVER CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500037	20020605	00037	SW  	2002	6	5	HEEA079187       	1	20020523	G	5230	407070620218	PANEL           			BELL  	407   	407         	1182206	SW  										LITTER DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				LOWER TRIM PANEL ON RT AFT DOOR CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500038	20020605	00038	SW  	2002	6	5	HEEA079188       	1	20020523	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	1182206	SW  										FLOAT BOTTLE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416				207	53070				EMERGENCY FLOAT BOTTLE SOLENOID VALVE LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002060500039	20020605	00039	SW  	2002	6	5	HEEA079189       	1	20020523	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	1182206	SW  										FLOAT BOTTLE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH				248	53147				EMERGENCY FLOAT BOTTLE SOLENOID VALVE LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002060500043	20020605	00043	SW  	2002	6	5	HEEA079190       	1	20020523	G	6310	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE/XMSN	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				ENGINE/TRANSMISSION COUPLING MOUNT WEAK AND SEPARATED.						1	G	7	1 	3U			O	H2SW    					 
2002060500045	20020605	00045	SW  	2002	6	5	HEEA079191       	1	20020523	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				TAIL ROTOR DISC PACK HAS CORROSION.						1	G	7	1 	3U			O	H2SW    					 
2002060500046	20020605	00046	SW  	2002	6	5	HEEA079192       	1	20020523	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				TAIL ROTOR DISC PACK IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500049	20020605	00049	SW  	2002	6	5	HEEA079193       	1	20020523	G	2841		WIRE            			BELL  	407   	407         	1182206	SW  										SWITCH	BROKEN          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	402PH				286	53159				FUEL INDICATOR SWITCH HAS A BROKEN WIRE AT DETECTOR OUTPUT.						1	G	7	1 	3U			O	H2SW    					 
2002060500052	20020605	00052		2002	6	5	HEEA079194       	4	20020524	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										AUTOFLIGHT AMPLIFIER MALFUNCTIONED, ELEVATOR WOULD NOT STAY ON LINE.						2	G	7	2 	4U			 	H10SW   					 
2002060500054	20020605	00054	SW  	2002	6	5	HEEA079195       	1	20020524	G	2841	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										FUEL INDICATOR	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	404PH					53188				FUEL INDICTOR PRESSURE SWITCH WORKS INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW    					 
2002060500055	20020605	00055	SW  	2002	6	5	HEEA079196       	1	20020524	G	5320	407412101	PANEL           			BELL  	407   	407         	1182206	SW  										FUSELAGE TRIM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				FUSELAGE TRIM PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002060500056	20020605	00056	SW  	2002	6	5	HEEA079197       	1	20020524	G	5260	407535101	STEP            			BELL  	407   	407         	1182206	SW  										AIRSTAIRS	DEFORMED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										AIRSTAIR FOLDING STEP DOES NOT FIT COUNTOUR OF AIRCRAFT.						1	G	7	1 	3U			O	H2SW    					 
2002060500059	20020605	00059	SW  	2002	6	5	HEEA079198       	1	20020524	G	5340	500913	BRACKET         			BELL  	407   	407         	1182206	SW  										FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				FUSELAGE BRACKET CLIP FOR RETAINER STAP MISSING.						1	G	7	1 	3U			O	H2SW    					 
2002060500060	20020605	00060		2002	6	5	HEEA079199       	4	20020524	G	3457	8143802240D	GPS             			BELL  	407   	407         	1182206	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				DISPLAY COVER MISSING. PERFORMED PRELIMINARY INSPECTION AND REPLACED BAD DISPLAY LENS.  REPAIRED.  REALIGNED BUTTONS AND	 FACEPLATE.  BENCH CHECK GOOD.					1	G	7	1 	3U			O	H2SW    					 
2002060500061	20020605	00061	SW  	2002	6	5	HEEA079200       	1	20020524	G	5240	90015102156	LATCH           			BELL  	407   	407         	1182206	SW  										ACCESS DOOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH					53399				LEFT ENGINE COWL ACCESS DOOR LATCHES WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060500062	20020605	00062	SW  	2002	6	5	HEEA079201       	1	20020524	G	5240	90015032125	LATCH           			BELL  	407   	407         	1182206	SW  										ACCESS DOOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH					53399				LEFT TRANSMISSION DECK ACCESS DOOR UPPER LATCH WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060500064	20020605	00064	SW  	2002	6	5	HEEA079203       	1	20020524	G	6220	MS211536	BEARING         		406012129101	BELL  	407   	407         	1182206	SW  										PITCH LINK ASSY	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				MAIN ROTOR PITCH LINK ASSY ROD END BEARINGS ARE ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002060500067	20020605	00067	SW  	2002	6	5	HEEA079206       	1	20020524	G	6420		SEAL            			BELL  	407   	407         	1182206	SW  										PITCH LINK ASSY	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	404PH					53188				TAIL ROTOR PITCH LINK ASSY SEALS ARE LEAKING, BOOT IS DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2002060500069	20020605	00069	SW  	2002	6	5	HEEA079207       	1	20020524	G	6420	206011728003	TRUNNION        			BELL  	407   	407         	1182206	SW  										PITCH LINK ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				TAIL ROTOR PITCH LINK ASSY TRUNNION WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060500070	20020605	00070	SW  	2002	6	5	HEEA079208       	1	20020524	G	5210		STRUCTURE       			BELL  	407   	407         	1182206	SW  										CREW DOOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	5631 				53159				CORROSION ON INSIDE OF CREW DOOR.						1	G	7	1 	3U			O	H2SW    					 
2002060500087	20020605	00087	SW  	2002	6	5	HEEA079211       	1	20020524	G	6220	206011117003	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR HEAD	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	92MT					51175				FLAP RESTRAINT EAR STICKS IN STOWED POSITION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2002060500092	20020605	00092	SW  	2002	6	5	HEEA079212       	1	20020524	G	6310	206040270123	FREEWHEEL UNIT  			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				FREEWHEEL UNIT MAKING METAL.						1	G	7	1 	3U			 	H2SW    					 
2002060500093	20020605	00093	SW  	2002	6	5	HEEA079213       	1	20020524	G	3246	206324007	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206FS					51506				SKID TUBE CRACKED DUE TO CORROSION EXFOLIATING FROM TUBE AT FORWARD END NEAR HOLD DOWN RING.						1	G	7	1 	3U			 	H2SW    					 
2002060500098	20020605	00098	SW  	2002	6	5	HEEA079214       	1	20020524	G	2822		PLATE           			BELL  	412   	412         	1182202	SW  										VALVE	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				PLATE LOOSE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2002060500101	20020605	00101	SW  	2002	6	5	HEEA079215       	1	20020524	G	7810		BRACKET         			BELL  	412   	412         	1182202	SW  										EJECTOR ASSY	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z				A368	36019				EXHAUST EJECTOR AFT BRACKETS CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2002060500103	20020605	00103	SW  	2002	6	5	HEEA079216       	1	20020524	G	7810		BRACKET         			BELL  	412   	412         	1182202	SW  										EJECTOR ASSY	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z				I3000612	36019				EXHAUST EJECTOR AFT BRACKETS CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2002060500109	20020605	00109	SW  	2002	6	5	HEEA079219       	1	20020524	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	ERODED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				MAIN ROTOR BLADE LEADING EDGE ERODED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2002060500111	20020605	00111	SW  	2002	6	5	HEEA079220       	1	20020524	G	3340	A490A	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										EXTERIOR LIGHTS	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	81671					51301				EXTERIOR LIGHTING POWER SUPPLY FAILED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2002060500113	20020605	00113		2002	6	5	HEEA079221       	4	20020524	G	3442	MI5851352	INDICATOR       			BELL  	412   	412         	1182202	SW  										WX RADAR SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				STREAKS AND FALSE TARGETS IN WEATHER MODE AND MAP MODE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2002060500116	20020605	00116		2002	6	5	HEEA079222       	4	20020524	G	2300	PHI001L0001201	RADIO           			BELL  	206   	206L1       	1182107	SW  										FM SYSTEM	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27766					45312				FM RADIO RECEIVE WEAK ON PILOT SIDE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2002060500122	20020605	00122	SW  	2002	6	5	HEEA079223       	1	20020524	G	6300	PHI212412830	MAGNETIC SEAL   			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2148K					36001				MAIN ROTOR DRIVE MAGNETIC SEAL LEAKS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2002060500123	20020605	00123	SW  	2002	6	5	HEEA079224       	1	20020524	G	2822	1C2710	CARTRIDGE       			BELL  	407   	407         	1182206	SW  										FUEL BOOST	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				BOOST PUMP CARTRIDGE IS INTERMITTENT WITH LOW PRESSURE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2002060500124	20020605	00124	SW  	2002	6	5	HEEA079225       	1	20020524	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										EMERGENCY FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				EMERGENCY FLOAT COVER IS TORN.						1	G	7	1 	3U			O	H2SW    					 
2002060500128	20020605	00128	SW  	2002	6	5	HEEA079227       	1	20020524	G	6710	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				CORROSION ON MAIN ROTOR DRIVE LINK.						1	G	7	1 	3U			O	H2SW    					 
2002060500138	20020605	00138		2002	6	5	HEEA079235       	4	20020524	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				COPILOT OFF FLAG DOES NOT DISPLAY WHEN SLAVING.						1	G	7	2 	4U			 	H4SW    					 
2002060500146	20020605	00146		2002	6	5	HEEA079239       	4	20020524	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				ATTITUDE INDICATOR RT FLAG WON'T PULL FROM VIEW.						1	G	7	2 	4U			 	H4SW    					 
2002060500151	20020605	00151		2002	6	5	HEEA079242       	4	20020524	G	3421	1113035	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				ATTITUDE INDICATOR COMPASS CARD FLUCTUATES 10 TO 14 DEGREES OFF COURSE.						1	G	7	2 	4U			 	H4SW    					 
2002060500167	20020605	00167	EU  	2002	6	5	HEEA079252       	1	20020506	G	6300	1053172902	BUSHING         			BOLKMS	105   	BO105S      	5626006	EU  										M/R DRIVE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PITTED CORROSION ON BUSHING FLANGES ON MAIN ROTOR DRIVE.						1	G	7	2 	3U			 	H3EU    					 
2002060500189	20020605	00189	EU  	2002	6	5	HEEA079266       	1	20020516	G	6220	350A37124420	SCREW           			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH	830  				3248				SCREW CORRODED, COATINGS WORN THROUGH. .						1	G	7	1 	3U			 	H9EU    					 
2002060500193	20020605	00193		2002	6	5	HEEA079272       	4	20020516	G	3457	8143802240D	GPS             			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	972AE					3234				FACEPLATE SEPARATED. FOUND SET SCREWS ON KNOBS WOULD NOT COME OUT.  HAD SET SCREWS DRILLED OUT.  REPLACED LENS AND KNOBS	.  REPAIRED.  CLEANED FACEPLATE AND ALL BUTTONS.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H9EU    					 
2002060500197	20020605	00197		2002	6	5	HEEA079274       	4	20020516	G	2312	DMC634A	ANTENNA         			SNIAS 	350   	AS350B2     	8680813	EU  										VHF SYSTEM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				VHF ANTENNA CRACKED AROUND BOLT HOLES. SCRAPPED.						1	G	7	1 	3U			 	H9EU    					 
2002060500199	20020605	00199	EU  	2002	6	5	HEEA079278       	1	20020516	G	6730	SC5083	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	40466					3004				MAIN ROTOR SERVO LEAKING.						1	G	7	1 	3U			 	H9EU    					 
2002061800039	20020618	00039	NE  	2002	6	18	HEEA079336       	1	20020530	G	2400	7655000902101	RELAY           			SKRSKY	S76   	S76A        	8143006	NE  										ELECTRICAL	FROZEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				SUSPECTED NOT LATCHING PROPERLY AND STUD AT POSITION 21 FROZEN IN PLACE. SCRAPPED.						1	G	7	2 	3U			 	H1NE    					 
2002060700032	20020607	00032	SW  	2002	6	7	HEEA079510       	1	20020528	G	7931	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE OIL	READS LOW       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5759N					33002				PRESSURE READS LOW. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2002060700168	20020607	00168		2002	6	7	HEEA079568       	4	20020530	G	3442	80510800001	CONTROL BOX     			BELL  	206   	206L3       	1182108	SW  										WX RADAR	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6748D					51106				WEATHER RADAR CONTROL BOX INOPERATIVE.  SKYWATCH INTERMITTENTLY HAS DATA FAIL MESSAGE.						1	G	7	1 	3U			 	H2SW    					 
2002061000004	20020610	00004	SW  	2002	6	10	HEEA079588       	1	20020530	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K	13953				36001				FIBERGLASS REPAIR BELOW THE TRIM TAB ON THE MAIN ROTOR BLADE HAS SOME SEPARATION ALONG THE EDGES.						1	G	7	2 	4U			 	H4SW    					 
2002061000100	20020610	00100	SW  	2002	6	10	HEEA079659       	1	20020530	G	7714	412075010105	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				COPILOT TRIPLE TACH READS 2 PERCENT LOW.						1	G	7	2 	4U			 	H4SW    					 
2002061000276	20020610	00276		2002	6	10	HEEA079768       	4	20020531	G	3442	7021450601	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										RADAR SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5748M					28102				WILL NOT PAINT TARGETS.						2	G	7	2 	4U			 	H10SW   					 
2002061800071	20020618	00071		2002	6	18	HEEA079786       	4	20020530	G	2300	071121540	CONTROL PANEL   			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6607K					S841				DIGITS WEAK. REPLACED DISPLAY LENS AND PHOTOCELL.  ALSO REPLACED MISSING FROM END OF KHZ SELECTOR SHAFT.  REPLACED BAD 2	8 VOLT BACKLIGHT BULB AND TOUCHED UP FACEPLATE WITH BLACK PAINT.  BENCH CHECK GOOD.					1	G	7	2 	3U			 	H3EU    					 
2002061800084	20020618	00084	EU  	2002	6	18	HEEA079797       	1	20020530	G	2432	RG390E	BATTERY         			BOLKMS	105   	BO105S      	5626006	EU  										MAIN	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911PF	12   				S718				BATTERY WEAK.						1	G	7	2 	3U			 	H3EU    					 
2002071000059	20020710	00059	NE  	2002	7	10	HEEA079891       	1	20020611	G	6210	7615009043050	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										M/R BLADE	ERODED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5128					760181				FIBERGLASS SKIN ERODED.  INTERNAL DOUBLER UNBONDED, FIBERGLASS BETWEEN ENTER AND OUTER DOUBLER BROKEN.						1	G	7	2 	3U			 	H1NE    					 
2002071000062	20020710	00062	NE  	2002	7	10	HEEA079892       	1	20020611	G	2910	7665009801104	MODULE          			SKRSKY	S76   	S76A        	8143006	NE  										HYD SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	792CH					760193				OVERBOARD DRAIN WILL NOT PASS FLUID OR AIR. REPLACED HYDRAULIC MODULE.						1	G	7	2 	3U			 	H1NE    					 
2002071000116	20020710	00116	GL  	2002	7	10	HEEA079915       	2	20020625	G	7320	0164348810	FUEL CONTROL    			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				ENGINE NOT RESPONDING TO MOVEMENT IN ENG. TRIM MOTOR.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002071000118	20020710	00118	NE  	2002	7	10	HEEA079917       	1	20020625	G	7714	23007981	PICKUP          			SKRSKY	S76   	S76A        	8143006	NE  										TRIPLE TACH	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	792CH					760193				NR 2 ENGINE N2 NEEDLES ON BOTH TRIPLE TACHS ERRATIC, THEN AT ZERO WITH ENGINE RUNNING. REPLACED WITH SERVICEABLE N2 PICK	UP.					1	G	7	2 	3U			 	H1NE    					 
2002071100012	20020711	00012	NE  	2002	7	11	HEEA079922       	1	20020625	G	7714	7645001076101	TACH GENERATOR  			SKRSKY	S76   	S76A        	8143006	NE  										N1	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911UK					760275				WITH STARTER ENGAGED N1 READS BETWEEN 1 AND 6 PERCENT INTERMITTENTLY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2002071100034	20020711	00034	NE  	2002	7	11	HEEA079923       	1	20020625	G	2121	7650007901103	BLOWER          			SKRSKY	S76   	S76C        	8143008	NE  										AIR DIST	ODOR            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH					760505				BLOWER PRODUCING A BURNING SMELL.						1	G	7	2 	3U			NC	H1NE    					 
2002071100036	20020711	00036	NE  	2002	7	11	HEEA079924       	1	20020625	G	6200	7665001802102	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										VTA	LEAKING         	E			HEEA	K				NONE                    				K	L		FLUID LOSS                	NO TEST                   		IN	INSP/MAINT     	1			SW	03	911MJ					760231				DURING LEAK CHECK AFTER INSTALLATION OF VTA ACTUATOR RECEIVED FROM STOCK FOUND ACTUATOR TO BE LEAKING.						1	G	7	2 	3U			 	H1NE    					 
2002071100045	20020711	00045	SW  	2002	7	11	HEEA079927       	1	20020626	G	7712	32447066	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				TORQUE SPLIT. REPLACED WITH SERVICEABLE CONTROL UNIT.						1	G	7	2 	4U			 	H4SW    					 
2002071100072	20020711	00072	GL  	2002	7	11	HEEA079937       	2	20020603	G	7310	23071644	ECU             			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH	2325 				53266				ECU HAS A BROKEN CONNECTOR PIN.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002071200040	20020712	00040	SW  	2002	7	12	HEEA080060       	1	20020611	G	5210	407070620213	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				RT AFT CREW DOOR TRIM PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002071200060	20020712	00060	SW  	2002	7	12	HEEA080075       	1	20020611	G	7714	407375008101	INDICATOR       			BELL  	407   	407         	1182206	SW  										DUAL TACH	INOPERATIVE     	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	496PH					53398				DUAL TACH INDICATOR ROTOR NEEDLE DROPPED TO ZERO.						1	G	7	1 	3U			O	H2SW    					 
2002071500029	20020715	00029	SW  	2002	7	15	HEEA080128       	1	20020626	G	7920	212040232001	VALVE           			BELL  	412   	412         	1182202	SW  										ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2149S					36002				VALVE LEAKS OIL. REPLACED WITH SERVICEABLE VALVE.						1	G	7	2 	4U			 	H4SW    					 
2002071500070	20020715	00070	SW  	2002	7	15	HEEA080149       	1	20020626	G	2840	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				UNIT WILL NOT HOLD CALIBRATION.						1	G	7	2 	4U			 	H4SW    					 
2002071500077	20020715	00077	SW  	2002	7	15	HEEA080153       	1	20020626	G	6321	94501031	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				BRAKE ASSY PUCKS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2002082000017	20020820	00017	SW  	2002	8	20	HEEA080525       	1	20020729	G	7722	3030083	COMPENSATOR     			BELL  	412   	412         	1182202	SW  										ENGINE TRIM	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				ADJUSTMENT PIN LOOSE IN HOUSING.						1	G	7	2 	4U			 	H4SW    					 
2002082100007	20020821	00007		2002	8	21	HEEA080619       	4	20020729	G	3421	504001790116	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	PRECESSES       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				DURING FLIGHT, INDICATOR WILL PRECESS AND DRIFT. REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2002082100012	20020821	00012		2002	8	21	HEEA080623       	4	20020729	G	3421	504001790116	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2149S					36002				HORIZON GYRO PRECESSES TO THE RIGHT. REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2002082100022	20020821	00022	SW  	2002	8	21	HEEA080633       	1	20020729	G	2421	51509002R	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										GENERATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				AFTER SETTING PARALLEL VOLTAGE, UNIT DRIFTS.						1	G	7	2 	4U			 	H4SW    					 
2002082100030	20020821	00030	GL  	2002	8	21	HEEA080639       	2	20020730	G	7200	6898761	ELBOW           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	30KH					51527				ENGINE LINE ELBOW LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002082100075	20020821	00075		2002	8	21	HEEA080666       	4	20020730	G	2350	AA34200	RADIO           			BELL  	206   	206L3       	1182108	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	31801					51074				WEAK RX AUDIO.  LOOSE PARTS INSIDE.						1	G	7	1 	3U			 	H2SW    					 
2002082100098	20020821	00098	SW  	2002	8	21	HEEA080683       	1	20020730	G	2910	C4264215	SLEEVE          			BELL  	206   	206B3       	1181506	SW  										HYD SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03										LEAKED EXTERNALLY APPROX. 1 EA. TEASPOON UNDER PROOF PRESSURE TEST AT INNER SPOOL WITHIN 3 MINUTES.						1	G	7	1 	3U			 	H2SW    					 
2002082100100	20020821	00100		2002	8	21	HEEA080684       	4	20020730	G	2300	CI31020	ANTENNA         			BELL  	206   	206L3       	1182108	SW  										FM SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6603X					51412				FM HAS LOW POWER OUT. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2002082200026	20020822	00026	SW  	2002	8	22	HEEA080714       	1	20020807	G	2840	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL INDICATOR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03										SIGNAL COND UNIT PRODUCING INTERMITTENT LOW FUEL LIGHT WITH FUEL IN AIRCRAFT.						1	G	7	2 	4U			 	H4SW    					 
2002122300045	20021223	00045		2002	12	23	HEEA082389       	4	20021206	G	3130	9806020023	CVR             			CLARK 	1000  	1000CLARK   	2230102	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										COCKPIT VOICE RECORDER CAUSES THE CVR TEST LIGHT TO STAY ON.						1	Q	7	1 	3R			 	2A6     					 
2002122300057	20021223	00057		2002	12	23	HEEA082394       	4	20021212	G	3452	066104100	TRANSPONDER     			SKRSKY	S76   	S76A        	8143006	NE  										ATC	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1546K					760082				INTERMITTENT MODE "C" OPERATION. CLEANED CORROSION FROM UNIT.  FOUND WEAK MTL AND TRANSMIT POWER.  TROUBLESHOT AND REPLA	CED V201 CAVITY OSCILLATOR AND CATHODE ASSY, ADJUSTED FREQUENCY AND POWER TO SPECS.  ALSO FOUND DYNAMIC RANGE OUT OF SPE	CS.  ALIGNED AND ADJUSTED RECEIVER AND VIDEO BOARD SEVERAL TIMES.  BENCH CHECK GOOD.				1	G	7	2 	3U			 	H1NE    					 
2002122300059	20021223	00059		2002	12	23	HEEA082395       	4	20021212	G	3455	066104701	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										ADF	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4253S					760035				WEAK RECEIVE AUDIO, WON'T POINT TO STATIONS. IN SHOP REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2002122300062	20021223	00062		2002	12	23	HEEA082398       	4	20021212	G	3455	066107700	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										ADF	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	22342					760096				ADF RECEIVER FOUND INOPERATIVE. PERFORMED PRELIMINARY INSPECTION.   FOUND IC I306, I307 BAD.  REPLACED.  REPAIRED.  BENC	H CHECK GOOD.					1	G	7	2 	3U			 	H1NE    					 
2002122300064	20021223	00064	NE  	2002	12	23	HEEA082400       	1	20021212	G	3150		WARNING LIGHT   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	ILLUMINATED     	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	1546K					760082				BATTERY HOT LIGHT ON. IN SHOP REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2002122600019	20021226	00019	NE  	2002	12	26	HEEA082429       	1	20021212	G	3212	297800013	BOTTLE          			SKRSKY	S76   	S76A        	8143006	NE  										EMERGENCY FLOAT	DISCHARGED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				EMERGENCY FLOAT BOTTLE DISCHARGED, REPAIRED.						1	G	7	2 	3U			 	H1NE    					 
2002122600026	20021226	00026		2002	12	26	HEEA082435       	4	20021212	G	3442	4000038	CONTROL HEAD    			SKRSKY	S76   	S76A        	8143006	NE  										WX RADAR SYS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	760PH					760078				WEATHER RADAR CONTROL HEAD IS INOPERATIVE. FOUND CORROSION ON UNIT, SWITCH R4/S1 AND VOLUME KNOB BAD.  CLEANED CORROSION	 AND INSTALLED SWITCH AND VOLUME KNOB.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	3U			 	H1NE    					 
2002122700002	20021227	00002	NE  	2002	12	27	HEEA082443       	1	20021212	G	3150	7001840913	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										WARNING SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1546G					760076				TRANCEIVER FLAG STAYS IN OFF POSITION.						1	G	7	2 	3U			 	H1NE    					 
2002122600032	20021226	00032		2002	12	26	HEEA082445       	4	20021212	G	3442	7007700614	DISPLAY         			SKRSKY	S76   	S76A        	8143006	NE  										WX RADAR SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	760PH					760078				WEATHER RADAR SCREEN INTERMITTENTLY COMPRESSES AND FLICKERS.						1	G	7	2 	3U			 	H1NE    					 
2002122700030	20021227	00030	NE  	2002	12	27	HEEA082488       	1	20021213	G	6700		BEARING         			SKRSKY	S76   	S76A        	8143006	NE  										LINK ASSY	RATCHETING      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911MJ					760231				LINK ASSY HAS RATCHETY BEARINGS. REPAIRED.						1	G	7	2 	3U			 	H1NE    					 
2002122700055	20021227	00055	NE  	2002	12	27	HEEA082505       	1	20021213	G	7712	7645001078123	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										TORQUE	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				TORQUE INDICATOR FLUCTUATES IN FLIGHT.						1	G	7	2 	3U			 	H1NE    					 
2002123000082	20021230	00082	SW  	2002	12	30	HEEA082597       	1	20021209	G	6720	PHI214ST103	COUNTERWEIGHT   			BELL  	214   	214ST       	1182106	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				TAIL ROTOR COUNTERWEIGHT HAS WORN BEARINGS. REPAIRED.						2	G	7	2 	4U			 	H10SW   					 
2002123000101	20021230	00101	EU  	2002	12	30	HEEA082616       	1	20021211	G	6710	10531821	CONTROL ROD     			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TAIL ROTOR CONTROL ROD PITCH LINK HAS WORN BEARINGS. REPAIRED.  REPLACED BEARINGS.						1	G	7	2 	3U			 	H3EU    					 
2003010200006	20030102	00006		2003	1	2	HEEA082625       	4	20021211	G	3424	206070274005	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TURN & BANK	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	81832					S828				TURN AND BANK INDICATOR INOPERATIVE.						1	G	7	2 	3U			 	H3EU    					 
2003010200010	20030102	00010	GL  	2003	1	2	HEEA082629       	2	20021211	G	7320	23033400	FILTER          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C30      	03013	GL  					PC AIR	CLOGGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5031U					S678				NR 1 ENGINE PC FILTER CLOGGING WITH WATER ON ENGINE WASH AND CAUSING HANG STARTS. REPLACED WITH SERVICEABLE FILTER.						1	G	7	2 	3U	3	U	 	H3EU    	E1GL				 
2003010200015	20030102	00015	EU  	2003	1	2	HEEA082634       	1	20021211	G	2436	51565000R	VOLT REGULATOR  			BOLKMS	105   	BO105S      	5626006	EU  										DC SYSTEM	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6607K					S841				DC VOLTAGE REGULATOR WILL NOT ADJUST. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H3EU    					 
2003010200020	20030102	00020	EU  	2003	1	2	HEEA082639       	1	20021211	G	7931	BSE206150G3	TRANSDUCER      			BOLKMS	105   	BO105S      	5626006	EU  										OIL PRESSURE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5031U					S678				NO OIL PRESSURE INDICATION. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H3EU    					 
2003010200024	20030102	00024	EU  	2003	1	2	HEEA082643       	1	20021211	G	7712	DK50439	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										DUAL TORQUE	READS LOW       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5031U					S678				DUAL TORQUE INDICATOR READS LOW.						1	G	7	2 	3U			 	H3EU    					 
2003010300046	20030103	00046	GL  	2003	1	3	HEEA082666       	2	20021211	G	7320	23073525	ELBOW           			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20      	03013	GL  					PC FILTER	STRIPPED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				PC FILTER SIDE STRIPPED. SCRAPPED.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003010300056	20030103	00056	EU  	2003	1	3	HEEA082676       	1	20021211	G	2820	AE705801	HOSE            			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7170D					S840				FUEL HOSE LEAKING. REPLACED WITH SERVICEABLE HOSE.						1	G	7	2 	3U			 	H3EU    					 
2003010300057	20030103	00057	EU  	2003	1	3	HEEA082677       	1	20021211	G	7712	DK50439	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										DOUBLE TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7170D					S840				INDICATOR SHOWING NR 1 NG TORQUE FLUCTUATIONS.						1	G	7	2 	3U			 	H3EU    					 
2003010600148	20030106	00148	GL  	2003	1	6	HEEA082799       	2	20021216	G	7261	0292217030	LABYRINTH SEAL  			AEROSP	AS355 	AS355*      	       	EU  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AE					3229				CARBON BUILD UP IN LABYRINTH SEALS CAUSING BINDING NG.						1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2003010600149	20030106	00149	GL  	2003	1	6	HEEA082800       	2	20021216	G	7323	0292928540	METERING VALVE  			AEROSP	AS355 	AS355*      	       	EU  	ALLSN 	250C  	250C20      	03013	GL  					TURBINE GOVERNOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	972AE	326  				3234	22065			FUEL LEAKING FROM CASE DRAIN OF METERING VALVE.						1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2002020500049	20020205	00049	SO  	2002	2	5	HO1R15248        	1	20020119	G	5711	6205401	SPAR            			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					RT WING	CORRODED        	B			HO1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	7728J	3679 				321130	R1351240			DURING ANNUAL INSPECTION THE RIGHT WING AFT ATTACH FITTING OUTBOARD OF THE FUSELAGE AND AFT WING SPAR WERE FOUND TO EXHI	BIT DISSIMILAR METAL CORROSION BETWEEN THE STEEL ATTACH FITTING AND THE REAR SPAR.  THE AFT SPAR WAS CORRODED TO THE POI	NT WHERE A CRACK HAD DEVELOPED IN THE REAR SPAR.  CRACK WAS NOT FOUND UNTIL STEEL ATTACH FITTING WAS REMOVED FOR HIDDEN 	DAMAGE INSPECTION.			1	L	7	1 	3O	3	O	 	A3SO    	E295				 
2002031300148	20020313	00148	CE  	2002	3	13	IC1D213K         	1	20020212	G	5320	53120252	CHANNEL         			CESSNA	340   	340A        	2076405	CE  										HORIZONTAL STAB	CRACKED         	D			IC1D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	324WA	3012 				340A0608				AIRCRAFT PAN CHANNEL JUST BELOW HORIZONTAL STABILIZER AFT SPAR ON EMPENAGE STRUCTURE HAS (NR 2)-.7500 INCH CRACKS IN RAD	IUSED AREAS.  CRACKS WERE FOUND ON ANNUAL INSPECTION PROBABLE CAUSE UNKNOWN STRESS. RECOMMENDATION: DETAILED INSPECTION 	AT ANNUAL INSPECTION.				1	L	7	2 	3O			 	3A25    					 
2002071900070	20020719	00070	EU  	2002	7	19	IO5R080367       	1	20020711	G	2121	A206621250	FAN             			UROCOP	EC120 	EC120B      	8680987	EU  										AIR DISTRIBUTION	BROKEN          	H			IO5R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	488SH	257  				1181				PLASTIC FINS BROKEN, WILL NOT ADJUST RMA#RO37749 REMOVED AND REPLACED						1	G	7	2 	3U			NC	R0001RD 					 
2002101500024	20021015	00024	EU  	2002	10	15	IO5R081096       	1	20021003	G	2434	23081057	STARTER         			UROCOP	EC135 	EC135P1     	8680990	EU  										NR 1	FAILED          	H			IO5R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			FS	01	551BA	376  				188				STARTER WILL NOT ROTATE INSTALLED LOANER ASSY.						1	G	7	2 	3U			O	H88EU   					 
2002012300135	20020123	00135	EU  	2002	1	23	ISHA077549       	1	20020116	G	6220	704A33633156	BEARING         			SNIAS 	350   	AS350D1     	8680804	EU  										MAIN ROTOR	WORN            	H			ISHA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	301EX	983  				1358				WARRANTY CREDIT FOR WORN PART WHICH HAS A S.L.L.OF 6400.0 HRS. AND ONLY LAST 982.5 HRS.						1	G	7	1 	3U			 	H9EU    					 
2002012900012	20020129	00012	NM  	2002	1	29	IVSA077688       	1	20020123	G	7600	B2475	GOVERNOR        			ROBSIN	R22   	R22BETA     	7640110	NM  										ENGINE	DEFECTIVE       	H			IVSA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	HP145	593  				1031				GOVERNOR MOTOR RUNS SLOWLY,  TAKING 10-12 SECONDS TO BRING RPM UP TO FLIGHT RPM REPLACEMENT MOTOR INSTALLED, DEFECTIVE U	NIT RETURNED TO ROBINSON FOR WARRANTY EXCHANGE OR REPAIR.					1	G	7	1 	3O			 	H10WE   					 
2002041900027	20020419	00027	WP  	2002	4	19	IVSA078430       	1	20020409	G	6310	A1902	BELT            			ROBSIN	R22   	R22         	7640102	WP  										ENG TO ROTOR	STRETCHED       	H			IVSA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			FS	01	7101J	3    				3005				BELTS WERE REPLACED DURING 100HR INSPECTION AFTER 693.3 HOURS TSI.  FAN WHEEL WAS BALANCED AND RUNUP WAS NORMAL.   FIRST	 FLIGHT OF APPROXIMATELY 2 HOURS WAS UNEVENTFUL.  DURING SECOND FLIGHT PILOT REPORTED CLUTCH LIGHT FLICKERED ON AND OFF 	SEVERAL TIMES.  ON INSPECTION AFTER PRECAUTIONARY LANDING, BELTS WERE FOUND STRETCHED TO THE POINT THAT OVER LIMIT SWITC	H DEACTIVATED THE SYSTEM. SYSTEM INSPECTED WITH NO FAULTS FOUND OTHER THAN BELT STRETCH BEYOND LIMITS.  NEW BELTS WERE I	NSTALLED AND ADJUSTED.  FAN WHEEL BALANCE CHECKED.		1	G	7	1 	3O			 	H10WE   					 
2002111400086	20021114	00086	CE  	2002	11	14	JAC001RR         	1	20021108	G	2810	41423	CELL            			CESSNA	414   	414         	2075908	CE  										FUEL STORAGE	DETERIORATED    	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	414TH	2720 	2720 			4140400				DURING ANNUAL INSPECTION, LEFT WING OUTBOARD AUX FUEL CELL LEAKAGE NOTED. UPON INVESTIGATION, FUEL CELL FOUND TO BE SERI	OUSLY DETERIORATED AROUND THE FILLER PORT OPENING. THE FUEL CELL MATERIAL AT THAT POINT HAD BECOME BRITTLE. SUGGEST THOR	OUGH EXAMINATION OF FUEL CELLS CONDITIONS DURING ALL SCHEDULED INSPECTIONS.				1	L	7	2 	3O			RT	A7CE    					 
2002111400087	20021114	00087	SO  	2002	11	14	JAC002RR         	1	20021108	G	7810		EXHAUST PIPE    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	WRONG PART      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	5494R		48   			317405410	RL324361A			DURING 100 HOUR/ANNUAL INSPECTION, LT ENGINE TURBOCHARGER EXHAUST PIPE WAS NOTICED TO BE ABNORMAL, IN THAT IT WAS ASSEMB	LED OF 13 WELDED SEGMENTS, WHEREAS THE CORRECT PART CONSISTS OF TWO WELDED SEGMENTS. PART WAS REPLACED WITH THE CORRECT 	ITEM, PART NUMBER 40310-10. NO MENTION OF INSTALLATION FOUND IN THE AIRCRAFT RECORDS. SUGGEST THAT A CAREFUL WATCH FOR B	OGUS PARTS IS INCLUDED IN ALL MAINTENANCE FUNCTIONS.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002052300010	20020523	00010	CE  	2002	5	23	JG0201741        	1	20020521	G	3242	5007916	BRAKE ASSY      			MTSBSI	MU300 	MU300       	5780602	CE  										MLG	DISINTEGRATED   	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	11	574CF	483  				A079SA				WHILE TAXIING AFTER LANDING FELT AIRCRAFT SHUTTER. STOPPED AIRCRAFT ON TAXIWAY AND VISUALY INSPECTED OUTSIDE OF AIRCRAFT	 NO DEFECTS NOTED. CONTINUED TAXI TO PARKING. MAINTENANCE REMOVED LT WHEEL AND FOUND BRAKE ASSEMBLY HAD CAME APART.					2	H	7	2 	4F			RT	A14SW   					 
2002032700171	20020327	00171	SW  	2002	3	27	JJWA078248       	1	20020321	G	5302	206020123048S	RIB             			BELL  	206   	206B        	1181511	SW  										HORIZONTAL STAB	CRACKED         	H			JJWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	281CB	10170				3303				REMOVED BOTH HORIZONTAL STABILIZERS THAT HAD BEEN LAST INSTALLED OVER 5 YEARS AGO. FOUND EXCESSIVE CORROSION IN SPAR CLA	MP AREA ON RIB CLOSEST TO TAILBOOM. REQUIRES TOTAL RIBE REPLACEMENT OF $1966 RIB. INSPECTED OTHER RIB ALSO HAD CORROSION	 & PIECE MISSING SO REPLACED 206-020-123-047S RIB ON THAT SIDE ALSO. THIS IS SECOND REPORT IN LESS THAN YEAR ON SAME PAR	TS. SUGGEST BELL HELICOPTER INSERT A 3 YEAR INSPECTION IN MAINTENANCE MANUAL, ESPECIALLY WHEN AIRCRAFT IN CORROSIVE ENVI	RONMENT LIKE THE STATE OF FLORIDA.		1	G	7	1 	3U			 	H2SW    					 
2002071900148	20020719	00148	SO  	2002	7	19	JK001            	2	20020527	G	8550		OIL SYSTEM      								CONT  	O360  	IO360D      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	LOW             	G				A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			GL	03	2442									DURING CRUISE FLIGHT OIL PRESSURE WAS NOTED TO BE LOW AND FLUCTUATING, ALONG WITH SEVERE VIBRATION.  THIS WAS FOLLOWED B	Y A COMPLETE LOSS OF OIL PRESSURE AND SUBSEQUENT LOSS OF POWER.  THE ENGINE EXPERIENCED INTERNAL FAILURE FOR UNKNOWN REA	SONS RESULTING IN THREE LARGE HOLES IN THE ENGINE CASE.									3	O			E1CE	5	C	P3EA	 
2002102500011	20021025	00011	WP  	2002	10	25	JV2R200200001    	2	20021024	G	7261	30726361	LINE            			PIPER 	PA23  	PA23        	7102302	SO  	GARRTT	TFE731	TFE7313R1D  	01518	WP  					LEFT ENGINE	CHAFED          	B			JV2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	03	7SE	6830 				231127	P83169			REPORTED OIL LEAK, REMOVED COWLING TO INSPECT FOR OIL LEAK, REMOVED CLAMP AND INSPECTED TO FIND THE CLAMP HAD CHAFED THE	 LINE WHICH CAUSED AN OIL LEAK. THE TEFLON ON THE CLAMP WAS WORN CAUSING METAL TO METAL CONTACT.  INSPECTING THE LINE AT	 THE CHAFED AREA AND USING THUMB NAIL, A HOLE WAS CREATED.				1	L	7	2 	3O	4	F	 	1A10    	E6WE				 
2002111400089	20021114	00089	WP  	2002	11	14	JV2R200200003    	2	20021106	G	7261	30726361	LINE            			RKWELL	NA265 	NA26565     	7630107	CE  	GARRTT	TFE731	TFE7313R1D  	01518	WP  					NR 1 ENGINE	NICKED          	B			JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	750CC	7625 				46537	P83175			WHEN COMPLYING WITH CAMP CARDS, A VISUAL INSPECTION OF THE ENGINE WAS PERFORMED AND FOUND THE OIL LINE HAD NICKS IN IT C	AUSE BY THE CLAMPS THAT HAD THE TEFLON WORN CAUSING METAL TO METAL CONTACT.  REPACED LINE AND CLAMPS.					2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2002111400090	20021114	00090	WP  	2002	11	14	JV2R200200004    	2	20021106	G	7261	30726361	LINE            			RKWELL	NA265 	NA26565     	7630107	CE  	GARRTT	TFE731	TFE7313R1D  	01518	WP  					NR 2 ENGINE	NICKED          	B			JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	750CC	7603 				46537	P83176			WHEN COMPLYING WITH CAMP CARDS, A VISUAL INSPECTION OF THE ENGINE WAS PERFORMED AND FOUND THE OIL LINE HAD NICKS IN THE 	LINE CAUSE BY THE CLAMPS, THAT HAD THE TEFLON WORN CAUSING METAL TO METAL CONTACT.  REPLACED LINE AND CLAMPS.					2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2002042200038	20020422	00038	EU  	2002	4	22	KBMA112001       	1	20020108	G	2612	0301037070	HARNESS         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FIRE DETECTION	SEPARATED       	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19		502  					4173			FERRILS UNBONDED/SEPARATED.  REPLACED WITH NEW HARNESS.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002081400016	20020814	00016	CE  	2002	8	14	L2232            	1	20020805	G	5712	57222062	RIB             			CESSNA	441   	441         	2076020	CE  										RT CENTER WING	CRACKED         	B			LK0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	666HC	7255 				4410292				DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (LCWS 26.85	") HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45") AND EXTENDING APPROXIMATELY 1" AFT OF	 THE SPAR. AFTER REMOVAL FO THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE B	END RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK. CESSNA CURRENTLY DOES NOT HAVE	 ANY SPECIFIC INSPECTIONS RELATING TO THIS MATTER, THEREFORE, THIS AREA SHOULD BE CLOSELY INSPECTED DURING ROUTINE INSPE	CTIONS.	1	L	7	2 	3T			RT	A28CE   					 
2002081400017	20020814	00017	CE  	2002	8	14	L2240            	1	20020805	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										LT CENTER WING	CRACKED         	B			LK0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	666HC	7255 				4410292				DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIBCAP P/N: 5722206-1 (LCWS 26.85 I	NCH) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45 INCH) AND EXTENDING APPROXIMATELY 1IN	CH AFT OF THE SPAR. AFTER REMOVAL FO THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED W	ITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK.			1	L	7	2 	3T			RT	A28CE   					 
2002103000238	20021030	00238	NE  	2002	10	30	MDR00402         	2	20021009	G	7230	1711M20P08	SEAL            								GE    	GE90  	GE9090B     	 	NE  					1ST STAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		20177					900207			FPI INDICATIONS FOUND IN STAGE 1 BLADE RETAINER ARM AT EACH BLADE LOCATION.  ITEM TO BE RETURNED TO MFG FOR DETAILED ANA	LYSIS.  PART WOULD HAVE BEEN REDUNDANT TO SB 72455.										4	F			E00049EN				 
2003020500029	20030205	00029	CE  	2003	2	5	MEA200301        	1	20021227	G	5610	1013840227	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	FAILED          	C				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			GL	23	593MA	614  				FL68				A/C WAS ENROUTE AT FL260, WINDSHIELD ANTI-ICE WAS SELECTED ON AND WAS ON FOUR 1 1/2 HOURS WHEN A LOUD CRACK WAS HEARD AN	D THE PILOTS WINDSHIELD SHATTERED THE INNER PANE INTO PEA SIZED PIECES. CREW FOLLOWED AIRCRAFT ABNORMAL PROCEDURES AND D	ESCENDED BELOW 25,000 FEET AND KEEP CABIN PSI BETWEEN 2 AND 4.6. OAT AT TIME WAS -35C. AIRCRAFT WAS FLOWN BACK TO HOME B	ASE.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2002032800009	20020328	00009	CE  	2002	3	28	N421DG030102     	1	20020321	G	3230		HYDRAULIC SYSTEM			CESSNA	421   	421C        	2076016	CE  										MLG	CONTAMINATED    	G				L				ABORTED APPROACH        				G			MULTIPLE FAILURE          			LD	LANDING        	1			NM	11	421DG					421C0456				EXTENDED THE MLG ON APPROACH AND ONLY THE LT LOCKED INTO PLACE. NOTIFIED TOWER OF THIS CONDITION AND MANEUVERED WHILE WO	RKING ON THE PROBLEM.  INITIATED THE APPROACH AGAIN AND EXECUTED EMERGENCY PROCEDURES,  ONLY LT MAIN WAS LOCKED, THE LAN	DING WAS INITIATED AND THE A/C TOUCHED DOWN WITH LT DOWN AND LOCKED, THE RT WAS PARTIALLY EXTENDED BUT NOT LOCKED, THE N	OSE GEAR WAS EXTENDED BUT IT WAS NOT LOCKED. NLG STAYED EXTENDED ON ROLL OUT AND THE RT WING, AILERON, FLAP, AND PROP SU	STAINED DAMAGE. HYD MLG SYS WAS INSPECTED. FLUID WAS EXAMINED, AND A SMALL AMOUNT OF WATER WAS FOUND.  IN SHOP AT 60 DEG	 F THE MLG FUNCTIONED NORMALLY. IT APPEARS THAT MOISTURE IN THE HYD SYS FROZE AND PREVENTED FUNCTION OF THE MLG.	1	L	7	2 	3O			 	A7CE    					 
2002071600200	20020716	00200	CE  	2002	7	16	ODAR0184         	1	20020207	G	3710	442CW12	PUMP            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					VACUUM SYS	FAILED          	B			ODAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	707PW					TH1106				PILOT EXPERIENCED A DUAL VACUUM PUMP FAILURE IN VFR CONDITIONS.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002051500184	20020515	00184	CE  	2002	5	15	OG5R092N         	1	20020508	G	2810	715371	FUEL TANK       			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360H1A  	41514	EA  	HARTZL	HCC2Y	HCC2YR4     	GL  	FUSELAGE	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21		390  					L2592851A	AU10095B		DURING ANNUAL INSPECTION A FUEL LEAK WAS NOTED ON THE BOTTOM OF THE LEFT WING BENEATH THE FUEL TANK. UPON MORE DETAILED 	INSPECTION THE INTERNAL BAFFLING OF THE FUEL TANK WAS FOUND TO BE SEPERATED AND THE TANK TO BE LEAKING FROM ONE OF THE B	AFFLE ATTACH WELDS. RESEARCH OF THIS AIRCRAFTS HISTORY REVEALED THAT THIS HAS HAPPENED 3 TIMES PRIOR. THE ORIGINAL TANK 	WAS REPLACED AT 1728.1 TOTAL TIME, THE NEXT 3 LASTED 396.0, 647.6 AND 390.0 CONCURRENTLY. WE FEEL THAT THE DESIGN OF THE	 TANK CONTRBUTES TO ITS FAILURES. THE INTERNAL BAFFLE IS WELDED IN THE TANK DIRECTLY UNDER THE CENTER MOUNTING STRAP FOR	 THE TANK CAUSING A PRELOAD UPON INSTALLATION. DURING USE FOR ACROBATIC FLIGHT THE TANKS CANNOT BE FILLED DUE TO WEIGHT 	1	H	7	1 	3O	3	O	 	A21CE   	1E10	5	C	P920	 
2003010600040	20030106	00040	SO  	2003	1	6	P49R490N         	2	20021221	G	7320	AN737TW26	CLAMP           	CONT        		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					BALANCE TUBE	BROKEN          	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			NE	05	4898N					18267445				PILOT REPORT REPORTED SMOKE FROM THE COWLING DURING AN ATTEMPTED ENGINE START DURING COLD WEATHER. FOUND FIRE STARTED AT	 CLAMP SUPPORT FOR THE ENGINE INDUCTION SYSTEM BALANCE TUBE. CLAMP HAD BROKEN AND TUBE HAD CHAFED THROUGH DUE TO LOOSE A	ND BROKEN CLAMP. RAW FUEL LEAK OUT DURING START ATTEMPT AND WAS IGNITED THOUGH PARTIAL IGNITION. THIS IS THE SECOND BROK	EN BALANCE TUBE CLAMP IN ONE MONTH ON THE 182 SERIES AIRCRAFT WITH REPLACEMENT OF THE BALANCE TUBE REQUIRED.  SUGGEST CA	REFUL VISUAL INSPECTION ANYTIME THE LOWER COWLING IS REMOVED AND USE PROPER TORQUE ON THE CLAMP WHEN INSTALLING.		1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003061100010	20030611	00010	CE  	2003	6	11	PF212LW          	1	20021029	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A11      	52043	NE  					COCKPIT	FAILED          	P				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CE	07	212LW					BB1420				INNER PANE OF PILOTS WINDSHIELD SHATTERED WHILE CLIMBING THROUGH 28000 FEET.						1	L	7	2 	4T	3	T	 	A24CE   	E4EA				 
2002041900030	20020419	00030	GL  	2002	4	19	R377W            	1	20020418	G	2720	AN37A	BOLT            			CIRRUS	SR    	SR22        	2130001	GL  										RUDDER PEDLE	SHEARED         	B				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CE	03	225CD					0031				PILOT NOTICED RUDDER PEDALS STIFF DURING TAXI.  PILOT FELT RUDDER PEDALS GIVE WAY.  DURING INSPECTION, FOUND CO-PILOT'S 	RUDDER PEDAL TORQUE TUBE INBOARD AFT MOUNTING BRACKET BOLT PN AN3-7A SHEARED.  FOUND CO-PILOT'S INBOARD MOUNTING BRACKET	 BENT PN 11478-001 AND BUSHING PN 11504-001 DAMAGED.   BOLT APPEARS TO HAVE BEEN OVERTORQUED WHICH WEAKENED ITS SHEAR ST	RENGTH.   REPLACED BRACKET, BUSHING AND ALL HARDWARE.  SENT DAMAGE PARTS TO CIRRUS FOR ANALYSIS.			1	L	7	1 	3O			NT	A00009CH					 
2002090400084	20020904	00084	GL  	2002	9	4	R895W25          	1	20020830	G	5330		PLATE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					FUSELAGE	DELAMINATED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	214BB					0085	685824			DURING ANNUAL INSPECTION, FOUND LOWER FORWARD FUSELAGE EXHAUST HEAT PLATE DELAMINATED.  FURTHER INSPECTION REVEALED HOT 	SPOT UNDERNEATH CO-PILOT'S RUDDER PEDAL INSPECTION PANEL ABOVE THE EXHAUST AREA OUTLET.  ALSO FOUND VISIBLE LIGHT SHOWIN	G THROUGH THE COMPOSITE STRUCTURE AT THE FIREWALL AND FUSELAGE BELLY.  INVESTIGATED AIRCRAFT N225CD, SN: 0031 AND FOUND 	SAME HOT SPOT CREATED BY THE SHORT EXHAUST SYSTEM.  SUSPECT THE EXHAUST TAILPIPE IS TOO SHORT FOR EXHAUST GASES TO CLEAR	 THE COMPOSITE FUSELAGE LOWER STRUCTURE.		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2002041100091	20020411	00091	WP  	2002	4	11	RFTO             	1	20020410	G	2742	AJH7150501	JACKSCREW       			DOUG  	DC10  	DC1010      	3022110	WP  										ELEVATOR	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	910SF	69567								JACKSCREW REMOVED FROM A DC10-10,N910SF, THIS PART TO OUR KNOWLEDGE HAS 69567 HOURS, 25480 LANDINGS AND WAS INSTALLED IN	 PRODUCTION 1971. WE SENT THE UNIT IN FOR INSPECTION AND OVERHAUL AS NECESSARY TO THE PART MANUFACTURE AS THERE IS NOT A	 CURRENT INSPECTION/OVERHAUL PERIOD CALLED OUT IN THE MPD FOR THE DC10. THE TEARDOWN REPORT INDICATED CONCENTRICITY MEAS	UREMENT AT MIDDLE SECTION IS .010 INCH AND THE MAX. IS .004 INCH. THE BUSHING HOLE DIAMENTIONS FOR THE SCREW WERE 1.7510	/1.7518 THE MAX. LIMIT IS 1.7510. THE JACKSCREW BEARING HAS EXCESSIVE PLAY WITH THE LOWER TEFLON SEAL MISSING.		2	L	7	3 	4F			 	A22WE   					 
2002081400022	20020814	00022	EU  	2002	8	14	RX8R2002001      	1	20020719	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	FAILED          	B			RX8R	A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			SO	15	4043L		362  			3015	9318			DURING FLIGHT AT 2500 FT. ONE SET OF BRUSHES IN THE STARTER GENERATOR FAILED. THE GENERATOR WAS STILL PUTTING OUT 28 VDC	 THROUGH THE REMAINING BRUSHES SO THE GENERATOR WARNING LIGHT DID NOT ILLUMINATE. THE GENERATOR WAS NOT PUTTING OUT ENOU	GH CURRENT IN ITS DAMAGED STATE TO KEEP THE AIRCRAFT BATTERY CHARGED. THE AIRCRAFT BATTERY SLOWLY LOST VOLTAGE TILL ALL 	AIRCRAFT ELECTRICAL POWER FAILED WITHOUT WARNING.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002090400089	20020904	00089	NE  	2002	9	4	S3898            	2	20020819	G	7250	311818101	RIVET           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					HP TURBINE	ERODED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	457CW	2505 				RK57				HIGH PRESSSURE TURBINE BLADE RETAINING RIVETS AND COLLARS APPEAR TO BE SUFFERING EROSION CAUSING RIVET TAILS TO FALL BEL	OW THE .050 INCH PROTRUSION AS OUTLINED IN THE MFG SB. IN ITS CURRENT CONDITION ALL 71 EA. RIVETS (PN 311588901) COLLARS	 (PN 311683801) ARE BEING REPLACED WITH NEW.				2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2002071900151	20020719	00151	SO  	2002	7	19	S5248            	1	20020612	G	5740		FITTING         			PIPER 	PA32  	PA32R300    	7103213	SO  										RT WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	882TM	1852 				32R7780273				RIGHT AFT WING ATTACMENT FITTING CORRODED,INSPECTED IAW PSB977 CORROSION MORE THAN SURFACE DEEP PITS						1	L	7	1 	3O			 	A3SO    					 
2002112100005	20021121	00005	EU  	2002	11	21	S5656            	1	20021120	G	2510	TYPE3431	SEAT BELT       			SOCATA	TBM   	TBM700      	8682000	EU  										COCKPIT	FAILED          	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	700PP					59				REF. SAIB NO.CE-02-44 DATED SEPTEMBER 4, 2002 PREBUY ON AIRCRAFT CHECK,  ALL CABIN AND COCKPIT SEAT BELTS COULD BE PULLE	D APART WITH A SLIGHT PULL OR TUG.  WOULD NOT STAY ENGAGED RECOMMEND REPLACEMENT OF ALL BELTS WITH NEWER STYLE					1	L	7	1 	3T			RT	A60EU   					 
2002081400023	20020814	00023	NE  	2002	8	14	SQM212002        	3	20020813	G	6110		PROPELLER       			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 4 ENGINE	LEAKING         	B				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	99	401LC					N401LC	550348	230992		APPROXIATELY 3.5 HRS INTO THE FLIGHT AT 0515 Z (ENROUTE TO OKO), PILOT ENCOUNTERED PROPELLER LOW OIL LIGHT. VISUAL INSPE	CTION CONFIRMED FLUID LEAKED AT NR 4 PROPELLER HOUSING. THE NR  4 ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO PLA.  DU	RING THE DEFECT SIMULATION CHECK, HYDRAULIC FLUID WAS FOUND LEAKING FROM THE PROPELLER SHAFT HOUSING WHILE THE PROPELLER	 WAS SELECTED TO FEATHER POSITION.			2	H	7	4 	4T	4	T	 	A1SO    	E282	6	C	P906	 
2002031400026	20020314	00026	NM  	2002	3	14	SROM200200001    	1	20020204	G	5315	6545834109	FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	31030	4865 			23465				CORROSION ON FLOORBEAM BS 294.5,  LBL12,  WL208  CUT OUT AND REPLACED CORRODED SECTION OF FLOORBEAM PER SRM 53-10-2 & 53	-10-9.					2	L	7	2 	4F			RT	A16WE   					 
2002031400028	20020314	00028	NM  	2002	3	14	SROM200200002    	1	20020202	G	5315	6545810502	FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	31030	4865 			23465				CORROSION ON FLOOR BEAM B.S.312  LBL 12 TP RBL 12  WL 208.  REMOVED CORROSION, FOUND OUT OF LIMITS PER SRM 53-10-1 FIG. 	1.  FABRICATED REPAIR PARTS, COMPLETED REPAIR TO B.S. 312 FLOOR BEAM PER SRM 53-10-9 FIG. 5.					2	L	7	2 	4F			RT	A16WE   					 
2002031400030	20020314	00030	NM  	2002	3	14	SROM200200003    	1	20020127	G	5330	6545775	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	31030	1304 			23465				GOUGE ON FUSELAGE SKIN AT B.S. 791.  6 INCHES BELOW STR. 23 RIGHT.  BLENDED GAUGE .028 REMAINING OUT OF LIMITS.  REPAIRE	D IAW SRM 53-30-3  FIG. 46.					2	L	7	2 	4F			RT	A16WE   					 
2002031400032	20020314	00032	NM  	2002	3	14	SROM200200004    	1	20020216	G	5330	6545774	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30928	1480 			23466				DURING C CHECK INSPECTION FOUND FUSELAGE SKIN HAS SEVERAL DENTS FROM B.S. 847 TO 872 BETWEEN STR. 19R AND 20R.  REMOVED 	DAMAGE 11 INCHES X 7 INCHES AT STA. 864 TO 874.  FABRICATED REPAIR DOUBLE & FILLER, ALODINED & PRIMED AND INSTALLED PART	S PER SRM 53-30-2 FG 6 PG 11-12A AND SRM 51-10-02.				2	L	7	2 	4F			RT	A16WE   					 
2002031400033	20020314	00033	NM  	2002	3	14	SROM200200005    	1	20020216	G	5330	6545774	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30928	1480 			23466				DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 910, 2 INCHES BELOW STRINGER 22R.  REPAIRED DENT IN FUSELA	GE SKIN AT B.S. 910 2" BELOW STRINGER I.A.W. SRM 53-30-03 PAGE 97.					2	L	7	2 	4F			RT	A16WE   					 
2002031400034	20020314	00034	NM  	2002	3	14	SROM200200006    	1	20020216	G	5330	6545774	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30928	1480 			23466				DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 898, 2 INCHES ABOVE STRINGER 24R.  DENT FOUND TO BE OUT OF	 LIMITS.  REMOVED DAMAGE IN A 4X8 INCH AREA.  FABRICATED DOUBLER AND FILLER AND INSTALLED PER SRM 53-30-03 FIG. 6.					2	L	7	2 	4F			RT	A16WE   					 
2002031400037	20020314	00037	NM  	2002	3	14	SROM200200007    	1	20020218	G	5315	654681025	FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30928	4838 			23466				DURING C CHECK INSPECTION FOUND AT BS 967 RBL 29 W.L. 208 FASTNER HOLE IN FLOOR BEAM ELONGATED.  CUT OUT FWD. FLANGE OF 	BS 967 UPPER FLOORBEAM CHORD AT RBL 29 AND RBL 43 IN A 1.2 X 3 INCH AREA.  FABRICATED REPAIR ANGLES AND FILLERS AND INST	ALLED REPAIR PER SRM 53-10-09 FIG. 7.				2	L	7	2 	4F			RT	A16WE   					 
2002031400038	20020314	00038	NM  	2002	3	14	SROM200200008    	1	20020219	G	5315	6545815108	FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30928	4838 			23466				DURING C CHECK INSPECTION FOUND CORROSION ON FLOORBEAM STA 344 LBL 2 TO RBL 10 WL 208.  REPAIRED PER SRM 53-10-9 FIG. 6.						2	L	7	2 	4F			RT	A16WE   					 
2002031400040	20020314	00040	NM  	2002	3	14	SROM200200009    	1	20020220	G	5311	6546525	FRAME           			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30928	4838 			23466				DURING C CHECK INSPECTION  FOUND FRAME SHEAR TIE BS 380 BETWEEN STR 20 RT & STR 21 RT TO HAVE ELONGATED HOLES.  REMOVED 	DAMAGE SECTION OF FRAME SHEAR TIE, FABRICATED NEW SECTION & INSTALLED I.A.W. SRM 53-10-4 FIG. 8.					2	L	7	2 	4F			RT	A16WE   					 
2002031400042	20020314	00042	NM  	2002	3	14	SROM200200010    	1	20020216	G	5230	6547952161	BEAM            			BOEING	737   	737205      	1384456	NM  										CARGO DOOR	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30928	1480 			23466				DURING C CHECK INSPECTION FOUND AFT CARGO DOOR NR 1 TRANSVERSE BEAM FROM BOTTOM O/B T-CHORD VERTICAL FLANGE CRACKED AT F	WD STOP-PIN FITTING BETWEEN FIRST & SECOND FASTNER.  REMOVED AFT CARGO DOOR TRANSVERSE BEM & INSTALLED REPLACEMENT BEAM.					2	L	7	2 	4F			RT	A16WE   					 
2002031400043	20020314	00043	NM  	2002	3	14	SROM200200011    	1	20020227	G	5230	654692124	BEAM            			BOEING	737   	737205      	1384456	NM  										CARGO DOOR	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30956	1480 			23466				DURING C CHECK INSPECTION FOUND FORWARD CARGO DOOR NR 1 TRANSVERSE BEAM FROM BOTTOM O/B TEE CHORD CRACKED ON VERTICAL FL	ANGE AT AFT STOP PIN FITTING BETWEEN FASTNESRS.  REPAIRED TEE CHORD PER ASA EM 5230-01097 STEP 6 C OF SECTION 2.					2	L	7	2 	4F			RT	A16WE   					 
2002031400044	20020314	00044	NM  	2002	3	14	SROM200200012    	1	20020227	G	5310	6549921116	DOOR FRAME      			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30956	1480 			23466				DURING C CHECK INSPECTION FOUND FORWARD CARGO DOOR FORWARD LOWER FRAME CRACKED AT NR  4 FWD STOP FITTING.(COUNTING FROM 	TOP TO BOTTOM)  REMOVED AND REPLACED FRAME PER ASA EM 5230-01097.					2	L	7	2 	4F			RT	A16WE   					 
2002031400046	20020314	00046	NM  	2002	3	14	SROM200200013    	1	20020216	G	5330	6545768238	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA	30928	1480 			23466				DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 404 1 INCH ABOVE STRINGER 19R.  TRIMMED OUT DAMAGE, INSTAL	LED REPAIR PER ER 02-0215   ASA EA 5330-01572					2	L	7	2 	4F			RT	A16WE   					 
2002032800013	20020328	00013	NM  	2002	3	28	SROM200200014    	1	20020326	G	3350		BULB            			BOEING	737   	737205      	1384456	NM  										CABIN	BURNED OUT      	C			SROM	K				NONE                    				L			NO TEST                   			NR	NOT REPORTED   	1			AL	03	733PA		6    			23466				OVERHEAD BIN EMERGENCY LIGHTS ROW 9 (RT) AND LAST 3 LIGHTS ON LT SIDE OUT.  RELAMPED AND ALL OPS NORMAL						2	L	7	2 	4F			RT	A16WE   					 
2002042400052	20020424	00052	NM  	2002	4	24	SROM200200015    	1	20020422	G	3350	6013211	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										CABIN	DISCHARGED      	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				AFT LT BULLNOSE EMERGENCY LIGHTS INOPERATIVE.  REPLACED AFT OVERHEAD EMERGENCY LIGHTS BATTERY PACK.  ALL OPS NORMAL.  RE	F. 33-51-151					2	L	7	2 	4F			RT	A16WE   					 
2002071900154	20020719	00154	NM  	2002	7	19	SROM200200016    	1	20020628	G	3350	58209	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										CABIN	DISCHARGED      	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				L2 EMERGENCY EXIT SIGN LIGHT DIM.  REPLACED BOTH AFT EXIT SIGNS AND BATTERY PACK AT L2 DOOR.  OPS CHECKED NORMAL.						2	L	7	2 	4F			RT	A16WE   					 
2002081400024	20020814	00024	NM  	2002	8	14	SROM200200017    	1	20020804	G	3350	6013211	BATTERY PACK    			BOEING	737   	737205      	1384456	NM  										CABIN	DISCHARGED      	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	736BP		3    			23465				"R1 EMERGENCY DOOR (OVERHEAD) STAYS LIT FOR ONLY 20 SEC."  REPLACED BATTTERY PACK.  CHECKED GOOD REF MM 33-51-01.						2	L	7	2 	4F			RT	A16WE   					 
2003010600041	20030106	00041	NM  	2003	1	6	SROM200200022    	1	20021217	G	5320	69429494	BRACKET         			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32285	1255 			23465				DURING C CHECK INSPECTION FOUND THRESHOLD BRACKET CRACKED BS 807, RBL 22 IN AFT CARGO.  REMOVED DAMAGED BRACKET AND INST	ALLED NEW PER SRM 51-30-2. MAJOR REPAIR.					2	L	7	2 	4F			RT	A16WE   					 
2003010600042	20030106	00042	NM  	2003	1	6	SROM200200023    	1	20021213	G	5310	69353509	STANCHION       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32285	1255 			23465				DURING C CHECK INSPECTION FOUND FWD CARGO BAY STANCHON CRACKED.  REPLACED STANCHON PER SRM 51-30-2. 51-10-3, MINOR REPAI	R.					2	L	7	2 	4F			RT	A16WE   					 
2003010600043	20030106	00043	NM  	2003	1	6	SROM200200024    	1	20021213	G	5320	6546533503	BRACKET         			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32285	1255 			23465				DURING C CHECK INSPECTION FOUND CRACKED BRACKET IN FWD CARGO COMPARTMENT BAY.  REPLACED BRACKET PER SRM 51-30-2, 51-10-3	.  MINOR REPAIR.					2	L	7	2 	4F			RT	A16WE   					 
2003010600044	20030106	00044	NM  	2003	1	6	SROM200200025    	1	20021216	G	5210	65458001215	SKIN            			BOEING	737   	737205      	1384456	NM  										PAX DOOR	WORN            	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32285				23465				DURING C CHECK REPLACED SMALL OUTER SKIN PANEL FWD OF L-1 DOOR BETWEEN HINGES THAT HAD A PREVIOUS REPAIR OF A HOLE IN TH	E SKIN WITH A EXTERNAL DOUBLER.  REMOVED AND REPLACED PER SRM 51-30-2, 51-20-1.  MAJOR REPAIR.					2	L	7	2 	4F			RT	A16WE   					 
2003010600045	20030106	00045	NM  	2003	1	6	SROM200200026    	1	20021217	G	5720	6573771	GUSSET          			BOEING	737   	737205      	1384456	NM  										WING	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32285	1255 			23465				DURING C CHECK INSPECTION FOUND NUMBER ONE O/B FIXED FAIRING UPPER AFT GUSSET GOUGED.  REMOVED, FABRICATED AND INSTALLED	 GUSSET PER SRM 54-10-2 & 51-30-2.  MINOR REPAIR.					2	L	7	2 	4F			RT	A16WE   					 
2003010600047	20030106	00047	NM  	2003	1	6	SROM200200028    	1	20021215	G	5753	65464312	SKIN            			BOEING	737   	737205      	1384456	NM  										RT TE FLAPS	CHAFED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32285	1255 			23465				RT OUTBOARD FORE FLAP CHAFED  INBOARD END 4 INCHES FROM INBOARD END ON LEADING EDGE.  REPLACED CHAFFED SKIN PER SRM 57-5	0-1 & 51-30-2.  MINOR REPAIR.					2	L	7	2 	4F			RT	A16WE   					 
2002013000073	20020130	00073	SO  	2002	1	30	U23R624Y         	1	20020108	G	5320		BRACKET         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C505   	GL  	LT ENGINE	BROKEN          	B				K				NONE                    				G			MULTIPLE FAILURE          			IN	INSP/MAINT     	1			EA	07	35GK	178  	36   			3449174	322317	992855		UPON ANNUAL INSPECTION OF THE AIRCONDITIONING COMPRESSOR, IT WAS NOTED TO MOVE AROUND BY PRESSING ON THE AIRCONDITIONING	 BELT FURTHER INSPECTION REVEALED THE FORWARD AIRCONDITIONING BRACKET TO BE BROKEN. DURING REMOVAL OF THE BRAKET IT WAS 	ALSO FOUND TO BE BROKEN AT THE LOWER FORWARD INBOARD ATTACH POINT ALSO. THERE WAS A TOTAL OF TWO BRAKES FOUND OF THIS IT	EM ONE HIDDEN AND ONE NEEDING A MIRROR TO LOCATE.			1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2002081400032	20020814	00032	CE  	2002	8	14	UVVR200200001    	1	20020805	G	4940	1666731	GASKET          			RKWELL	NA265 	NA26565     	7630107	CE  										APU START	FAILED          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CE	05	65AK					46535				"AFT FUSELAGE HOT" LIGHT CAME ON IN FLIGHT. CREW MADE LANDING AT SUS. AVMATS TROUBLESHOT PROBLEM, FOUND APU START BYPASS	 VALVE GASKET BLOWN - CAUSING HOT BLEED AIR TO TRIP THERMAL SWITCH, ILLUMATING WARNING LIGHT. REMOVED AND REPLACED GASKE	T WITH NEW GASKET.				2	L	7	2 	4J			 	A2WE    					 
2002020500058	20020205	00058	NE  	2002	2	5	WRLA200201       	2	20020201	G	7230		BLADE           			DOUG  	DC10  	DC1030      	3023501	WP  	GE    	CF6   	CF650C2     	30018	NE  					COMPRESSOR	VIBRATION       	A			WRLA	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			SO	11	526MD					46998	517515			NR 1 ENGINE VIBRATION 80-95, ALL OTHER INDICATIONS NORMAL.  EVENT OCCURRED AT THE TOP OF THE CLIMB SEGMENT WHEN THE FLIG	HT AS THE CREW WAS LEVELING THE AIRCRAFT.  THE CAPTAIN ELECTED TO RETURN TO MIA.  LUBED FAN BLADES, PERFORMED MAX POWER 	RUN AT 80-95 PERCENT TRANSITION, NO VIBRATION NOTED.  THE ENGINE WAS RUN AT ALL POWER SETTING FROM IDLE TO TAKEOFF POWER	 WITH NO VIBRATION NOTED ON THE NUMBER ONE ENGINE.			2	L	7	3 	4F	4	F	 	A22WE   	E23EA				 
2002101500038	20021015	00038		2002	10	15	YHLR200200001    	4	20021010	G	3497	2055612	CONNECTOR       			AMRGEN	AA5   	AA5B        	3960105	SO  										GPS SYSTEM	ARCED           	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SO	17	854PD					AA5B0854				AIRCRAFT OWNER STATED THAT UNIT QUIT WORKING IN FLIGHT. REMOVED GPSCOMM FROM TRAY AND FOUND THAT PINS 21 & 25 HAD ARCED.	 FOUND THAT GPSCOMM WAS NOT SEATED PROPERLY IN TRAY AT TIME OF ORIGINAL INSTALLATION BY GULF COAST AVIONICS. REPLACED CO	NNECTOR & DAMAGED PINS 21 & 25. THIS COULD HAVE BEEN PREVENTED IF THE ORIGINAL INSTALLER (GULF COAST AVIONICS) HAD VERIF	IED THAT THE UNIT WAS SEATED PROPERLY & CORRECTLY IN THE TRAY.			1	L	7	1 	3O			 	A16EA   					 
2002092000072	20020920	00072	SW  	2002	9	20	YT2R01050763     	1	20020808	G	6230	206010443001	BEARING         			BELL  	206   	206L3       	1182108	SW  										SWASHPLATE	ROUGH           	C			YT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	206MB					51321				SWASHPLATE BEARING SERIAL NUMBER F02-09999 IS ROUGH AND HAS A CATCH TO IT WHEN INSTALLED.  CAUSED HIGH IPS.						1	G	7	1 	3U			 	H2SW    					 
2002101000112	20021010	00112	SW  	2002	10	10	YT2R631356       	1	20020816	G	6320	407375001105	INDICATOR       			BELL  	407   	407         	1182206	SW  										MGT	FAILED          	B			YT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	407KA	592  				53121				INDICATOR HAS FAILED (FALSE EXCEEDANCES THAT CANNOT BE CLEARED).  WHEN LAPTOP IS CONNECTED GET AN ERROR SAYING THAT IP A	DDRESS IN NOT CORRECT.					1	G	7	1 	3U			O	H2SW    					 
2002101000113	20021010	00113	SW  	2002	10	10	YT2R631357       	1	20020816	G	7714	407375002103	INDICATOR       			BELL  	407   	407         	1182206	SW  										NG	FAILED          	B			YT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	407KA	592  				53121				REPLACED GAUGE, INDICATOR HAS FAILED (FALSE EXCEEDANCES) THAT CANNOT BE CLEARED.  WHEN LAPTOP IS CONNECTED GET AN ERROR 	SAYING THAT IP ADDRESS IS NOT CORRECT.					1	G	7	1 	3U			O	H2SW    					 
2002111500013	20021115	00013	SW  	2002	11	15	YT2R631367       	1	20021023	G	2840	7G547	SWITCH          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL BOOST	INOPERATIVE     	B			YT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01										FUEL BOOST SWITCH INOPERATIVE UPON INSTALLATION.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002111500014	20021115	00014	SW  	2002	11	15	YT2R631369       	1	20021023	G	2840	7G547	SWITCH          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL BOOST	INOPERATIVE     	B			YT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01										FUEL BOOST SWITCH INOPERATIVE UPON INSTALLATION.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002012400030	20020124	00030	EA  	2002	1	24	YTRR077529       	2	20020102	G	7322	3028325	LINE            		3028325     	BELL  	212   	212         	1181420	SW  	PWA   	PT6   	PT6B36      	52043	EA  					P3 FILTER	CRACKED         	H			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	293CA				1	33005	CPPS62245			P3 FILTER LINE ON NR 1 ENGINE CRACKED, REPLACED P3 FILTER LINE ASSEMBLY WITH NEW SERVICEABLE ASSEMBLY.						1	G	7	1 	4U	4	U		H4SW    	E4EA				 
2002032800029	20020328	00029	SW  	2002	3	28	YTRR077999       	1	20020315	G	6230	204011404125	BUSHING         			BELL  	212   	212         	1181420	SW  										SWASHPLATE	WORN            	H			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	250MH	438  				30519				SWASHPLATE SUPPORT BUSHINGS AT GIMBAL RING MOUNT HAD ELONGATED BOLT HOLE. COMPONENT HAD BEEN IN SERVICE FOR APPROXIMATEL	Y HALF OF ITS LIFE.					1	G	7	1 	4U				H4SW    					 
2002032800030	20020328	00030	SW  	2002	3	28	YTRR078000       	1	20020315	G	7331	206364601101	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	MISOVERHAULED   	H			YTRA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	104RT					51364				UPPER FUEL PROBE WAS OVERHAULED. THE UNIT FAILED 7 DAYS AFTER INSTALLATION.						1	G	7	1 	3U				H2SW    					 
2002041900031	20020419	00031	SW  	2002	4	19	YTRR078431       	1	20020410	G	7334	2060751865	METER           			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					FUEL PRESSURE	MISREPAIRED     	H			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	5750Y					45517				FUEL PRESSURE / LOADMETER WAS OVERHAULED. THE FUEL PRESSURE SIDE FAILED AFTER 1.0 HRS IN SERVICE. THE UNIT WAS RETURNED 	FOR WARRANTY REPAIR.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2002041900032	20020419	00032	SW  	2002	4	19	YTRR078432       	1	20020410	G	6520	206011728001	TRUNNION        			BELL  	206   	206L4       	1182110	SW  										T/R GEARBOX	WORN            	H			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	207RT	464  				52207				TRUNNION WAS FOUND WORN BEYOND LIMITS DURING A 100 HR A/F INSPECTION.						1	G	7	1 	3U			NC	H2SW    					 
2002042300053	20020423	00053	NE  	2002	4	23	YTRR078434       	2	20020416	G	7532		DIAPHRAGM       			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					BLEED VALVE	RUPTURED        	H			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	250MH					30519				BLEED VALVE LEAKING DUE TO RUPTURED DIAPHRAM.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2002042300054	20020423	00054		2002	4	23	YTRR078435       	4	20020416	G	3457	13824120234	RECEIVER        			BELL  	206   	206L3       	1182108	SW  										GPS	FAILED          	H			YTRA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	473RT					51473				GPS UNIT REPAIRED.  IT REMAINED SERVICEABLE FOR 4 MONTHS FROM THE DATE OF INSTALL THE FAILED AGAIN.						1	G	7	1 	3U				H2SW    					 
2002082700066	20020827	00066	GL  	2002	8	27	YTRR080718       	2	20020819	G	7261	357950111452	SHAFT           			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					WORN	WORN            	B			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	207RT	555  				52207				OIL PUMP SPLINES WORN EXCESSIVELY.						1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2002082700067	20020827	00067	GL  	2002	8	27	YTRR080719       	2	20020819	G	7261	357950111452	SHAFT           			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					OIL PUMP	WORN            	B			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	207RT	1343 				52207				OIL PUMP SPLINES WORN EXCESSIVELY.						1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2002082700068	20020827	00068	GL  	2002	8	27	YTRR080720       	2	20020819	G	7261	357950111452	SHAFT           			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					OIL PUMP	WORN            	H			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	520RL	1100 				52052				OIL PUMP SPLINES WORN EXCESSIVELY.						1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2002121700126	20021217	00126	SW  	2002	12	17	YTRR081614       	1	20021211	G	5302	206033426001	SUPPORT         			BELL  	206   	206L3       	1182108	SW  										T/R GEARBOX	CRACKED         	H			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	405RL	4290 				51405				CASTING CRACKED AT AFT LEFT T/R GEARBOX MOUNTING HOLE.						1	G	7	1 	3U				H2SW